230 20 8242 https://digitalprojects.uah.edu/files/original/40/877/uah_uahp_322_323.pdf 5a1644330c77a1c16d7708fcdd0515e9 PDF Text Text f', CAIIC,, A.Jo . �> FOR RELEASE: July 26, 1969 PHOTO NO: 1969 Picnic "o. 8 PHOTO CREDIT: NATIONAL AERONAUTICS ANO SPACE ADMINISTRATION HAH.SHALL SPACE FLIGI-IT CENTER, Ala. -- A ca.Mera.nan catches Dr. \!ernher von Brann, director of the l!ASA.-Harshal.l Sp ace Flight Center, his son, Peter, and da'U{;hter, liargrit, as they arrive at the enployee picnic held to celebrate rian 1 s first landing on the moon six days earlier. In the foreground is David H. Newby, director of Administration and Technical Services at HSFC. I � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource UAH Photograph Collection Identifier An unambiguous reference to the resource within a given context UAH Photograph Collection Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context uah_uahp_322_323 Title A name given to the resource Wernher von Braun with daughter Margrit and son Peter in the crowd at the 1969 MSFC employee picnic. Description An account of the resource MSFC Director of Administration and Technical Services David H. Newby is shown in the foreground. Creator An entity primarily responsible for making the resource United States. National Aeronautics and Space Administration Date A point or period of time associated with an event in the lifecycle of the resource 1969-07-26 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Newby, David H. Von Braun, Margrit Von Braun, Peter Von Braun, Wernher, 1912-1977 Company picnics George C. Marshall Space Flight Center Project Apollo (U.S.) Huntsville (Ala.) Madison County (Ala.) Type The nature or genre of the resource Photographs Still Image Source A related resource from which the described resource is derived UAH Photograph Collection University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource uah_photos_2019_05 https://digitalprojects.uah.edu/files/original/40/878/uah_uahp_324_325.pdf 8203f73089c62f6939100a2f5cbfc3fe PDF Text Text �I ····- _..,._. -- ___,,.,. ·-- ·- ····-··. ···-·· · - ··---·--· C FOR RELEASE: July 26, 1969 PHOTO NO: 1969 Picnic ;�o. h3 PHOTO CREDIT: NATIONAL AERONAUTICS AND SPACE AO;AINISTRATION }fftu"qSHALL SPACE FLIGIIT CENTER, Al.a. -- Dr. Wernher von Braun, director of the NASA-Harshall Space Flight Center, stakes claim to a table for the picnic celebrating man 1 s first lunar landing. With Dr. von Braun are his wife , Maria (seated, right), and son, Peter (back to camera). His daughter, Margrit , also was present but is hidden from view by friends in this view. I � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource UAH Photograph Collection Identifier An unambiguous reference to the resource within a given context UAH Photograph Collection Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context uah_uahp_324_325 Title A name given to the resource Wernher and Maria von Braun claim a table with son Peter at the 1969 MSFC employee picnic. Creator An entity primarily responsible for making the resource United States. National Aeronautics and Space Administration Date A point or period of time associated with an event in the lifecycle of the resource 1969-07-26 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Von Braun, Maria Von Braun, Peter Von Braun, Wernher (1912-1977) Company picnics George C. Marshall Space Flight Center Huntsville (Ala.) Madison County (Ala.) Project Apollo (U.S.) Type The nature or genre of the resource Photographs Still Image Source A related resource from which the described resource is derived UAH Photograph Collection University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource uah_photos_2019_05 https://digitalprojects.uah.edu/files/original/40/879/uah_uahp_326_327.pdf 6d1cf0a2e4fd1f7e6cf3070b79428f19 PDF Text Text .,.� �I > FOR RELEASE: July 26, 1969 PHOTO NO: 1969 ?icnic do. 17 PHOTO CREDIT: NATIONAL AERONAUTICS AND SPACE ADMINIS1 RATION :t-WIBHALL SPACE FLIGHT CENl'ER, Ala. -- Mrs. Jean Drake o f the Safety Office accepts her Award of Achievement for the Apollo 11 mission from Dr. Wernher von Braun, director of the �ASA-Marshall Space Flight Center. - The presentation was symbolic of' similar presentations to be made to a number of other employees later. The presentation was made during the special employee picnic held at celebrate man I s first landing on the moon, an event that occurred six days before the picnic. at left is Hrs . Lois Smith. Looking on � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource UAH Photograph Collection Identifier An unambiguous reference to the resource within a given context UAH Photograph Collection Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context uah_uahp_326_327 Title A name given to the resource Wernher von Braun presents an Award of Achievement to Jean Drake at the 1969 MSFC employee picnic. Description An account of the resource Drake worked in the Safety Office. Lois Smith is shown seated at left. Creator An entity primarily responsible for making the resource United States. National Aeronautics and Space Administration Date A point or period of time associated with an event in the lifecycle of the resource 1969-07-26 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Drake, Jean Smith, Lois Von Braun, Wernher (1912-1977) Company picnics George C. Marshall Space Flight Center Huntsville (Ala.) Madison County (Ala.) Project Apollo (U.S.) Type The nature or genre of the resource Photographs Still Image Source A related resource from which the described resource is derived UAH Photograph Collection University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource uah_photos_2019_05 https://digitalprojects.uah.edu/files/original/46/896/spc_hfac_000001.pdf a36a9b4c462c2ad835e657c6902a4311 PDF Text Text � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Human Factors Engineering Collection Identifier An unambiguous reference to the resource within a given context Human Factors Engineering Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/12">View the Human Factors Engineering Collection finding aid in ArchivesSpace</a> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_hfac_000001 Title A name given to the resource Brian Nelson and Nelson Brown conduct Human Factors Engineering experiments on the KC-135 Vomit Comet. Creator An entity primarily responsible for making the resource United States. National Aeronautics and Space Administration Date A point or period of time associated with an event in the lifecycle of the resource 1968-05 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Brown, Nelson Nelson, Brian Human factors in engineering design KC-135 (Tanker aircraft) Type The nature or genre of the resource Contact sheets Photographs Still Image Source A related resource from which the described resource is derived Human Factors Engineering Collection University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Provenance A statement of any changes in ownership and custody of the resource since its creation that are significant for its authenticity, integrity, and interpretation. The statement may include a description of any changes successive custodians made to the resource. This item was digitized for the Apollo 11 50th anniversary celebration. Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource ap11_exhibit_2019_08 https://digitalprojects.uah.edu/files/original/46/897/spc_hfac_000002.pdf 8a799b09d4cd358173b7001f3c4de161 PDF Text Text � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Human Factors Engineering Collection Identifier An unambiguous reference to the resource within a given context Human Factors Engineering Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/12">View the Human Factors Engineering Collection finding aid in ArchivesSpace</a> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_hfac_000002 Title A name given to the resource Brian Nelson and Nelson Brown conduct Human Factors Engineering experiments on the KC-135 Vomit Comet. Creator An entity primarily responsible for making the resource United States. National Aeronautics and Space Administration Date A point or period of time associated with an event in the lifecycle of the resource 1968-05 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Brown, Nelson Nelson, Brian Human factors in engineering design Type The nature or genre of the resource Contact sheets Photographs Still Image Source A related resource from which the described resource is derived Human Factors Collection University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Provenance A statement of any changes in ownership and custody of the resource since its creation that are significant for its authenticity, integrity, and interpretation. The statement may include a description of any changes successive custodians made to the resource. This item was digitized for the Apollo 11 50th anniversary celebration. Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource ap11_exhibit_2019_08 https://digitalprojects.uah.edu/files/original/23/924/spc_lund_000000.pdf 12dc32557a00ff8c6dbbb415b32d31f4 PDF Text Text � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Charles A. Lundquist Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/46" target="_blank" rel="noreferrer noopener">View the Charles A. Lundquist Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Charles A. Lundquist Collection Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_lund_000000 Title A name given to the resource Charles Lundquist briefing Wernher von Braun and Hermann Oberth on satellite orbits. Creator An entity primarily responsible for making the resource United States. National Aeronautics and Space Administration Temporal Coverage Temporal characteristics of the resource. 1950-1959 Subject The topic of the resource Lundquist, Charles A. Oberth, Hermann, 1894-1989 Von Braun, Wernher, 1912-1977 Satellites--Orbits Type The nature or genre of the resource Photographs Still Image Source A related resource from which the described resource is derived Charles A. Lundquist Collection University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Provenance A statement of any changes in ownership and custody of the resource since its creation that are significant for its authenticity, integrity, and interpretation. The statement may include a description of any changes successive custodians made to the resource. This item was digitized for the Apollo 11 50th anniversary celebration. Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource ap11_exhibit_2019_08 https://digitalprojects.uah.edu/files/original/19/927/spc_stuh_000006.pdf b987dbe9ee337bcb23583dee53b7697b PDF Text Text � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Ernst Stuhlinger Collection Identifier An unambiguous reference to the resource within a given context Ernst Stuhlinger Collection Description An account of the resource Ernst Stuhlinger was born in 1913 in Niederrimbach, Germany, and died in 2008 in Huntsville, AL, USA. Stuhlinger was a German scientist brought to the United States through Operation Paperclip, and like many of his Paperclip peers, he became a naturalized United States citizen in 1955. Stuhlinger’s accomplishments in both promoting and advancing space travel were many. He worked as a technical consultant with Walt Disney Pictures to create “Man in Space” (1955), “Man and the Moon” (1955), and “Mars and Beyond” (1958). Stuhlinger contributed to the 1958 launch of the Explorer I satellite by inventing a timing device, helped design the solar x-ray telescope used in the Skylab space station, worked on the Apollo Telescope Mount, worked on the initial phases for what would become the Hubble Space Telescope, and authored “Ion Propulsion for Space Flight.” Stuhlinger served as the Marshall Space Flight Center in Huntsville’s director of the Space Sciences Laboratory from 1960 to 1968, and then as the associate director for science from 1968 to 1975; he retired in 1975. After retiring, Stuhlinger joined the University of Alabama in Huntsville as an adjunct professor and senior research scientist, and he stayed on for two decades. Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/91">View the Ernst Stuhlinger Collection finding aid on ArchivesSpace</a> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stuh_000006 Title A name given to the resource NASA personnel wait to greet President John F. Kennedy during his second visit to Huntsville. Description An account of the resource Kennedy visited Huntsville on Armed Forces Day 1963. He first visited the area on September 11, 1962. Creator An entity primarily responsible for making the resource United States. National Aeronautics and Space Administration Date A point or period of time associated with an event in the lifecycle of the resource 1963-05-18 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource George C. Marshall Space Flight Center Redstone Arsenal (Ala.) Visits of state Huntsville (Ala.) Madison County (Ala.) Type The nature or genre of the resource Photographs Still Image Source A related resource from which the described resource is derived Ernst Stuhlinger Collection Recognition Collection, Box 2, Folder 3.14 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Provenance A statement of any changes in ownership and custody of the resource since its creation that are significant for its authenticity, integrity, and interpretation. The statement may include a description of any changes successive custodians made to the resource. This item was digitized for the Apollo 11 50th anniversary celebration. Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource ap11_exhibit_2019_08 https://digitalprojects.uah.edu/files/original/19/928/spc_stuh_000007.pdf 115a6635a0e54c9542097c6401f74813 PDF Text Text � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Ernst Stuhlinger Collection Identifier An unambiguous reference to the resource within a given context Ernst Stuhlinger Collection Description An account of the resource Ernst Stuhlinger was born in 1913 in Niederrimbach, Germany, and died in 2008 in Huntsville, AL, USA. Stuhlinger was a German scientist brought to the United States through Operation Paperclip, and like many of his Paperclip peers, he became a naturalized United States citizen in 1955. Stuhlinger’s accomplishments in both promoting and advancing space travel were many. He worked as a technical consultant with Walt Disney Pictures to create “Man in Space” (1955), “Man and the Moon” (1955), and “Mars and Beyond” (1958). Stuhlinger contributed to the 1958 launch of the Explorer I satellite by inventing a timing device, helped design the solar x-ray telescope used in the Skylab space station, worked on the Apollo Telescope Mount, worked on the initial phases for what would become the Hubble Space Telescope, and authored “Ion Propulsion for Space Flight.” Stuhlinger served as the Marshall Space Flight Center in Huntsville’s director of the Space Sciences Laboratory from 1960 to 1968, and then as the associate director for science from 1968 to 1975; he retired in 1975. After retiring, Stuhlinger joined the University of Alabama in Huntsville as an adjunct professor and senior research scientist, and he stayed on for two decades. Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/91">View the Ernst Stuhlinger Collection finding aid on ArchivesSpace</a> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stuh_000007 Description An account of the resource Kennedy visited Huntsville on Armed Forces Day 1963. He first visited the area on September 11, 1962. Creator An entity primarily responsible for making the resource United States. National Aeronautics and Space Administration Date A point or period of time associated with an event in the lifecycle of the resource 1963-05-18 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource George C. Marshall Space Flight Center Redstone Arsenal (Ala.) Visits of state Huntsville (Ala.) Madison County (Ala.) Type The nature or genre of the resource Photographs Still Image Source A related resource from which the described resource is derived Ernst Stuhlinger Collection Recognition Collection, Box 2, Folder 3.14 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Provenance A statement of any changes in ownership and custody of the resource since its creation that are significant for its authenticity, integrity, and interpretation. The statement may include a description of any changes successive custodians made to the resource. This item was digitized for the Apollo 11 50th anniversary celebration. Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource ap11_exhibit_2019_08 Title A name given to the resource Crowds and television cameras wait for President John F. Kennedy during his second visit to Huntsville. https://digitalprojects.uah.edu/files/original/20/1137/spc_stnv_000053.pdf 55709717c2e368c830bd610c1f0dc8a7 PDF Text Text YllWEF 8F THE Y h l H E l FLlCPT AWIREWESS SEMIMAR YAMRED SPACECRAFT CENTER S f PTtYBER 15-28, 1161 �FOREWORD THE PURPOSE OF THIS SEMINAR WAS TO PROVIDE THE GOVERNMENTI INDUSTRY TEAM WITH NEW INSIGHTS INTO THE FUTURE OF MANNED SPACE FLIGHT AND ITS ATTENDANT REQUIREMENTS FOR QUALITY WORKMANSHIP IN THE PROSECUTION OF APOLLO AND FOLLOW-ON PROGRAM ACTIVITIES. GUIDELINES, OBJECTIVES, GOALS AND MOTIVATIONAL INNOVATIONS WERE DISCUSSED, AND PRESENTATIONS WERE GIVEN BY KEY MANAGEMENT PERSONNEL OF NASA AND THE AEROSPACE INDUSTRY. �AGENDA SEMINAR ON MANNED FLIGHT AWARENESS Maned $acecraft Center Houston, Texas Thursday, September 25 - - SESSION I NASA Management: The Manned Flight Awamness Challenge as NASA Sees i t SESSION II Industrial Executives: Industry's View of the Future Session Monitor: Mr. Philip H. Bolger Session knitor: Mr. Philip H. Bolger Opening Remarks Philip H. Balger, Acting Director Manned Space Flight Safety McDonnell Douglas Astranautics Company Walter F. Burke, President Welcome Address Dr. Robert R. Gilruth, Director Manned Space Flight Center North American Rockwell William B. Bergen, President The Boeing Company Harold J. McClellan, General Manager, Southeast Division, Aerospace Division Panel Discussion Moderator W. C: Schneider NASA - Industry W. C. Wi& R. A. Petfane R. R. GilruUl W. F. Burke W. 0. Bergen Dr. George Mueller Keynote Address "The Future of Manned Associate Administrator for Space Flight" Manned Space Flight Apollo12and!&yond Dr.Rocwktrone Apollo Program Director Apollo Applications Program Planning William C. Schneider, Director Apollo Applications Program The Management Challenge b e James, Director Pro@m Magement Marshall Space Flight Center Astronaut Participation Major Stuart Roosa, USAF in the Manned Flight Astronaut Awareness Program - H. J. McClellan Panel Members Friday, September 26 Moderator Dr. Preston T. Farish John Mill~Mtt- IBM The heing Company Tom Scott Dwayne Gray - North American Rockwell T ~ ~ ~ T o c-TRW co Harold Durfee &urnan Aerospace Corporation Gordon Macke McDonntll Douglas As~ronauticsCompany Space Station Task Group, Manned Spaceflight Om ter John W. Small, Assistant Field Director Manned Flight Awareness Themes and Progam Continuity Reliability and Quality Assurance Office, NASA Headquarters Dr. John Condon, Director 1. Central Themes and Awards Al Chop, Headquarters West Coast Representative, Manned Flight Awmncss Off ice Industrial Relations and Compensation Service, Texas Instruments, Incorporated Dr. Charles Hughes, Director 2. Manned Flight Awareness Warking Tosls: Pastas, Newslettar, Films, Decals, etc. Eugene E. Hixbn, Chief, Manned Flight Awareness Office, Manned Spacecraft Center "Innovations in Motivation" Moderator Sununary and Closing Philip H. Bolger - SESSION Ill - MFA Concept at Work Session Monitor: Dr. Preston T. Farish - Eugene E. Horton - Remarks �TABLE OF CONTENTS Page OPENING REMARKS Philip H. Bolger - 1 WELCOME ADDRESS - Dr. Robert R. Gilruth 2 MANNED FLIGHT AWARENESS CHALLENGE AS NASA SEES I T THE FUTURE OF MANNED SPACE FLIGHT - Dr. George Mueller APOLLO 12 AND BEYOND - Dr. Rocco Petrone APOLLO APPLICATIONS PROGRAM PLANNING -William C. Schneider THE MANAGEMENT CHALLENGE - Lee James ASTRONAUT PARTICIPATION IN THE MANNED FLIGHT AWARENESS PROGRAM - Major Stuart Raosa, USAF INDUSTRY'S VIEW OF THE FUTURE Walter F. Burke William B. Bergen Harold J. McCleilan PANEL DISGUSSiON MFACONCEPTATWORK Johfi W. Small Dr. Jab Condon Dr. Wlarjes Hughes INNOVATIONS IN MOTIVATION MANNED FLIGHT AWARENESS THEMES AND PROGRAM CONTINUITY CENTRAL THEMES AND AWARDS - Al Chop MANNED FLIGHT AWARENESS WORKING TOOLS - Eugene E. Horton CLOSING REMARKS - Phi lip H. Bolger iii �OPENING REMARKS PHILIP H. BOLGER Acting Director Manned Space Flight Safety The successful lunas landing and completion of the flight of Apollo 11achieved a national objective in this decade and is a significant milestone in man's continuing progress in space exploration. Historically, achievements of such magnitude, requiring concentrated efforts over an appreciabh time period, are followed by a letdown aad general relaxation ~f the personnel involved. Ea addition, this letdown may be amplified by a serious morale problem when funding cutbacks a r e experienced. The result is a decline in the required attentkoa ts detailed w o r l n n a ~ h i pwhieh can cause a rise in a d d e n t rates and potential loss of life. Ta ctam* tBew p&@atidmmde ~uqlacency prdem in the ht pmgram, WB Gcwsmnmsa% daFi tne; rn Mmn& l?li&&Awarenp;m &~xllinaris bhg eollmlwbd. The abjer&itre af this +emhm Irs the In We way we ~$11get the rn6sli~agefrom NASA Maaagemetat ta the X&WC$ua2a m&pc-maiMa for dolng the work t b t k 76W ta t ~ h a Pi& g quallty of wmkmau~bipIn the aem~spaeefame. The grc%=&iwsof tSlis 8ez~ias-r WUbe trasnsibed are &tenid%, hopefully wiWn w e m~ath. d d o t & &to CBw who Mow, I have a sta%mtfro-m Dr. P a b e , who was d l e to be here isday, he IEL quite interested in o m lihmed Fltght Awareness P r o g r m ;ui$ what it is trying to do. ~r paim says: . "1 wish to ezpreae my regret W I eun unable Q participate in the Msrnned Flight AwareSeminar b e c a r e of previous commitment~.The subjects that you will discuss tue of the greatest importance to the future of Manned Space Flight. It is imperative that the NASA/Contractor Team maintain it&mamenturn a d cantinue to achieve the highest degree of quality workmanship. I rediee that this is a difficult task to achieve in thie period of cutback in space aetivities following the succesrs of the Apollo 11mission. On the other hand, however, we a r e entering a new e r a of relatively stable space flight activity and will be undertaking new pragrams that Dr. Mueller and his associates will discuss witb you. We must impress on the aerospace worker force the fact that our future in space is a bright one and that we will continue to move forward in achieving an ever greater operational capability and broadeningour scientific knowledge in q a c e . To achieve these goals we are as always dependent upon the individual worker, his motivation and interest, and ultimately the quality of Ms workmanship. I know that you support my views on these subjects and will make every effort to bring our future space f l w t programs to successful achievement. The Manned Flight Awareness E o gram is one of our most valuable tools in support of these objectives slnd I hope you will make every effort to utilize its capabilities to the utmost. Now, we've asked you to come today to discuss some ~elativelyserious problems that a r e confronting us in Ohis period of instability a s we a r e cutting back a f b r the Apollo 11 succesrs. Our speakers will address these subjects in light of their particular programs. �WELCOME ADDRESS DR. ROBERT R. ClLRUTH Director Manned Space Flight Center Good morning, I am happy to welcome you to this seminar. I would especially like to thank Walter Burke, Bill Bergen, Pat McClellan, and you other leaders in industry for taking time to be with us today, and to bring us views for the future of manned space flight from your perspective in industry. It is fitting, I believe, that thismeeting is being held following the most remarkable expedition of all history-manf s f i r s t journey to the moon. Neil Armstrong described Apollo 11 as lla giant leap for mankind, " and there is no question but that i t was a giant leap. It proved among other things that the moon is no longer quite so remote and inaccessible a s i t had been. It didnot assure us, however, that the next step in space would be equally successful. Whether o r not i t is will depend to a very large extentupon the inspiration and leadership, and the imagination that will be shown by those of u s who a r e in this room today. I think this can be a very valuable meeting for all of us. We a r e going to hear a bit aboutwhat is planned, what i s possible, both from the viewpoint of NASA and from industry. I believe that this frank exchange of views and comments can give each of us a freshperspective on our jobs, and a better understanding of what lies ahead in our national space program. I think we a r e all concerned about the period of let-down that tends to occur following a great milestone, such a s has just been completed. We all know that we cannot afford a let-down. There a r e many important missions to be flown. There a r e many more flightcrews waiting their turn for flights. We know that we a r e being looked a t very critically by millions inthis nation and abroad. We must continue to demonstrate to them that success can follow success, and that the words lfMade in USAu stand for excellence and worth in leadership throughout the world. Success results, I believe, from the interaction of many people doing many things. But success can never come about without pride. It cannot come about without personal dedication and a fundamental understanding of the job that is to be done. Unfortunately, motivation is an intangible. It i s not something that the Federal Government can write into its contracts. It has to be self-induced. It comes from within. It results from knowing that the work we a r e doing is important and that the job we have been given is more than just an 8-hour day. It is impossible to get everyone, in all our organizations, to think like this, but if we could just raise the number by 10, 25, o r even 50 percent, then I believe we would be working in an entirely new realm, with f a r greater potential for success and less probability of costly mistakes. I cannot over-stress the importance that NASA management attaches to the Manned Flight Awareness Program. We know that the program has and will continue to have a very important and positive effect on our flight missions, an effect that can be felt in such vital areas a s crew safety, cost, schedules, and new technology. I hope that each of you will find ways in this conference to put the tools of our Manned Flight Awareness effort to use to revitalize and rededicate the efforts of this great team. I wish this conference every success, and again welcome. Thank you all very much. �MANNED FLIGHT AWARENESS CHALLENGE AS N A S A SEES IT ��1-r qlooration program; one that is, however, I think, a wite festsllhle wms d m e a t also serve# as a proving ground for planetary exploration, because it brm mt that moSt Q%ofbt'W.qg8 that we w a need to have d e n we explore tha planets can be daveloped and tested a$ &a moan, w%$&31~)- oowiderable irer.vi~sin time 4money. P m n M FearlqlNu Iiuum.E COST REWFION USE OF SPACE RIGHT SCIEP1Q AQPLICATIW & lEClW3LOCY .TO ENSURI INCSWSING RFfUMS IN SCIENCE AND APPLICATIONS USE OF EARTH ORBIT EXPLORATION OF THE SOLAR SYXTEM LUNAR MPLORATf ON 010 STRUCTURE A PROGRAM Of INCRWSINO CAPABILI.TY - M A W MPCOaATlBN FIGURE 1A The results sf this h program, as shown in FipFve (iaad I im kind of skipping to &e end and then I will come b w k and fill in-htwm) a r e first of all that it fulfills the objactiveer d the wieme 4 applications disciplines, it pravidee an agpeseiive planetary program, and a capability for a lrmar eqloration program leading to the QVQZIW e-xploiWon of the moon. In ptw&t&w, it p r w l d e ~a r m o d 1 e pregram leading to a surface base. It p s a v i d ~a capability for a program to urn e%fiorbit for M t m e olppltoathm and mission operations. It deveiops anew spa4xtflight aagability of ccndderable power and it provides a precursor data technology system for manned planetary exploration in the 86's. It also provides a basis for cost reduction. The capabilities that are developed in the course of carrying out this program include (Figure 2B), in the case of the aut.omat;ed spaeecd2 (which a r e still used f a r those naihlsions where they a r e more effective), the develspaamraft; the use of special-purpose spacecraft, particularly for those opment of longduration interplanethings that r q i r e eantisuinf! observations; and the operational earth application spacecraft where you are, for example, taking the f~Uow-msto the mros and the Nimbus satellites. Much of the equipment developed is designed for a combWbn d m m m d aur$ wtamated operation. For example, the astronautical observatories are a dual mode type of operation where raen will work with the telescopes over a period of time and then allow them to fly freely a3sd operate aUOom%tically. Man in this kind of ttn application will be used primarily for changing instrume~ts. The lunar rover i5 an example of a dual mode system in which we normally will have a manned operation of the rover, but it will have another mode that will permit it to carry out long traverses in an automated fashim. And then we will have the man-tended satellites of many kinds: that have been proposed, including even manufactming facilities where they can be automated. 1 INESRATEO SPACE PRaORAM SPlCE GLPABILIW DEWLOWOIE INTEGRATED PROGRAM RESULTS 1910- 1980 !aw!El lLWODURATIW rn FULFILLS RR OBJICTIM ff THE SCIENCE & APPLICATION Q I $ C I P l I R S m m w m R Y SIC *SPfCIM PURPOSE SIC a OPERATIWAL WR7H APPLICATIONS Sk PROVIBES AN AWESSILT PUWFTARY PROGRAM PIZOVlBES CAPA5ltlTY FOR A LUNAR EXPLORATION PROGRAlW WIDlNG TO EXPLOITATION PROVIDES CAPABILITY FOW A PROGRAM TO USE EARTH OXBIT S C I M Q , APPLICATIOMS &MD MISSION OPERATIONS b ASTRBUUdICAL . L M OMAN INSlRUMB175 RWER mom sAmLrrs &&.!a SPhCE STATION MODULE 8 ATIACHEB UBM(AT0RIIS DEVELOPS NEW SPA& FLIGHT CAPABILITY LMIB CREW CAPSULE BROVIMS PBeClJRS061 DATA & TECkMOLOCY EXPLORATlON IN T M rar FOR MANNED PlANETARY GWERIU USE $PAC€ SHUTTLE PROVIDES A BASIS F O R COST REDUCTION a WCLUR $HUTRE c j P A C f TUG PROPULSION MOUE FIGURE 2A FIGURE 28 . �its attached labonabasiew. We also have In the mmplebly masTFec3 wea, we have tlra space atatim module that .t.caa be wed for wureignct to the moon or for e s c u r s i w from w e arbit to such things be a mew another In the earth b a i t . For general w, we prerp& the d ~ l w ~af1a spwe ~ t thtf.le f ~ earth r axface ta eartb orbit and return; a nwlaar sWt&&r$oiagfmm e m orbit t.elumw o&t eula ratnrn; md a mas tug wtri~h,for e-xample, is used fog &&+b-orbit~hmge8 near a 8WWt. 4%e space &g, incidmtauy, dm is designed to provide us with the aap&ilitg of lawling that menw c ~ d one the mbon. Sa it is a multipurpose ewpment. I &ink the basic strategy that we b y e devekcpd fw e a ~ mt m thid p;mg;raim is one ol first, reusability, and, if you will aetiae hem, wc gat reu&lity in two fashisns. Qw, in the o m e o0 the apace shuttle, dl of you knew, is a o&cle. W takes of£from the earth surftee, flies into orbit, rendezy~~,s witb wha#ever platform it needs to, t ~ a d 8 c~ q8 o sad pa$s to that space atatcan module, thm rebras to @art&,hiding horieontally on a mguhEPt3dlng &%p, Psrl is bmught over tO B hunch pad, r ~819d takes ~ offagain. , And here we have reuo&tb.nSeJr. In&@ sure af the nuohas shuttle we are talking about a vebide that caa operate from orbit to orbit many Urn-. We expiwQW we will be able ta cavrp out somewhere betweein 10 to 50 orbit-to-orbit flights, with- a staglet canuofem shutue, b9ff)re we have used up the ncaclear materid. In the cam of the s p m station we ~t reusability in B d:fffem& fashion, and that is tftrough the lifetime. We are talking aLborrt spaw station modules a t last ten yearm mid that are in emtlauous use for that period of time, through mpply from the w e e shuttle. I% sgssnd @ major L c o m a W t y . Although it is most diffioult in fact to aobieve, we are looldng at a program where we hay8 o d y a fmv basic modules to be dmlaperd, and then we modify them to fit particular applhtim. fn grwthl&r,are expat the w e station module to be the same, whether it happens to be in earth orbit, lunar orbit, or in eynehramus orbit. Now that places mme constraints on the first design, but once mxwmhated, it t b n has a wldca range of ueefulnem. Th8 same thing i s true af this space tug propulsion mvdule, We expect & be able: to use that ~~ltme propulsion stage for landing on the lunar surface, as well space station module to one of the man-tended satellites and back again. as for taking the crew cayldefmm Now one of tbe keys to this wbb program again is the refuelhtg in space of these various proputsion units, We d o ~ ' tintend to bring them bmk d m to the aurfaoe. In mo$t cases, we plan to reduel ahem in space. And that again means that we have a fair oargo, but a flaxihle cargo, that we can use in carrying out the program. The kind of a program that we are now talking about has a schedule that takes off from our present Apollo equipment and its uses, and begins within 1972 (in the case of L e Eartb Orbit Program), with the Garturn V warkshop ruLd ar quiewent CSM, as s h m in Figure 3A. Thatworktdtop is deeigned to provide us with an understading Bf what it takes for men ta live for extsnded periods of time in space. Its first flight is for a month, its e o m d flight is for two monfhs, and it has a Wrd flight for two months, where we will have a three man crew buildbg up aur e z p r i w e e h t the phyaiolo@cdeffwts of I q - t e r m expoewe to the space environment. In addition to that, it has a major scientific instrument, the Ape110 Telescope Mount. It is really the first manned apace d a r observatory, and it will be in w e thmmgbat that time period. We have in the integrated plan the ability to fly a secQsPd of these workshops in the 1973-1974 time frame, leading up ko the introduotion of a space etation madule in 1975. k t that earnetime, we would hope to be able to bring on the line the .space tug and the spaee shuttle. Now f ought to say a word about there dates, they are indicative of what we can do. The question, of course, is how nrueh do yau have in the way af resources? Well, we have earefdly structured this program in a way that divide# it up into p b w . So it i s a phahied program. The first phase of earth orbit operations is the &oUa d@~aticmer Program, which you are all familiar with. The second stage will be the apaee station mod&. You hawe an a p p o ~ i t to y delay that $me, if you wish, in order to conwrve near-term resourceti. And m, these date# repmeat tfis s l i e s t pos~ibledates that ane acarld bring W e inb be-. I think if you s t m c w e the progmm on lass re-s in Me near-term, then thee dsltw will stretch out. In 1978 we p h to t;crtmcbe the f i r s t of tb man-tended spomr9fts. In the case of the automatedmiesions bet w k now and 1976 and 1977, there is a very acttve program in this plan of flights, building our knowledge of tbe near-earth enuironzwst, rind leading to the use d *e space station and space tug in 1977 as it becomes awailabh. And Bere we w i l l first use ths space shuttie f o r carsyiae; the satellites b t use to fly on b p of regular rocket vehieler. We use them to atwry fh8) satellite into orbit, ahedr them out at the space station, and then p h e them in whtever orbit we redly want them eventually b be in with the spme tug. This provides us wiEb the opportunity, if wmething gaes wrong with the satellite, to go back over, pick it up, and either fix it there or Is,it h e $ to the spa- station and fix it. In the event of et major failure, we can bring it back down b earth and fix it. Thenby 1979, we wouid have et e @tationin santelaw altitmde earth orbit. We w d d expect that tbere might well be a w e station inpolar orbit, a& we would expect W t there wouM be a space station in geosynchronous orbit. The space statian modules are d p ! ~ @ d ta be coupled one to another, 80 that ane can build up the amount �of living room you have in space. We think t h d we could use 'these to build up a: space base capable of accommodating several tens Qrevenhundreds of people a earth orbit. The n u 0 - k ~shuttle would be the mdmtay for translation from earth orbit to synchro~ousorbit, or other widely varying orbits. In the lunar explor$eion grqp~rm (Figure 3B), we have onee again a takeoff from the ApoUo Program. We would expect, in the peris$ beween n m and a b u t 1975, to contfnue a program of @xploration lunar flights, using the basic Apollo squipm~tft,akded for &itidad staytime on the lunar euTfaw, md to pmvide for some observations of the moon from wbit, by using the empty bay in the wmi6e module d the orbiting vehicle. We would expect to introduce ~ometimein the 1972 time frame, a manned roving vehicle that will permit the astronauts to venture some di&t%nc-eaway from the landed lmas m98ule. We wodd q e e t by a h t 1976, or some year after the fir@*spme sWim ~ o d u l was e put into orbit, Q put one into lunar arbit, and t~ begin then to use it a s a mobile base tn lunar orbit. f t b 5 one great itage age. That is, it is 60 miles from every plwe on the lunar surface, it's in o ]pol= l m r orbit, and os a eonsleqywe, every two weekre can reach my point m the surface of the m w . F m early exploration &hisappears to be a most desirable mode of operations. It is coupled with the tug and the cpew capsule to provide ac~pabtlityfortake-off from the mace rtation module, landing at m y point on the noon, staying Wre for either two o r four t w k s , rand then rcstwminp to the space station module. The long term appli~61fft-m4 this ~rbitixxgmodule is, of course, as an intemredW@b a w If you think of what we will be d a h g on the ~ E K ) Rsomet;lme in the early 1980's o r the late 1980's depending on how we p r o c d , we would envision a situatitm in Bvhiah we h d shuttle8 going from the earthts surfme to earth orbit, carrying propellants, cargo, w d crew, to this transfer point in earth orbit, A nuclear shuttle would then pick up the cargo, load up on propellants, wid take the cargo axid crew out to the space station in lunar orbit. Here again they transfer to a third &uWe that gues from lunar orbit to the lunar surface base, and retarns to the lunar orbit. . + W?!dOEBlT MFAPARR PWlBllXM Sf-E L W LXWTlW lmmm BRBEOm'mBICE MANNED MMMeD INSTRUMMTS AtW IMRODUCE M ~ SPAR 9TATiaW L SVC WGLfAR SHWllf R BASE lUNlR ROML APOLLO JISCIPLINAUV SPACECRAFI AO IWXRMBIAE TO SMML LkwcH VIHIrnS SPICE STNIOU mmw PWXSMUmt 19 OPF?WTiW ME1 MRBdkW SPMXBM AS b P m l & R SYSlEMS FIGURE 3A FIGURE 3B W e now have a tcaaspa~8Sisasy&emthat p;ravidec for a o m p l s ~ l yreumble vehicles, all the way from the earth surfme to the moon surfwe m d r-rn, One d the advantages of this is that you can project cost per pound for such transportatton asbeing something like $200 a pound for a pouad carried from the earth's surface out to the moon and back again. That compares with m e b & & s of thousands of dollars a pound at the present time. I have tried to summarize the major events a s they take place in the earth orbit part of this integrated spme program, in the time frame from 1970 to 1980. I think Figure 4 demonstrates what. we have been saying. You find we do not have very many new pieces of equipment introduced, but instead a build-up in the k i d s of things we a r e doing that is quite impressive. ltn fact, I believe this program meets all af the objectives that t-he scientists ad the people that have been working on space ~pplicationshave been able to define for this time period and d m provides the flexibility to do many things in addition. tha Again (as shown in Figure 5) in lunar orbit you have the same build-up of capability and in the planetary area another buildvp capability. Now, we have taken the program out through 1980. We also have looked atwhat the implications are of this programthrough 1990. It turns out that by using the same basic equipment of a nuclear shuttle and a @pacestation module it is possible to build in earth orbit o planetary expedition. One of the ideas we have looked at says we take a space station module, plus some planetary peculiar equipment, and attach to it three nuclear shuttles in paralIe1. The first Wo of these fire, and drive the third shuttle and the space station �FIGURE 48 module with .tBe pliw~truypeauliar equipment off to, for example, Mars, The two outer shuttles, once they have achieved the Wawfer velocity, leave the vehicle andreturn ta earthorbit for reuse, the remainder continues on out f~ Mars, and tbe third nuclear shuttle p l w s the spme station module in orbit about Mars. There are excur&an modules to the Mars s h e am3 return. They stay there for about taro months, then they return past Veauls, using the nuclear shuttle for the second t i m ~ ,and u ~ ae Venue flyby to reduce the return velocity to earth. Then they fire #e nuclear shu#le for the third time, and return the whole assembly, including the space station module and the ehuttle into earth orbit, where it can be refurbished and reused. That is the kind of p r o m flexibility that is available o w e you develop these reusable vehicles. Here in Figure 6 ie a detailed flight program. I w@nttdwell on that this morning, but you will notice that there is a considerable progrru~of usmannedor rtutomatedl~rebiclesin the early phases. They eventually become reused, utilizing ths: spme staticin as a base to operate from, and so the numbers dwrease. That decrease in nzuabers, in tarn, pmvIdeBI u6 wfth a better understanding of how we reach the 88vings. We are doing something lfke three o r f o u ~times as much work in space, by the-1977-1978 time period, but the costs of operations have & o W y decreased. I guess the one thiag: I ctfdn't do was to discuss two very important parts of this program whichwill, i n f s t , determine how successful thie program is in reducing met (Figure 7). One of these ie the third item where we the have tried to prwide fma w 1 d qualification and checkout criteria. Now, that is particularly true experhefit area, beowse once we have a @ace shuttle, itwwld seemthatone ought tobe ableto use essentially tbe s a n e kind af equipment for exploratory research that you use in tbe laboratories here on earth. If that is true, you can put fbose thing%in the space shuttle, carry them up to the space station, move theminto position FIGURE SB �and see if they work. If they dmqtwork, you can fix them, became you have the tfma and p p l e &ere to do it. That should redwe t8e very eons~iderablecost that we have ~stso(sit~te3 with making sure that all of this equipmat works pefpwtly a m it is launched. And much of the cost of prmbnt day equigment is in the qualification and Wa&flity area. We had h c p d to be able to eliminate that. THIS P m m IS 81216*0 f f S ~ R I a I t ,m mm e TMem ~ % w ~ *ww N ~ l U B ~ I ~ BSQ-a. ma I * C I R ~ IN~ ua W101 FCX L mDWlW YSSim 812lQ F[B( BPOIlM rOMR1U r OtSlDl fOS~l1-MtL$1*H Y P l l U f l W llPUEW CDSl (I,rU(. S W UTt6IhT1(Y. 4WM.IFICITIW, BiLglD S U M FffilLITlf!& WBIU, IMP€MHTtW6 w Mt5smM 1 WS YMICbEs MStW KR LOU6 WRRlDl MISSIOIS WIQ t 0 WMW R Z U E W M t C l N IN MU( V(nlUf s 5 1 aFCX MAXW a RWSAW r r w w a ~ * r m c fiRLDWHBOIMmRM BWVl m(l:7wW6wkflDl OKll W Y MlSSlOIS mWZDEF0R IlcLMa PUUffWilSIR M i O C W m B WllralA .. . us The s e ~ o n dWng is that we h v e tried to provide for autonomous flight misdonss because, again, a. very IISi WUIf1(IP 1616QSl @%W IF ICCSSMIIY CmP4WKS r a t u ~ p rel t i*sv RE& a SPNBCW ma ~ * I R ~ A T I O I large part of the cost d o w present systems operam URN COR MWIF1C~lICU011 REPAIR Fbl W nM &DWiWiTUB SPAM sv&CK.Mfr UD tnsamm3 tion is in the mind mpyrort ecorst that goes with it. *w* RMMU ' I R U S P O R T W TP W I T WAVY Au0 M*IIR141(1LL m l Q We have, as you b o w , some 20,000 people at Cape 1 PQOslBE F B AtlWIWWS FLbW MMI%SIM Kennedy who participate inlaunbhing a Saturn V. We mstm POS H ~ I W maKrn? L WIUTAINWC~ PEWSIR F a RIWT C W MISSIE* C W M U would like to end up with a groundcrawfor our spme m r r IU NOW m e w f m ~ m L RIW mlaStm s u m mTI shuttle that i a not h r e r #aa tbat for FL 747 aircraft. E%Vm15nffl -1PB PRkUWMA H we can achieve that, then &@ c o ~oft operfitioo will ISHRC W A L sUwORT enurn D IPReWMMYUIL BY 8 1 O T C ~ ~ m C W USf W TRLNSWAIION AND FRWW WPPORT plummet. That means tIso~h,h t we have ta do mcutrls something differeat about the desfgn af these vehicles. + They have to be capable of operating with very small crews and be checked out and be ready for launch with FIGURE 7 very small crews. That s a p , in turn, that we have to design the srtbs~rgtamto operate in that made, which is quite different tb way %@ym e designed at the present t h e . Therefore, one of the great challenges is going to b to G the way we a r e doing bu%ineesto be much more nearly the kind of checkout and design philwophy aseociatsd with airoraft, rather than that which we have developed for launch vehicles and spacecraft. b P(IWiDL (I . Another facet of this is the development of a better way of handling information that is generated in the space module itself. One becomes aware of the problem, when you think of the warehouses full of magnetic tapes that now dot the ldsaape around each of our Centers-magnetic tape that is storing, at the present time, housekeeping dab, d not a very high bit rate. And then look a t the saientific equipment and the desires of the scientists for new eqaipment in the next 5 to 10 years. You can imagine that there probably won't be space enough on the surface of the earth to house all the magnetic tapes that would be gener~tedin a few years of operation of some of this equipment. WeI1, we do need to pre-procegs data, reduce the volume of data, and increase the quantity of informaLtlon we get out of these things. That is gaing to be another challenge in the development of both the *ace station and the space shuttle (Figure 8A). We atre in this kind of m approach, estrtbiishing an integrated program that is capable of meeting the needs of the scientific comr$.unity and our engineering community a s well. Xn this instance, the equipment we have developed c o n s i ~ t of s just a few basic kinds that a r e used to do all of the things that we have been able to think of doing in the 1970 to 198Qtime period. Here (Figure 8B)in the case of the cislunar operations we continue �to use S a ~ m VWstfrne ~ ~ period, t sincethat size of vehicle is necessapy tulaunch many of the modules into orbit. Bat. $he. major trwportation is carried out by the space shuttle itself. The space station module has many ugw of courtw, W a s the balse for laboratories in space, d dm a s a way-station for Qavel to ' other orbits. AEJpat can see, we have space station modules in several places, each one af which is supported by the nuclear shuttle. The overdl planning ,s&edde that we have talked about is ehown on the left hand figure. You will note that one of the khings we tried to do in making; this plan was to have a continuing flight program both in the lunar area and in tfie earth o ~ b i t da~ea. Dobg so, tmms out to be not tao expensive, ;tnd at the same time it provides us with the contintling buil&p of knowledge that is so essential for an orderly program. Wow I would like fa tell yon of the plan which went into the Space Task Group repert, Basically, the Space Task Group rep@& emt with Blaree program alternatives Figctre 9). 'Rie integrated plan, that I described, is really the oae thatwouldrequire resources r s h m W a r the maximum pawe in the dutted curve on top (Figure 10). As y m can sass, it bums up to a fund- level that reaches about 10 billion dollars in 1976. That was the most ambietious p r a g ~ mpresented, and from that program the President1&Space Task Group selected certainalternatives. It tww out that the principal cbmge in each one of these alternatives is in the pace of the schedule in whioh the pl.af~3~am ia wid out. But there are differences in the conteats of the several prqgrams. For exmnp1e, by the time you get to option 2, ar program B, as is the case in the right hand figure, you find that m workshops to one workshop, and so on. There are actual reductions in content, as you have reducsd f r ~ mt well as in the schedule of the program a s carried out here. But basically, each one of the three options has the same ear& opbitd b&d-up of equipment. The third option essentiauy defers the decision on when one undertakes a plmetary mission out beyond the scope of this particular study. Essentially, the difference between option 1 rand option 2 is in the time at which you carry out your first mamed planetary expedition and the time at dub you bring yo= firet station module on orbit. The-difference between option 2 arid option 3 is that the sta& of a p b w e y prog;ram does not take place in that funding curve. But, of course, as is true of most prop - ~ , you have to recognize a t y m have flexibility, and these programs are designed to have flexibility so initiate a new program start at any point a s you go along. that y m I think that the position the Space Task Group took is one that is quite constructive for the future of the space program. I find that the alternativesdo pennitus to buildup those basic elements that are essential to aflexible long-term program. In particular, each of the programs provides for the development of the space shuttle, a space station, EUXil a space tug. A11 of them also have in it the development, but on different schedules, of the nuclaar shuttle. So thst ia the sssenc8 of the situation a s we stand today. I am encouraged, p e r e d l y , with the actionsthat have beentaken over the past several weeks and I believe that we do, in fact, have a sound basis for a continuing space program. I think you all ought to be encouraged. I think you all ought to recognize, though, that our ability to carry fopward with such a program as this depends upon the continuing succtess of the present flight program. There is nothing that will cause some of these dresuns to wither on the vine more rapidly than failures in flight. With that in mind, I would like to conclude with just a w d abaut the i m p o r t w e of t e r n work in carrying on in the future and to show a film that we had prepared in time for the Apollo 11 flight. It is a film that we prepared to commemorate the end of the Apollo Executives Group. We invited to the launch all of the top executives of your companies and the service groups who had participated in the program for so many years, allowing us to reach that point when we could take C SPACE R I M PROGRAM PPERSPfCTlVE LtmAR OWIT BAS€ LWR M A C E BASE I I FIGURE 88 �off for the moon for s. lunar lmdhg. We trkd to show in inis film some of the characteristics of the teamwork that made t f t Big& powibla, I Link %at t~am~orlr that was so essehtial in ApoIlo is going to cuntime to be essentid in the h@xe, ir we w e to suwe4 in this e@a~e aeffuttyr. And so I would like to leave you wi& the thougM that ft i s the taan *at is import&, a d it b our &stre md Lope that we can preeeme that same kind of teamwork in thefuture k t has been so fnstmental ia the succese, of the past. Thank you all very much. FIGURE 9A COMPARISOW OF NASA FUbfDIN6I REQUIREMENTS (BILLIONS OF DOLLARS1 FIGURE 10A FIGURE 10B �APOLLO 12 AND BEYOND DR. ROCCO PETRONE Apollo Program Director - 8 . - +->*+- 2% * moami&, genheken .-it.iS ,,, ,,, ;I- &&h iiOe to ~ci here today. In the few moments I have on the schebule I am going to stress Apollo 12 and beyond. I am also going to stress the fact that each bird eomes by itself. Before you w n W k 13, you have to talk 12. Before you can talk 14, you have to talk 13. Same years ago, when I was playing football for Earl Blaik, he had a favorite expreersian that r e d l y sank home in later years. He said, "If you want to win, you've got to pay the price." Now, Apollo has its price in order to win and mcceed. It is a question of dedicationto the job-that little bit extra, that little extra push. It is far beyond what we would call an 8-hour day for those of as who are going to lead the program, and those of you who have to lead others. It is a question of following tb-rsugh oa details. That is the price we have to pay in this program, where the smallest detail ignored i s going to hurt us. It is a thorough probing of problems. It is a question of not accepting a first answer that comes in. You know, you are so harried and pressed, therfirst m w csmes in with a' ready answer and, b y , it's the answer to a maiden's prayer. You have to be careful not to take thd answer. Probe it! Make sure it is the answer to THE problem, not an answer to get rid of the problem, which could really be some other problem. It is a question of constant review to make sure there are no cracks; and again, that means hours of effort, that means a thorough review on the part of people who can see if there are cracks. Ancl then there is the question of teamwork, the integrated teamwork between the plant and the field. Group dl these together and that's the price we have to pay. Now with Apollo 11, we proved we were willing to pay the price to meet our goal. Many people, some naturally but wrongfully. feel we have paid the price for success and now we can rest on our oars. I want to tell you &at the demands on management for the fu~ ehave had in the ture are r e d l y greater than t h ~ we past. When I looked ctt the future missions this last month, in my new position in Washington, I literally had my eyes opened on the future. We have been busy operating. We have beem busy pmhing , fighting the details-31 of which haa to be done. But the missions in the future of Apollo are mom demanding. We are talking smaller ltuulctr windows. We are talking same launch opportunities t b t we onlyhave one day to meet. W do not have a nice eight-day spread with maybe three recyalee. One day! And on some sites only one day a year I So you can see the demands we are going to have on quality performanee of operational follw-through. We are going to be carrying heavier payloads. We want to do a larger number of EVA'S. The point to be made : "The demand is on management to make sure no one ertaunMes. " To hit that site which is going to be important to us, demands are going to be greater than ever. Let us look at the Apolla series from 12 to 15, we call these the H series. H-1 coming up i s the Apollo 12 landing site, I am sure most of you know just where it i s . It has certain objectives, and one of the new things we a r e going to do is to run two EVA'S. We are going to spend some 32 hours on the s~rrface,and, hopefully, we a r e going to bring back some new information, It is a very intriguing mission. One of the secondary objectives, not the primary, is that we land near the Surveyor. We a f a going to be able to see the results of what two and a half years of exposure in the l u w environment can do to equipment. Now, this i s very important for the future, as we talk of building shelters on the moon, a s we talk of better understanding conditions on the moon. Here now we see that with our second flight we a r e broadening our grasp. We are reaching for more data, more knowledge. The Surveyor landed these about two and a half years before �A p d o 12 is s ~ k d d e di;o I d . T l z i ~!%vreyar dld n number of things. One thing it a d was to dig a trewh Now we have the m q a e rrppa~iunityon &is flight to take pictures of that Surveyor, auad analyze what ttRB and a half years of expoasare on the lumr surfaae a s . It's quite uniqae! We will p1mtS~b1~ not have that opportunity again. met a;t ttte WOaCErCT W 8 C d e r t r . a ~ sprulmd e by NASA a d the National Academy of k2eace. The purpose of tW meebiag was fo b ~ & gbgetber p e d e h thirr fmaPywbo oodd lwkm~w taol we have. Apollo had d e v a S e a tool &qua in hiatmy. This ~ f ~ g h a momel3ded wwe adopta flight p ~ @ pofmbetween 10 & 15 ladings toflll the mael* tu b~inghome the pieces to W k t w eJ o to us tha picture here fn the yews &sad d us. We J s o , as we look at &lew rnissibni~,are try- to ~ o r the. s thing we call ~ r b i t ds c i m e . This is qUit!~&Wld. We are f X 0 b aboard eomand module. We we znditt~es~ s do. a Wte a bit of picture what . The Apollo 12 h u g b 18 m i e s of miasisionr,will go SQ sites we can use and exphit wlth essentidlythe present Apollo hatchware, slfghtly extended. Starting with Apollo 16, we go inSs @&ad& lmar explor~tion Here, we are m a H n g r n W a a o m on the lwar module to be able to stay on Ure lunar @wf=e 54 hours. Also we are plaaaing .onthree EVA'S of four haurr on the surface. . What has been irtk'fguhgtr, me is to watch the scientists who have studred every site ; t h y seem to h o w eaoh site now like p u 1 d d h o w the back of our hand. By &dybg the maps made from #e lunar orbiter phobs and S L &a& brwigbt back from the prior Apollo mimi.rseims, the sci&ists have been able to plan traverses where it is w r y important whether you go North or South, h term of tile data you are going to get. Nolw to get there in the fitsst place we will require very preci&ewvlgatian. We will need a very accurate sya$em to gst hl ~JCBewh site. Once we get to these sibs, the lcwmIt*e we o m k i n g back is unlimited. There i s n .pcrwise re98m fm s i n g to each site. We are going to 'be laoking for 61 new crater. In s a n e of the m;ate~rswe have the ~dmwtagetha* when the meteortt@s hit, WJT ejected matarid from 10 miles below the stlsfm. Sa we are pftqg to k able to pick up q ~ c i m e mtfint redly r e p s e n t the i n t e ~ o of r the mocm. We are p i n g €obe able & determine tbe process wMab far& them rw3Kse. The techniques we b e to mdyse Usesse things w e very intriguing. YOU em 1it-e~ dl3 bll when the rock was formed. You caa tell h ~ w1- the r w k hsca kRgn MI the gurfaee. These Wktp came ;tdgetb l i b a gi-t jigsaw puzzle. And &at is part of the message. 1the FY 1970 budget p m w a , the auhrimtian bill appropri5~gioabiU g~ fsr has d y passed the House, the Sea@%yet is to e w i d e r it. We are talking follow-on , buys, WE& ie very important, of course, for our future. We are talking some five Saturn V's. Again we are looking for missions beyond Apollo 20. We a b o are making plans fop follow-en spacecraft. One of t b 8bps we are taking, agrtia in l&ie with the comments Dr. kIsteller made, f s cost redu&ion, which is earrentid for the future of waee exploration. Refurh i s h e n t of command mcddes is one of the methads we thW offerer us 8-e epportunity So, ertarting with CommandUodde 106nowat Domey ,there will be-let me call it-prototype reffirbfshnxent, hoping Ulat with Spwecraft 118 we nil1 be able to take command modules and refmbish them. This will save a considerable cost in m h foilow-on misaion. Again, these are ~ thoughts we have in order to get some & the s t q and mare for the dollar in the exploitation of space. The ApoUo game is just starting, The inform~tion we are goingto bring back, the int4gration of that information, is geisg: ta eve us rs tPemeadonra inrsigbt to understanding the moon and t b wlar ayst.arn, AB Dr. Mueller s d d earlier, it will give us the first leg up an planetmy expbratian. These te!cturiqn~sfor work* on #e moon me gahg to give ul the h w l edge, the plan, far l&er explora@onof Mars. One of the very impo-t taala wa we looking at is a Rover. Iarn sme m m y d ~ri3ltEakowabout it. But the ability b go out maw 16 kilometers Zrt a precise direct&on;,stqqiag at certain "sciwesee ~dtztti~fis~~ (as we o d l them) al~ngt b way, pickiag up apecimen~, ~mkiag ~ S W M ~recorbinp; B , in pictures, and bringing back this information from acth trip, or traverse I s important. And each tmmrse hae a particular jab to fill o certain piece of a puzzle. We are talking ~f nine landings-nine n o r e that have been s ~ m e dTBg . @ c k m e $rmpr Eww t looked at the lmwr sr;trfac;e md have put together the puzzle that t h e y d d like to we filled. Tlrese mielaee greups )L$s passed Imk#t&e&~$d €he t%mai%~. . The point I want to W e wlth these remarks is that the future of Apollo le just beginning. The exploration and exploitationphases arejust aow here. -re are many ways to prepare, like the football team that practices through the long, hat summer, wid sweat h i t s eyes, and with hard knodrs. But now comes the payoff. We have played the first game. We have acMeved a goal. But we have no #me to relax. The goal of Apollo was nat just to b d oa the moan a d return. Those were the key words in President ICenn&yts address to the C o n p e ~ e .But other word8 were that we are ping to Ism b sail on these sew, We are goingto learn how b operate. And &at's the payoff, andthat's the phase we have yet ahead of us. Can we operate ? Can we be successful ? Can we deliver hardware in the quality manner on time? Can the people prepare for launch? Will it do its job ? The question of can we do the job, of course, meam we have got to keep our eyes on the future. But let us review our remnt experiences to see where we need more practice. Where do we need more intepated teamwork? Where do we need more scrimmaging, to make sure we don't come up short when we face what I like to call the moment of truth ? When this gear is committed for launch and we reach T -0 r ��to a new'enviromnetxt t Ham we lost mntrol of our process apac? We b w e ta make e8rtab that we first answer. it's also true in our never accept testa. B is so easy in betfag that &metimes you will see a glitch on the record. "Well, yeah, we understand it, or "B eouldn't be important. '' If that glitch was never thew bdore , you must trclderstana it. You must pursue it. Now tfrere are times you crmnot get t o w bottom of it. But Wey havegot to be few and f a r between. Aad Cben it has to Be the right ement level that meeptr it. h n l t let these things be bought off at the middle management. E they are not explained properly, where you can go €xi& and audit later, they have to come to the higher level for acceptance. I believe those two items, the qtlaI test program and mdfwetion analysis, have redly contributed in a tremeRd&ue degree W the swcess we have seen of the ApoUo hardware. - We have always facing us the puestroln of quality. There are many people who believe, and, they believe wroagly , t b t q d i t y is %omMngthat depends upaa the inspector b insure. Not&% muld be further from the truth. Quality i s a three-lagged stool. Itfs that engineer who did the design or laid out the te&, it's t h ~ engineer t running the operation of the shop, and then t h quality ~ inspgcbr. And those three bunctions must hold each other up. You rare not going to have a good teat becaase you have rufl it through a procedure if the, test engineer lets you h in setting up the procedure. The- three elemente m e vital. Yet I have seen many times when people thaught, as long se we cover the item of quUQ, we have got it made. That's wrong. M; W tQ be cavered with good engineering, good shop operations, huad then good quality. I have seen in my experiendes at the Cape a number of fafluree to do the pki correctly . One d the snes that hounded us wae the matter of crossed pressure lines. Ft is so easy to cross a pressure line. In designingthis equipmeat many of the wmectors all have the same diameter. Human ene;b.n&&~rfng for dfffermt values oftea m e w weight, d of course weight is at a premium with the h2lagWare we are working with. So very often you'll find we have the same quick disconnect, maybe 3 or 4 in one bracket, they are all quarter-inch quick itiacoanects These quick disconnects have the same serial number. But they d l have different de&gnation numbers. In genesd, thie ha4 not happened once-it has not happened twice. You will find two lines crossed connected. You pressurize in one tank, y w believe, and you are reading your gage out, k t ~rourpressure gws into another tank. We have come very close to blowing t d e at the launch site. . Now B$Y, "%%at ia tfre probbtn ?" There are always two tMltll:eq, I mfn#mmasf two. And them me tkingr b t shodel mver happm. We can admstand hafiran emor. As 1u &era are hum- be1ngs in W s sy&em, we m e going to hawe eome degree of human epi"~, We &nlt bank OR^ two btugm error&in enccewion. And %%atirwarfgbly hqqens w h n that &&I is sent to us, aad whether is acmes eozutechr , or kt valve tk&t Ws t& be open or a vdve A sad valve B emea eat sad a m m opens up the wrong one, you will usally ffnd at,quality has let the shop d m . Now h8X dd I m m that. There is always a problem. You kaaw, ff f am good I &aft l i b mybody looking over my shoulder .tellingme h t to do. Scl the qualitg ~ w a n b t o b e a i e e b ~ s b u d d y ot&ayews. f And ohy,if 30e s e k ap that jab, lt must be good, because Jbe set It up, The ~urtIiQman will somtimes sign off in the blind, ft. W h ~ w n e d more often %an you would care to Wnk. When that quality man is letting that h p p m , he is being Jm's wurst enemy. The ~ h u p nttsdethe protecttionof the quality men to oheck every step. And yet in our sktpobm, the errors we see cannot b v e h~ppctrtedif two eyes bad looked at the same job. One spes made a mirkrke and the second eye bought it witbout looking. We by&looked at a l i f i Mt of thet future, looked at a lime bit of our experiemeer aad said, f ' W b have ~ we@ to g a m ? Wbithavewsgwt todotomake sure we keep pressare on tha people ? The prewure tu produoe the quality, to p ~ d u c the e right enghensring ,t b qwistfon of beping everyone reaahlng for the god ?I' Andas I have said, "We have not acfrieved our gad yet. " We have shown we can do the job. I think that is dear. We have shown we can do it. But this does not mean success i e ours automatically. The fact that you won last Saturday's game doesn't mean you are goto win next %twdayls game. I don't care how g a d you are. You win the next game on what you put i& that game. Apallo 18, sitting on its pad at the Cape, doesn't know Apollo 11ever made the journey to the moon arid returned to earth. Apollo 12 sit8 there &one. And Apollo 13is soongoing to @itthere. alone. And whether those missions succetd or not, depends on what has been done at the Denver plant, what haer been done at the home pl& , the test d e s , and, finally, what has been done at the Cap. We Bmrva got to approach each epacecraft md each kmeh vetrfele with t b idea that this is the big om. And what was done last month, or 8 months ago, does not guarantee my success for the future. fi we keep o w eyes focused on the ball, and the j& to be do*, and if we apply the lessons we have learned, there Ys no ~uestionin the future that success will be ours. Thank you. �APOLLO APPLICATIONS PROGRAM PLANNING WILLIAM C. SCUMEIDER Director Apollo Applicut i0hs Program - - I was $rBcu1arlY intrigued by Roccois analogy with the football team, and it led me to think if A p U o has just had their opening game of what promises to be a long and exciting season, U P is in the business right now of just forming the league. We have the teama beginning to form, and we are beginning to get our ha,rrfwaee going, but we are wrfting s m e very new ;md different rules. Jwt to give you an illustration, I was lsokiDg at a plant newspaper Bob Gilruthts people put out here last we& and I copied this ad out of it. Itsatid, "Availablefcw rent, 2 bedroom cottage, kitchen, bath, living room, solarium, air conditioned, approved water supply, bemtifd vim, attached garage. All utilities supplied. Available March 1972 for suitable tenants. Reasonable rent. Apply the Apollo Applications Offloe. " Well, I am going to tell you about that two bedroom oottage, because we are really entering i n U P into an entirely new era. We are a bridge. Figure 1 &owe what our official objeotiwas are as laid upon us by NASA management, tlnd really what t t r a P s ~ yis~"You, AAP, a m aprecussor spa- station, axxiyou a r e also aprecursor spwe shuttle. " Now, our objectives a r e to prove that, agsfn, man can stay in space flight longer and longer, and whstBsmore he cando some very usefulwork. So we have some wry key tasks ih the medicalarea to extend the qualification of man, if you will, on out to where we end up with a6 days and hopefully even longer than that. At the same time, we are doing some w r y key thing8 in the area of habitability. What do you need to keep a man d i v e in orbit for 2 months at a time ? Yesterday, for example, Dr. Mwller tald me, "Gee, why don't we have rugs on the floor?If Well, wet are not quite going to ham rugs on the floor, but maybe we will exld up with wallpaper on the walls I These are very key elementer, ;urd they tiwe leading directly into the space station and space shuttle activity. Inthe area of work we have about 70 different q e r i meats, and they range f r m fairly simple mindedw e a camera and M e mme pictures-to some extremely complicated experiments that are costing in the neighborhood ol 70 to 80 billion dollars. They cover a wide m e of bchnolegiiim. And, of course, a whole batch of other things are going to keep the tenants that we will have up there busy for their period of time. For those of you who may not be familiar with GAP, I prepared Figure 2 to summarize what the missions APOLLO APPLlCATlONS BASIC OBJECTIVES EFFECTIVE AND ECQNOMICAL APPaOACH TO THI. DEVELOPMENT OF A t A S I S FOR WTEmlM FUTUBE SPACE PROGRAMS FIGURE 1 �are. We recently made a change from what we had termed the wet workshop into the dry workshop, and we a r e now launching the dry stage of a SaturnS-IVB stage on top of an active two stages of the Saturn V. That will be pre-outfitted a s a workshop and will be put into about a 235-mile-hQh orbit by the two atage Saturn V. It will then utay there far abmt one day, unmanned, at which time the solar rays will deploy and the systems w i l l Wmlitically get ready to receive the first t h e e man crew, which will be launched on top of a SaturnIB. (You remember theSaturnIB1s ? They're at Michoud, and they wiIl stay there until 1972. Now there is a reliability and quality problem for you as those vehicles sit there for that period af time, a r e taken out of Storage, and axe than used b put man into orbit?) The men will then go up upd join the workshop. They'll etay there for about 28 days. I have a thing about 28 days. I have set for myself, as a program g o d , to change that to one month. bnd then we go to laumh QB 31-day months. But anyway, afterabout 28daye -28 io a magic number, it's twice 14, and we had 14 day mkestans in Gemini -the crew will return to earth after having put f i t h e workshop into a standby mode, and it will sit there and wait about two months labr when the smond thme man crew will go up sad rejoin the w u ~ h o p . They again will reactivate the systems, a d they tbis time will stay up for two months, at whteh time they will coma back down and then h u t a month later the tMrd cmw will go up, aad they will repeat the cycle, dahg new experimenta and repeating some d the old experiments. They will currently stay up there for tr period of 56 days. I don't know whether f should annowee It here, because it aertaldy isa't official o r ham%besin worked yet, but we are tryfnp; to extend thst mission to an even longer duratim. I personally would like to m e it go up to 120 days, altEtou@ that's just in the study phase. Right now 56 days is our god. program fnitiatee a whole new era. The cluster has to work f o r 8 months. It has to survive being activated and deactivated repeatedly, and all of this at minimumcostl Now, let me go into afew of theother systems. I will show you some of the problems that we have. Figure 3 is theworkshap. The first launch is Saturn V, t s i ~stages fueled. Third stage is the S-IVB, in this case emptied andgsed, outfitted on the ground a s the workshop. There will still be minor things to be worked ug-and it is set up as this cottage that I spoke of before. There are two active floors right now, that io, the floor of o ~ l eside is the floor of the other side. In other words, people stand toe to toe when they a r e standing on the twofloors, and equippedwith experiment areas 6LIICI various com~onents This i s the major experiment that we have on top, which is the Apollo telescope. It is a solar observatory, and its task is to observe the Sun on a long-term basis bringing back observations in aphotograihic sense, as well as in the astronaut's mind, a s tn what has happened at the Sun. Very interesting experiments for astronomists So now what are we talking h u t S What is the reliability goal that you people keep shooting for ? This . . FIGURE 2 hoking at the pieces of equipment one at a time kind of outlines for you the types of p r ~ b l e m syou are going to be facedwith, or we arebeing faced with. Figure4 i s the air lock module, and its psrtioular problem is that most of the a c t i ~ esystems in this, OP a good number of the active systems in this, are Gemini equipment. That is what I said, Gemiai 14-day qualified systems, and we ape now having to take those systems and assure ourselves that they a r e now going tobe available andworking for this eight month period, of which five will be manned. So it represents a very significant problem for the R&&Apeople. Not onlvdo we have to worry about whether that hick in the h e , that Rocco talked about, is going to give us a short on lift-off, it now also has to work up there for that -5 5:-., . .- .long period of time-a particular R&QA program. 1 . �the Apollo comd and service module. But there a m some very important hardware differences, which are brought a b u t by the even more important differtmms in the way that we are using this equipment. Ttlie equipment will be used to take the men into orbit. .. the .-.workrrho~. at They will then transfer over into whish tfmc tke cornand service module i s emd down. That i s r , it is then allowed to remain there in a very quid shte, without all of the power on, and only those sy232ems operating thrtt we have to keep heated up, and things like that. And it must be available for any emergency, rn the crew c m return and come back. Obvicwely, then, it must be capable of being turned oa and returned to earth safely. So it looks the same, but it is doing a vastly different job, in a different manner. And that brings us into some veryfine subtilities in the qualprogram and the verification program that feed into our design and have led us to some changes in the command module. G- Particularly In the command module (Figure 8) we are adding a b m k p RCS tank so that we can have alternate means,of deorbit Hopefully this will save a tot of momy in the qua1 program, because now we won't have to (EILalifp &e basic. service propulsions system, whiah is a t we will rely on mos;tly tobring UB bsck froon orbit, quite as 9s a~ it wwld if we didn't have a backup system. Now theworlnshop areas m e in here, t]Lre experiments area, &he air lock, the multiple docking ctuf~tar,the ATM with its mlar rays depbyed, of ooarm, t h e are the mlar rays in the wozkshop and the eommand anEd semies module. In orbit the major power supply is solar rays. . The next bulk on the front is the multiple docking adaptor (Figure 5). This represents a NASA problem, and your NASA R&QA people have a good task in that Marshall is currently building the multiple docking adaptor, and this means that we are interfacing with the contractors, giving us interface problems, as well as our own R&QA problems. And I might also add, there was a lot of experiments and pieces of equipment that are put into that, that are fairly major in themselves, I will show you one a s r e go on (Figure 6). Up on the front is the Apollo telescope mount. This too i s being assembled inhouse a t Marshall, with some considerable help from many contractors. The experiments themselves a r e provided by the principal investigators. The biggest contractor being Ball Brothers building at least two of the experiments, with some of the others being built in-house, and others being built by other contractors. Very peculiar R&QAproblems are involved here because these a r e scientific instruments. They are being run by scientists who have different inclinations tfianperhaps our system's engineers, and a r e requiring considerable effort on our part to make sure that they a r e indeed good equipment, that they are going to work for those eight months. This is very complsx equipment as well. T b workshop itself (Figure 9), a~ I said, is a twobedroom house. And it is. I'm not particul&rly pleased with the layout that I am showing you here. T h i ~is the layout we had for the wet workshop, and I am sure that now that we don't have to have hydrogen compatibility, we can make it a lotmorelivable. Yon can see the view of the experiments area here, with some of the experiments, a view into one of the bedroom@,the food area, the waste management area, and the other bedroom is over here. And I might add, regarding the Apollo telescope mount, we feel that it has to work, because if that doesn't work, I think that the space station will lose all of its support from the scientific community. Because in that piece of equipment, we are proving to the scientists that really, when we undertake a manned space flight, we undertake a scientific task for the scientific community and we are going to deliver. And it's of very major importance to us that that does work. Now the AAP shuttle is the Apollo command and service module (Figure 7). And for the uninitiated who look a t it from the outside, it looks pretty much like FIGURE 5 �This i s what are in awr ~ e ' w i s i kall~ the epme waste mmagemmt arm ( F w e 50). I have taken steps torenrunethis '*%He&, tB Idm+tbmvhether I'll be suwea&l in that. You ltaow we kind Of get hung up--evwyow bas their o m IiWe kg-ups--aind in space business wekind of have hag-upe mmae. B& it is the "head. It ira gius some major developmental pmb-a bwawse it obvtotzblym&twork, and it is tied diremay P a b oar bemuse part of our problem in tb rnmlkoal area ia to b r h g back the w&e material f r a a t& nzen, the feoes and the urine, so b y can be pmperly maly%edon the p;rcrund, s~ the medics indead s q in US, '*Yeah, yscan go on axid put up a 1mg-duration space station .I1 Some of the experiments that we are doing a r e quite Wresting. I won't dwell on them,but a s I have said them are mmeT0 sf &ern. But this i~ isnethat E find pwtk2ulw1y interes(%igura, X I ) . We are going ta be flaround inside of the spacwraft in an attempt to lelearn a li€tle bit abaI extmvehiaular aotivitres. Hapefully, out of thfs we will figure out those mwtr~ibtsthat there a r e on m m , in these srnd other EVA experiments, s a ~ hthat EVAfs beaofne a fairly routine thing. You b o w , in the future in the q a e e station you won't pucker nearly a s bad as you do now. One of the expwiments is complimeed m d large. Figure 12 is f i e controi display f ~ the r Apollo telemape mount, asd it wiil ke mounted in the multiple FIGURE 6 . FIGURE 8 . , FIGURE 9 �have EVA a s a p a d of otlr program, and it ehould prom tts interesting as previoue EVA'e, When a r e they going to dothi@? (Figure 14.) George s d d we have n whedule that officially we say we a r e committing caurwlves to Congress for July 1972. I . order to aehieve that July of 1972, we have set our internal goal of March of 72, I've been asked "1s that j u d a fi@tious g d 7 Is i t just a pad ?" Believe me, we will go in March of 72, if the hardware is ready. And we have established a s a program policy that we a r e ncrt going to allow sandbragging on equipment deliveries. If Part "ATtfalPsbehind its delivery scb9dule to the Cape, we are aot going to relieve all other equipment of their delivery dates. We a r e going to, asbestwe can, keepthings in storage and wait for ail of the things to come up. We do, indeed, want to FIGURE 10 FIGURE 11 FIGURE 12 FIGURE 13 docking adaptor. It is kind 6f like the complexity af a DC-8 c w o l e , aMt lyou can see all the witchee and all the indicators that me necessary to run these five ATM experiments, oontrol the vehicle, control the ATM, watch what you are doing. The mtranaut loolss at what the Sun is doing en Wse displays here, and then records the activity on film. And we too have our o m moments of EVA which a r e going to give us our momenb in WQA. f h r EVA is neaessrrrrgr in ApoUcrApplicatiens i.n order to r e i e v e the f i b from tlae ATM (Figure 13). 60 we will still �hit that March of 72 date. We b e three revisits planned, as I er;fid, a d we have one bactrup emxma31d and service module. In the- cards, bppefully, as Dr. MueIler &m&dyou in the h%egratd p h i , is s second worltsshop. N m that s e m d war4Esbp is basically the b & d qEsqclipmeat, ref&lshe-d chnd with some modificatbns on it ferwhbh our eurmtplaw~ed; launch date is fn J m w y 1614. That too would b v e same refurbished oamrrren%l a d mrviee modules a s this one again and we wfll re-en@eer tt sad &mild it, and put it ba& in, and fly thatup for three 120-day misstons. Now, I did mentian k passing, refurkishment. I guess we in AAP are pa* t b way, d~~ we did aad gome h&%h e n a LiWe bit of this bmk in Ge-t aone Ifn Apono. Part d o w c o m & and service module philosophy ts to reuae ptw, a d some considerable part8 POI$.& eo?mad & service modules rfpllrt there ape things k t barwe gane to the moan and back. This L providing quite a melattoo to our public &'fairs p e o ~ v#ho t ~ orre w d w h g where they are going to get all the Apallo ~ p w ~ e ~ s fto t pput r in the museums. We told them, f ~ 8 5want pof than, and &ef! are just nno2 g a i q to b v s &am fos .display. k t seriously, we are planning m m a y pmirb FIGURE 14 that have flown beforekey parts, not TVcameras, htztehes, and &hga like that. We are even l&g at, although o decision basn4t bean made, not by a Lortg shot, "Can yon reuse heat shielder?" I'm sure yeu C B L ~reoqpize what kiml of implication that has in the R&$A area. W d , f%ve said thie befose, and I'll say it again real quickly, AAP is to spwe stat;Tm,what Gemini was to Apollo. We olre the bridge, We w e paving the way. We don't ap%ct that we will solve all the problems, but we have undertaken to provide answers in a number of areas, and we that objective of bing t r m s i t ~ r y ,of transferring our rnamed spwe flight thi&.iagfrom event being a launch, a lunar mission aad refwn ta living @workihg inapace (Figare 15). So we are wthe rule8 ri@k now, a.nd we need a 106 of help in Xke B&QA wea, axid in every area, in what the -pr*r su3m u e that we ehould apply tn make om ~pacearrmf2more like &craft, things that are derigml for multiple gnuyosea, multiple uses and, of course, long duration. - - Well, gentlemen, that c m l u d e s my brief discussion of what AAP I@. TIE& you very much. FIGURE 15 �THE MANAGEMENT CHALLENGE LEE JAMES Director Progrum Management Marshdl Space Flight Center Gaud morning, ladies and gentlemen. It wems to be the order d the day to start off with a football story. I did ncrt bring one. I have been trying to think of some analogy; one that might apply is that Rwco Petrom and f had the s t m e coach, Earl B1&. We sttU have the m e caach, George Mueller; we are stillon a winning t e r n anddthmghwe made one goal, the season is nat yet over. What I plan to do in a few minutes this morning is to put into p e r s p t i v e where we are in the Apollo Program, particalarly as it q p l i e s to manavment of the Safxrn Launch Vehicle Program. It seems to me that if spa6e can hsve a crossover point that we are now there. No matter how you describe it, the initial Saturn-Apollo Program is over, The Apollo job-to put man on the moon and safely return him to earthhas beendone euwessfdly. On just the other side of the cm.ossaoverpoint are tBdayfs programs. These programs include further lunar exploration and Bill S e w e r ' s Apollo Applications Program-tvfo vastly different progmms. Further downstream from this crosmver point a r e some things that are quite glamO]POUS, Thase are the future programs. They include m a g challenging things like @ace shuttles, large space ~tations, tugs, nuclear stages, Mars exploration, etc. Today, P am not overly concerned With the succese of the ApoUo Program because it is over. I am not concerned abbut h s e glamorous programs down the line-the mes &at Dr. Mueller demrfbed. Somehow the Government and industry have the ability to apply themselves most d i l i g d y to glamorous new programs, and we will probably do a good job on each of them. I m esomewhat cbnc~rned,though, with today's progpms. Theae programs, consisting of further lunar exploratSon and the Apollo Applications Program, a r e a r d chdlsnge to us. However, I am not sure that we are' equipped for that challenge. Let us sepzcrate and briefly analyze these challenges. First, the Apollo Program had a number of things going for it, It was, a clearly established national objective. I do not Wpk at the time the President made that objective for us thatwe realized how great a thing he had done. The e e w of a goal gave the ApaUo Program a big push. Next, the Apollo Program was supported by the general public. That may not mean much to us wCfl the general public does not support a program, and then one certainly takes note of it. Third, the Apollo Program had a certain amount of international support. We may not realize what that means until oar Government becomes concerned about lack of international support. Internally, the Apollo Program was supported in a number of different ways. There was a vast industrial base solidly behind it and that really provided momentum. It has a vary strang Government base behi& it, and I do not mean NASA alone; it included the Bureau of the Budget, the Congress, qnd the Department d Defense. There were a lot of members on that team. Next, there was a very strong scientific interest. The scientific community was highly intrigued by the Apollo Program and gave it full support. I, personay, would like to Submit that the Apollo Program had go@ leadership everywhere it needed it-in the Government, in industry, and in Congress. Lastly, to get down to the nitty-gritty, it had what it needed most: manpower, facilities, and sufficient dollars to get the job done. The combination makes for a successful program, and we have had a successful program. We had our problems in Apollo. I think some of you are aware of that. We had technical problems. Exotic new materials were developed and we had to learn �The -lo Propam was auob that we c a l d haw stn ~ e w 3 s P a2am3B P ~ WaB d gx& by wit& &. But the pulbli~ Bf3t m(t&& wfa-~w f@ &@ PEO@'alll leam tobandietfa8 sheer #beof p r o p o a . There ;are some seveB prlnzes bt the Ektufn. It mems a x astronomical f a t to bring, tEme after tlnna, aa4 launch after W m B , ewen major wzt%tPes to bar at exactly the m e mont$!at. SO WC l B wePe those of you and &om of ua who to hurry up a& wait. This caused praXl1ew. - We W acme s i f p i f i c ~ haPrfware losses during our tests and daring o w prflfgbt d v i t y . I mt totalk more about &at tn a mimute. Wa hod a Viet Ham conflict that is red and is with and that e& be overlooked. M had its Me&. As the prv$ram re&%& the peak, we immedfgtely experimed eerfaua manpower rBdLlcttoBs. Ha m&m" h* you cut it, e v a in the midst of a go.infF pm&rm, e m thug% it L pla.med m a though iit ,is aokhing new, it is dways tenuws to a m e df the w a p w e r cum, We had man$-&o=C1y maybe mms than any of u s realized-human emrs in the propam. . We had whatone might term a major program c a a trophe with the l@ss d 204. The aocirl.ent w w f a more s@ifbant than my oher p??&blern o r sucaess. It was Biglacant lsecmse ft W@S rtE that mom@ that we learned w b t atenuous rmP%&ge m dl Pivet on. We le& what a short di~),lame it i s from being known as a n&ianal macess ta b&g known M P mtional failme. We learned how cpliokty om can lose public support andfdlwing, n a t u l d l ~ Conglrembal , support. While we lost 3 I& whan this failrrzw occurred, aver b a m d r IN tm. We. W him, for at this p i n t we facad a rdlty Mtat said, f v Ycannot ~ get there from b t e without arbsolately btal wzecerp9 from here on in." Portmmtdy, we had that. . at t b htgb emt mme%sary.tcs $kt tb progrm ~Oarted And n s W r is t b Baremi .of Bx?get, Ccmgres8, or anybody dm. We Iram to faai up to %hat. After the kpollo wwwa, we to do mm&ing &o& iawerfag t b mat. We met Pkitb your hfhetrlal leaders, same of you here today, aa8 deeided that a 5Opement reduction p d was tfi the ball park for the follow-on B*rans, We have redimad the oost 50 gement. We all agreed to Wa, a d it is firm. The Bumau of the Budget barsc now a&ybd these figttres a d they are w h t we bars pjsfa to live wi&. The reductim is no I q a r rr porrsibilf%,p-.lt i s n fact1 Uf oourBe, I think everybod$ has Been Bask ta see me w s Oo~ a y , "You realiee W k 60 p Y m t did aot s d y apply to US. But it does tqpIy asrose & e M . l W a requires us to transfar a m fmm an RdD a o n q t which allows c-es and t&sVts, statlc tests WG!&P?P niee-tohave, be3 e x p n s i ~ etkihg8 ~ tQ a proctuction concept where . a ~ gare &&&nf ta have .static testing;, frequent change@,amd. t b 6.aie&ia. DldleELon ol rstatic testizig pr~ludehlprs-~pWaahwko&. When you do &athave Statio tarsting, you Q not haye a p08t-static @heckoat.We will have pod-m811ufactufng checkout, then go directly to launch. This means that some of the things-mistakes, maicfents, human errors-that have been happening cannot be allmad la happen any more. Now let us briefly consider the GAP Program that Bill Scheider d e w r h d to you. As I see it, and in the perspective that I am trying 'to make, the AAP Program b a r many of the same features of the Apollo Program, and several drastically different features. In the firer place, I thl[lrtc it has dl the complexity Apollo had. WB are trying to do b the AAP aprogram every bit as complex as landing man on* moon and returning him serfsty to earth. On the other hand, we are not building up sr big hardware inventory. In We have hadother a.chr!i@a tbi-qs, like natural&astrophies, wt& BBuPrlcaag G&e. Tfse~ething@ Awllo, our plane said, "If you do not make it on AS-501, how about AS-505, 48-513, even AS-515 1'' are part Qf tha prqgmx, Wmy gf 6he: k a c i h t a I havedeecrihi are whkm w d d e m t i n the course In U P , there will be two shots. It is a program of a large p r o g r w They happened, aod f o ~ ~ ~ l that y , build@up and &noat immdiatelg cuts off. So it the propam W e m g h g ~ h for g it b werocme W s e is different in that r e s p a t , Another big difference adversities and czapitdize upon moat failures. is that AAP is not a -11-funded program. We are gofng to do this aa, what I call, a shoe-string. This Now, I would llke to tdk hM3 aboat where we a r e is a cbstllenge. So what h v e we accumulated taday ? today. Aa hos been mentimed b earlier 8peeches, We have accumulated a program with funding; less we have 18 Satume in the last of produotian, than its challenge, We have built some hardware test, or checkout, & yet:to be beamched They are that we have got to use over sr period of time to make not schsdaltxl for fl@t right sway. Some of .thebe that work. And 1 say to you, that i@a real challenge. are built and stared, others d l soan be ccmpbted and it is goin;$ to be a 1- perfrv8 of Hrne befare we Now, I ask myself some questiom. Can we continue use all of t h m . mil61 i~9a pQbl&n. These stagae to improve and maintain the quality of this hardware are going to k aomgtleted br fmms that a m be& under them W o of conditions"l~;an we make a dismantled. TBGsa g t ~ e %re s p i a g to tw launched by transition from an B&D type of kunch vehicle to a teams tbat are samewhat rlismtmtltad. Believe me, sta.adard production type larxlloh vehicle and make it this is r problem l And in the midst of taking what work at this point intheprogram i" Can we aoaomplish wre might call old vehiolers finding out how to use the task within our budget ? (ff we do not coma within g~o$r;ilfls, we are entering: them for our on-goour budget, and that means 50 percent leas than it into a follow-w pmgr%mfar the pmduction of d i has been, it has to come out of something. Thsre tional Saturn V Lautach VehI6les. d l be no new funds for it. I think I have just de- . �scribal that M a p s pm@!am, like Wll zllbicPerer's, certainly is not go- to previae for it.) I w d d say that it is nice to ride along on a program like Apollo. Can we keep the Wenticxi of those workers who have a slightly different perspective of tkis whole Wng than maybe mmagement does &day ? Caa we motivate the people with the critical skills to transition from the dimbishing program thqt we have today to the f ollow-on program tbt has ta build up ? C m r e convert to a completely different program philosophy ? Maybe you have not thuught about it, but ean we really succeed in a m - c r a e h program atmo~phere:! The funding anct the over& situatkon dictate a --crash program atmosphere. We have a lot going for us. We have a tremendous team built up. We have a successful program. And goodness b o w s , we have a challenge. I have selected one launch' vehicle, which I do not Now, I w&t Q address the situetion one other way. What I h a w triedti19 do is talk about Ihe &$olio P q g r m and the trm%S%hn to the f o I h - o n prqpzaa. IRt us lo& at the &dl9 P r ~ r 8 m with the eyer of tk9 astronaut# f o r just L ~)etx&, QllCf Q e tranritian just allttle bit .l&ir. I t&ed thrm@ m m e paperr t b t I had and ea- ap W@.h cfuotras from a uoslple of the astronauts. For 'Ohe lmk ingo the pwt-the look int6ApolloI wmld like ta; r e d Urese. The first me 19 SranzMfke!W l L s dhr tfis,A p i l o 11 flwk $Xe saki. "Any flight like this is tm&einely long, PragiZe, daisy c h i n of evsnts . The mallwwtion of euzy one of the Zhsurw& d piecgdl of b-9 on the way could ruin the remainder of the mission. -spite the fact that I have great confidence in each i n d i . . a l item of equipment, f was a little peasimistie about our chances to carry the whole thing off. I figured that any chain as long and tenuous a$ this had to have a weak link. Believe me, I spent a lot of time before the flight worrying &out that link. Could I be it ? Could my training have neglwted some vital bit of information l Or had I been properly errposed but simply forgetful ? By launch day, I was convinced that I had taken d l the steps within reason toprepare myself, and I hoped that the t h o u s d ~d others re~ponsiblefor the equipment prepamtion had doae the sms. Obvi~us1y,$bey had, because the pdormance of the! whole was n~fhingshshsrt of pelrfeotiicsn. l' This fs bow o m feels abuut a ~suoowsfulflight. Neil A m f d : ~ rk@t , here ia tam s t the Rice Hotel on A-t 12 said, "It would seem thaa in mm%amdiUons we Would be expectsd to be verylonelyhr away from home' and alone. The facts are, I m e r felt less lonely in my Me. In every piece Bf equipment, in every corner of the @wec~a.€t,iti every cabhat, and in every piwe of scientific apipmcaat we carried to the surface, I felt the hands and the spirit of those who were riding dong;on Apollo 11. Those pieces of equipment were superb. They brought to my mind the proof of the return (and I like that word) the return of 'American craftsmanship. ' And as some of us, some of you, turn from this program to even more challenging adventures of tomorrow. you will take with you the knowledge that craftsmanship, initself, is a worthwhile objective. So to all of you and those who you represent, I say thanks for riding along. " choose to Identtfy,to illustratethe task mface in our continuing program. On this one vehicle, we traced some of the following errors to human beiflge. Fortunately, all of them were caught. a Two of seven helium filland dump valves, which had passed acceptance test and which had just been checked, leaked. A broken position switohpin and a short circuit valve in the LOX vent and release valve previously had passed a visual check. a Tie-down straps used duringfurnace brazing of the thrust chamber were found wedged in the upstream side of an engine. The straps hadnot been r e m o d during regular cleaning. a An electrical harness showed heavy rust deporsfts Water sLnd a broken pin in one connector were caused by improper insulating by someone. Corrosion and a bent pin were f d in the connector af the flight control transducer and an O-ring; was laft out of a mating cable connector; all due to human e r r o r during rework. Corrosion notea in the flight instruction harness c o m c t o r was cms& by ttmis8ing.U-ringwhich allowed moisture to enter. & offset i weld p r d m o c m e d during cireumferentf;il welding d the I,& tank forward bulkhead to cylinder six, primsirfly due to improper zmmufactklring and qyality control of the diame b r measurements. a During post-manufacturing check, a screwdriver was dropped and penetrated the wall of an engine thrust chamher. a LOX tank baffles were destroyed during too fast propellant loading. a An LH2 tank insulation problem indicated le&s and debonds caused by poor installation processes. a Leakage a t the main oxidizer valve idler shaft vent point check vdve wars cwrsed by ecmttmination from a change of lubricant. The vendor did not follow specs, An LH, a d drain valve ruptured causing much damage to the skirt ducting. . All of these were on one vehicle, Fortunately, they were caught. I pointed out earlier that we now have checks we were not going to have in the future, that is, pre-stdio, post-static, and static tests. 1 doubt ifyou would like to be riding dong with Neil, Euz-, and Mike if some of these things had not been caught and corrected. There are only two ways to stopthese errors with the programs we have, One is not to let them happen, and the other is to catch them. It is probably going to take some of both. Now I would like to carrythat just a little further and show you some things that were not caught in time, We traced a number of things that were found on �W o u s vehicle@at one tima or wrrther that had a h m m link involved in t h a n ars oppesed to something that may have been wron$bydes@. in Figure 1,the X's that a r e sbow in tae 8Sffezmk stqes represent such items. The e W d arew plppsw& -to-aallos618s that were caused b9 same k3nd af fault. I think ft ts interesting to mte &at we have onlyflwn six kturn V vehicles, but already we are finding a signififfant numbered Uke things b A & S l l ~ d ~ - 5 1 2 We . must catch these things. The follow-on vgihicles, M-516 through AS-521, a r e now under purchase. In the follow-on, we are going to have a lot fewer plwes to catch all these 'thing@. Turning now to same piecsa d hardware (Figure 2), &is usad to be a tank dome. Whm this was shipped, it hsrd two dust caps. One located inaide a piece of tubing; another was ~ u t s i d ethe tubing, Upon arrival for tests, the dust cap was Wen off the outside, and dr presaum indicafor put on. However, the &st cap was left onthe inside tsnd the pressure indicator w w showing zero when actually the pressure was a b ~ u 25 t p ~ i a . The bulkhead reversed, pulled away from the joints, and rmulted in the damage you 5ee. This stage (Figure 3) was lost clue to a vendor employee swing fit to change the weld filler to a pure titanium. Thb L the result of that one change FIGURE 1 FIGURE 3 FIGURE 4 �by a human., And we have h u r n m in our eysktm. Figure 4 r e p r e s e ~ t uan interesting ease. A static test was a b u t tt, start when the crew found a leak a d shut dewn. After shutting down, they disconnected some preseurs indictataxi to the tank. Tfng next shift came an, decided to presmrise and look for the leak. Since the pressure indieatore did not show a problem, they overpressurized and this is the result. hydrostatlc ted neared completion, a problem QCcu&. We needed &adump the water in a hurry, but we did not have a procedure to do it. Hence, a complete loss of the stage. ]In Figure 3 p e r b p s we did not carry oplr prwedures f a r enough. Thiar war r strtlctmd Bat vehicle, BLlld since we q e o t m e t failure in stntctural tester, we preelsRlriad it with water to avoid s blast. A s the Figwe 6 shows a very recent incideaThit happened on AS-511. K i where the man is pointing, there ie a polyurethane shippiag dim that is included with this unit for protection. It was left- in daring test preparation&. The result was a major leakage during the static test and a major fire which possibly was not extingulhed quickly enough. Hence, major damage to a very recent stage. FIGURE 7 FIGURE 8 �Figure 7 represenM a Wemnt- k b d of r thing. & C have sr r s M c €eat October 17, we were at sur Nlisslssippi Te& F&.Wy, We p00Q~ogad thst test although the eqa@mat ww m d y to go, alP#ere was one contpactar whe diq not feel rnmtdly ready to go. Now that 161 w y to understand s h e WI$) was a residential difstrict uvhem w y d tttoetD ~ ~ employees live, in Pass C'til-isrright after Euzrtcane Camille. I do not want to getfueraod tnWs. Mt I m t f y b g to do is to paint a picture fer ym. -6 iS, it cbies not take m a y of #eae fdlurgs (F&~r%r 8) to %k@a national p r o m h t is goiw -11, d cost it out of business. It does not taka matay of tbt~sisef a W e s to reverse a national tread. It sZoes wt W e much make a failure out of o s u c @ e e a space progrm. Therefore, we w ~ adCess t ta such r possibility. In ret~ospec%, when M e e d 1T1 came to me, X WS t%@W %%, that would a 8 t m q ,d that C Q B new ~ mcmey d e w It coming b d . The p d h k ~ kept coming up, SQ wwe put. $am Iwsluldlikc say., againfn f money well spent. ~ -- pt The Ikfttsmed F wA w w m m Pmgzaa qm~tezs,i f ~ vatiibnd mated&+ W € i p r i d h , Zt contrstetos plants, has IPIQ~~'YI;~M the workem d &e parbliu to be aware of our space program. I &inis it has done a great job. Mmg of as represt?rat the mmqgement aspect of the pmgrarn and I do aot Wnk h t wehave too muah of a problem foreseeing somewhat into the frtture, George Mue;Uep described st beautiful futme ~O-T that is probably going to carry on the re& Cdl Of USF of this oaturjr. I Wnk all of as will m a a g e somehow under this. But I submit to you this morning that am burnag beings-some in your organization, some in miae-that ws have to worry about. W e are aaw ~ontpM%g&age@withwelders who know they are gpiag; to be laid off. We m e completing stageis with sheet metal manufacturers who have their termination mtiees. We are putting in enginesbuilt in plants that have virtuaIly ishut down their productiosl line. I submit to you that this is a problem that cannot be solved by the lHarmd Fligbt Awwmess Pmg~am,at least not m we iohm it Way. An ostroaautfs visit to those p l a t s wiUL bt4lp. But f do m t think an astrcm&utts visit ts the plant can sn$mlve the kind of problem that we have today. I do net'bve mewerr to t b i ~ problem. I do feel that from this m e e I should go back a d worry about out what to &, You should gobwk a d it, and worry &out it atgd fiflam oat what to do, too. I am not stwe that we have %%e mems Of getting through the immcsdittb years, if we do not innovate beyand where we are right now. �ASTRONAUT PARTICIPATION IN THE MANNED FLIGHT AWARENESS PROGRAM MAJOR STUART A. ROOSA Astronaut Those of you that are sorry that Tom Stafford isn't here, well, I sympathize with you. I feel the same way, and I also realize that probably the best speech I could give is a short one. But seriously, the MFA program in our office is a personal thing. I t i s probably the only direct link that we have to the people, the literally thousands of people, that are building the vehicles. Mow, we spend quite a bit of time at some of the contractor facilities, climbing in and out of spacecraft, checking them out. You can sign a Snoopy doll, or give a Snoopy pin or something like this but in our normal duties we don't get to the majority of the facilities involved. I realize there a r e a lot of you here that have requested personal appearances, and have been turned down so many times that youthinkwe a r e not interested. That is really not true, we do feel thatit's veryimportant, Roeco Petrone made the statement, and Iwill steal it from him, "One vehicle does not know what the other has done. The only continuum we have is the people. And so from our office, through the MFA program, we do have a link with these people. I know the personal appearance requirements are given every consideration within the Astronaut office. Lack of time is why more requests a r e not honored. I know there a r e some people in this room who a r e quite familiar with our schedules, and not to belabor the point, I would just like to say that we stay quite busy, but we aren't unique in that respect either. I would be willing to bet that we could take 50 of you and have you do your job, and you couldn't meet all requests either. We do feel that the people-to-people approach is a good one. When you go to a plant, the enthusiasm and the warmth that you feel from the people is real rewarding. And it is good for us to visit with these people. I asmme it is also good for them to see the users of their product. Take the person that is bolting the heat shield on the command module, he can get pretty motivated, thinking of the consequences. But all the little things a r e so very important also. For example, a fountain penthat you a r e goingto be using on a one-man contingency rendezvous. The data comes up on the computer quickly and you have got to copy it before it's gone, we can't afford afailure with that fountain pen either. And from my standpoint, a s far a s getting ready to fly on 14, and from the office a s a whole, we a r e real concerned about the little things. We a r e real concerned right now during this transition period. We feel this direct link to the people is important. I wish we had more time to participate in those personal appearances. I guess if you spent all your time doing that, you wouldn't be training to fly, and then nobody would want to talk with you anyway. So it is sort of a vicious circle. We a r e already well past lunch time. I would just like to say, from the crew office, "Thank you for the support that all of you have given the MFA program in your facility. I t I would also like to continue on with the theme that "We've got to keep up, and get out the good work, right now. " You know that is really important to me between now and next July. And also to assure you that we a r e shying busy, and we don't turn down those personal appearance requests needlessly. We appreciate your support, and we ask that you continue. Thank you very much. ��WALTER F. BURKE President McDonnell Douglas Astronautics Company Gentlemen, I would like to say that I am very honored to be given an opportunity to talk at this seminar. I am r e d l y just filling in for Charlie Able. Be was called away on a very urgent matter t&y ,and I have besaaslmd to step in and try to pass on the message. h l o ~ k b gat the Manned Flight Awareness that we're sio auciws to be sure works, I'd like to go back a lifflr bit and t ~ lwhy l I think the Government, and ~ ~ W k ,is leoming to ythe right @proup of peepla, namely tlw aerospace industry, and the aircraft industry as the managers of some of these extremely large tasks. As you recall, b k in the very eaxly beginnings of any aermaIrtical endeavor, there was a very quick r8coWtion of the fact that intense research of a very deep Cchnologieal area was needed in order to make the rate d progress that was desired. This brought about, in the early days, the establishment of the NACA, where it was found that the depth of investigating the number of tests required and the caliber of t h e d y . r a t e was extremely important, andin fact, was the Iamdstion stone of America's aircraft industry today, and I think we can look b k there and see the very beginnings of this Manned Flight Awareness Program, telling you too fkccuratelymy age, I oaa sssure you that I have taken part in many of these early activities f a r enough back to be very familiar with such things aa terminal velocity dives and spin program. You no longer even hear about them, but at that time they were the first and only ways we had to get irrto the structure of the airpIane, and into the response of it those features that would give tbe astronaut, o r as he was then called, the aviator, a chstnce to perform his duty and survive. Although we do a much more sophisticated job today, it ~ r t a i n l ystemmed from the deep interest and the groupof peoplethatweregenerated at that time giving us their total lives in dedication to the aerospace industry, and it so happens that right now many of us who a r e just getting into it a r e luckily still involved. I say luckily and thankfully because to me I wouldn't have picked a different job if I could start all over q a i n . I'm m e fellow that was absolutely happy with what he chose a s a profession from the first day, and I wouldn't get out of it except by force o r age, Now when you get close to the activity of the space end of the business, namely our spacecraft themselves, I would fortunately connect it with the company that was involved in both Mercury and Gemini, and when we started Mercury you can be sure that looking out for the astronaut was not only a very important thing, but it was a brand new idea of how to assure the astronaut's safety in a vehicle that we at that time could not plan to bring back and try over again, so it had to be a success on every shot. There was to be no averaging out, no statistical high score. It was decided it had to be a success 100 percent of the time. Now to get that, we spent many long weeks and months with everybody that we could collar, trying tofindout the problems of environment, trying to whittle down the chances of thermodynamic o r electronic failures, doubling up on any system that could possibly be a trouble maker, sending all kinds of animals, frankly both pigs and chimps through our test program, trying to find out what the effects of shock on the piglets which we dropped in specially designed cultures in the hangar in St. Louis were. In every case, trying to find out how to better make the vehicle give us a 100 percent chance that man would come back from the mission. I r e d 1 receiving a letter from Dr. Wernher von Braun after he had walked through our shop in which he felt that we certainly could stand a much better �approach to She O ~ I rma* I Far &f31161. we kw k e n forever WO@m$N.@Ws mstlodar phase of it, and we%@dim@a 4 4 in deveE.~~imt@: so called +'wbtte r~0.m"w 4rclezlaroomt*approach to the total mauned sd o r t that we've been in. We also had cowern about our Zest procedures. Did we k n o w h o w t o b & B P 3 ~ d t & d a n g w ?W p i t e t b years of flying and the thousands of fl&& wit& test pilots, we still hati nst rwehecj th& peak of mental acuity WLat Clh you that yoa atre &OM the p p e r thing. As a matter ob feet, in o w of our @@sly space chamber rune, we veygpg nearly lost one of our own wtronauts, Burt Nor&, primarily for a lack of dry running Ziests in maH= s u e tkt everybody not o d y uaderstcaod what to ch, WWthe test was going well, but particularly, what to do quickly if the te& started to deviate from the plan. This brought W t a whole new approach b order of magnitude as to our p r e p rationfor tests whenwe had astronauts involved. The same thing happened when uvcs built our larger space we had fire chambers. We had escape &iUties, possibilities and equipment in there for extinguishing any fires. Despite the f&ctwe iPf.lt we wtonldnvtsee a fire, we did have pmvisians for b t b eztinguishhg it and removal of the astronauts. We trained dlligen*, not only f o r the succesishtl mission, but for dl the possible deviations one might consider at all likely. This waa our initiation, p u mig;ht say, to be aware of the value of the man, a~dlmake our men aware of the value of the mission. nor the f h m M s.tsuettm to handle one of these mslJ6r bc@be@ pmqgm~w. Eamver, that one program sucha as a m have carnot b~ i&eE r e d l y stlpport a total indwtry oorgaaimtion. There were twiny thi.agg on Gemini and Memury, in conneMon with our 6-NB that 1 I e \ r . e c d not b e been available to improve the caliberof eqnigment toprovide the capabilitbs, bad these mk been many other business activities oa ia that qgmfzaffon, The manner in whlahwe k v e stmmaq* emmat of amgineering for a rdaiwely rr d mmwat sd h m m delivered, does mean that you have to call on hoflities ,particularly in the manuibturing rarea, t;brrt youwould otherwise not be able to &Bard, And J$% tbe simultaneous exfsteme of &r large pmgra8o.a within s company which provldm the capZtal to give 3 ~ this r capability. We find tbat there a r e sametima some concerns of interfasaacw bfmeen wr program for you in one particular w e , and for t hAir Farce in a competing case, and for aommercial bpslit~msin another. It's our dete~?znUW&mand o w ceefrieticm tW$it's the combin&an of these in a company && pr~videathe real muee1~atrd L e hark, wsllioh &I t b olrsh, to go ahead aac? M e one of t k a e big progrsms. But every problem, o r every instance such as t h i ~obviously brings about some problems that a r e peculiar t~ ibelf. I would like to address myself to just a few of a w e . We then, at the very early dagrzs of Wk&mry prior to w e n launrihtttg the first m w d Hercury witb Al S h e p b d , were acmzMme'd very cloeely over an extended period af time by gl coznmitrt;ee called the Welsner C o m m i ~ .TMs W e f ~ n e rCommittee was s e t up by the Government to make an indwendent evaLuat1an d just what we *re &iw7hrnv we were doing i t , did we kwrw what we were doing, a d could we d e l y agree to launch #e man? This bolt us over every aspect of the d e s w of +be vehEcle, every aspect of the test, tt wry ~ l personal ~ e scrutiny, man by man for your rna~vation, for your in;teml thinking. You felt &oduteIy bare in front of them before €hey got through, and as we went through this we became convineaxid aoae thing-thstweladneither the time, nor the mollea, to have a convfnoing statistical record thdwe w d d haBe no failures. The anly answer to that, then, hrasl t@ be that every &hotstands on its own, and every ghat must wmk 100 per-cat by itself, and the o d y guan%nte&far that is the CP&manship of t b men, the mmagernenkof the p~~ the sWU of thedesigners, md the team work between the cotltracbr and 6he customer. Far one, I am a y we have nBver worked with any group &st rivaled the NASA persoriuel in giving us &is team work. It's unmatcherble wi& mything I've been connmbd with, and Z believe I am speak wiPh equal authority for the people with whom I've heen in co&&. How are we going to motivate the permmel? As I look around tbe- room hem, I notice very, vary many faces that I've ssenbsfor@at the m e kind of meeting, and I remgnizta that the purpose of this meeting is really dud. Itfs fimt to remotivate we t b t a r e sitting hem with the sole purpose of going back home and really motivating b e that a r e not present at the meeting. As the space program. eonfinues, and as was well said before, the probability Is that most of us here will stay in it, that we a r e the ones that have been in it befwe aad are likely to control who stays in it, so we will, liking our own personal jobs, very well try to stay in it ourmhebs. But &e hundreds and thatsands of people whose craftsmaniahip we counted on may not be as SerZlrnate as that. Some of the competition will come just in the very n a b r e of aur engineering pemonnel. W i t creative engineering pemomel, the space program could net have been as succes~fulaa it is. A creative person is very seldom a very patient person. He is anxious to progreaa personally, as well a s being a part of a live team. He definitely has to be kept motivated when a tempo slows d m a little, ancl itre in this ama'that we are going t o find, I believe, the most criticd problems. How to keep the areative engineering talent charged up if the program t e m p slows down appreciably. We have ways in a large oompany of moving people from one large operation to an-r, from one activity to another. At the same time, if we want to be able to call on them instantly, we muat find a way to keep them enough involved in the space activity that they really never lose tbir touch witb it. We cannot afford to let them go for three or four years into the commercial business, o r to the military business and suddenly just draft them and pull them back and ~~~. From naw oa as we keep @ping we have to look at a totally different climate, The size of the program is getting so large, and Eras h n so large, that it undoubtedly Is going to stay in one o r more of the major aerospace hndr,, A him@ campany by no means can have the aversity d s2rfIl, the facilities available, mag �)FAfjg %rtl&, T b ~h~"t e s d o r f t y g r M m . Thew dqgy pmblernr. Ve feel that we are ws oar a r ~ n p o a t m . &me a p f 3 r ~ r n ham! slat we s d up #3awaald & a i W proprtms *erethe men a r e e p M back Wougb the r w typed actieky @my had engageDd informerly on perkodb cycling ero &at they again do lose this +t M, By the & a m token, we have to be sure W ImUititw which %be~ie pwp1a need a r e not 2sU-d eb, m L o f u s e , to that poi& Wt boornesl a pr&lgm. Ba a pmbbm wiU edst fos which we must find at B & ~ ~ R I . H&mely, haw t o keep car Pgciiftg up h3 t,dorb, a d h f b XQZU%iq we wieh, k b pe0ge cotlstmtly trained for %time when we may suddenly wed them a@ we xmve fro@6neg k s e d the program to &wmtkw, fa theiee are- we b w e are going ts be d i m s s b g with oar labar unims, j& hmw rimy we da thL witkt sr nsiflimm imgaat on our bargdniag oa@biIities. wb* area, end I speak from ab&t Za W twelve y&w% Bb &oZIDry m n ~ upemtion r in our co-ny, I asm tall y a that a&ag ever motivated the job a mwh as yoursglf vihm goa walk out there a d miBc with tc6e people. We can put out all the poskw, you can hatre all the btermittmt visit@, YOU can have all the press releaeas within the company paper you wmt, but my own *&ion is that the meat, which r e p ~ & sthwe of as sitting right here, m we go through the shop, will have to g& o5P the:the: ~ & ~ a t ros&a ic and go out whslre the hardw w Is, and W k with the people, and ga wt there s o freqwfl.&3pWt W y @tto eort of e@bg you, and it% not a &mat big surprise o r soA of oz p r a d e when JQU W r e g r e ~ t l yg~ the shop. I have found t b t the cr&@?asnpsrtimkrly, is just cp&olukly in lave with t&iq yau Bis job. H e r l tellyou, he'll stop with yau m d speak t o you about his job, haw mueh he enjoys M a g it, aracl w b t new he founrl out to do well if you give him one halS a c ~ e And . %be only -my youtli ever get tbt L by the top mamagemeat circukt.& tha&ghthe shop on a complete mrtn-*man l~wi0, BO that the sthop people feel com@letelyf m e to tsUct.0 you at all times. wt Aa an e m m p g of wfia may happa if you don't conahme Ws, &rimg 8 four year period from '64 through '68 at M G - ~ I%4g1bts, we lawched 525 SnT'.la a d four Delta rnisstles wfthmt a failure. Itla bard to belime after thett tW the design wasn't good, It's hard Q believe that the s t s l t i ~ t i cwortnnamhig ~l wasn't good, but shxte May of '68we've had several hilurss. $&oh tftm w e t w femfced into t b s e failures we hawe found t b j haw h e n brsatgll about by a multiple ia-line pe11~aslWlum. % m n e did something wrong, a d the fal'tsaor thattaras supposed to find it, clidn't find it, a d &is pa%lou&srlyi~ tlw %ing khat we have to mteb. Ycru have to get rid d $BYI feeling that anythingnast just t5u-tomatidly eyaranteeta the next shot. Sbtis.tl&g it's lurt good enough. You have to have each el%& &andiw @tilts own. We bvepostera. How lmgdoes ct man l w k &ta pstm bfLforehe walks by it dtgid it laa fmger &BC& him P How many visila a r e there w b s e the man is w b l a through the plmt rapidly b a u m it's d o m to lunch, or it's about time f a r him to catah atn airplane, a0 all the man in slop sew is two efm whisking thw&tha shop, pz"&&I.y if you we= out there, you'd hear him say ta the q X t w e , Yl wonder what that group's doing?" Now you've w a l W through, you've thought you've motivated them, and you probably didnFt. You put more questions in their minds than you put answers. You have to ~ p thedtime in tbe shop, in the lab, on the drafting board-everywhere the people a r e individually working. All I can say is that having done tbiws like thast, this is the moat rewarding part of the whole j ~ b . You get to tow the people. Surprisingly enough occasionally they'll do exactly a s you say, mther than what they had wanted to do and make you feel lib you helped them, and theae a r e the ones that h i l d this company and in-plant morale. We look over our total engineering design areas. ~ltVht were the thing8 h t we could do better?" But we then stopped to ask, "What. a r e the things about the design we have right now that while they work, do have poseibilities of not working?" And without having to define what it is, i s going to make it work, assume certain failures, and then what is your recovery capability. So we ham done this time after time, and m sc o n t ~ u obasis ~ s now have a group which r e v i e w the design work done, withthe specific charge that they - deliberately insert mental failtlre into the design without regard to why they fail, but just assume they fail, and then determine w b t is the way you can overcome anythl.ng cata&rophic happening after that. Sometimes it's mdwdmcy, sometimes it is just a different wproach to design rather than that. Where the lack of statistics hurts, is .hat even if we get by a flight, we very seldom really know how close we were to the edge with many things. Almost no flight ie nomisYal from the point of view of the setup of physical conditions. You either &nTt have exactly the t e m p a r b r e you have designed it for, or you don't be axsdly the wiad shear, o r you don't h a m waetly tbe glitch. Everything; is just a little different on every individual flight, and therefore, you cannot be sure that many place^ on the vehicle weren't just about ready to hsve a problem. Of course, the more flights you get, the more you feel you can average t b w out, but we feel that the manned phase must have many flighb in it in order to wipe out these aseas where the facts of life a r e somewhat different from the fmte that are put down on the engineering design, and it's with this particularthing that wefeel we have to show the people in our country that we a r e really bearing downon how to do this job economically, s o that we'll get their support for an on-going , more �rapid, and very a & w t k & s p g r r w m . Witlrott t h i ~ without , the hdp ' f ~ e m -the & b r pwple, a d the r e d attention of t b p@ an the @~Unel,we just aren't going to be &h b enjoy the 1wr.y of P few flights per ye-. Wetre g&ng ta have t;g get a lat of repetition in o r k r C have a truly vduable propcm. lMJr time is ja& about w, but I \zaonld like ts make C%W other comment here. Wehve a$sigwd otne program manager for A p h , I3d Battar, who Zs 8 i W q in t$e auaeace here this &moon, and he b e n on the actual role of 8~~tunwng in d e w every s i d e piwe of hardware that entsrs into'sur 8-WB again, with a review af the M8t;ory every p i e bas had, the rwords of its problems in and oElt of wcepbmee, itr rwd out of mamfwture, eo t h a we can see whether o r nut with each prolonged s k m g e period, we have to do ~omethiqgm o thanwe ~ bad thaaght about doingwhen designed tbse p& to again g u m & the ab$~auteintegrity of thenz in future servics, So we a w eonrmitted to applying our top personnel to this m m t a c y of w&hing, this dedication of being in the p%qram. We fael &at we have many problems ahead of us in a z motivation ~ activity to lookat. Primarily, net what we need tQ do it, but better ways of getting i$done. we first I would say in clusingthat their reward is going to be very great. In the BbbIe Pa Xst Corinthiirns, there's a very excellent W e comment about what the reward is. It sayer "neither eyes have seen, nor ear hath heard, the great w o n k s W the h r d h a s to show to those believe," a& we believe in the space program at M~cDcrmell-J30uglw. Thank you. �President North American Rockwell h o d afternoon, Mee and gentJemran. Thla is a p a r t i d a r l y vital time far a meeting such a s this. We have a l l been complimenting o w e l v e ~during t b past few m t h a , And we all know that we did a wonderful job on getting thaw fellows to the moon a d , pwAic3darly, getting them bask. I am not sure a t we fully wckrstmtnd why we were &la to do it, b m u s e we tend to be e n g b e r ~ rud , look at things from a techniea.1 point of view, an8 make a lot of other ~ s w m p t i m . % pwple wbo ~ w l l yput the men on ths moonandgotthenn back, happen to be the peagle of the U n M Stabs who put up the money, And we d y were tools in tbir b u d . The most imporhat thing I think we must remember for the future i s Wt W Is our role. And I don%t m h w y w put a clolkr value oa it, but it b there. So where do we go from here? It is obvviowi h t one of the nice things abut the lunar program b that it can be eaaily understood. You can get it in ysur mind. You can easily M i n e it, and it ia what yon lalght call a single paint god. However, me d the things we w e a little bit a t fault for, Is t k t we really didn't do are much homework as we h l d havebefore we got tothe mom. Ewrybody s8y8, l1I'tn@IOg tO get thQge men to the moon. Then I am ping to get the hell out of this program. " So this b r oaused a little blur, h a u s e he had to pick up some speed in determining what we a r e going to do next. But here w i n , it i s fortunate because just withinthe I don% 'think anykdp ever had a better break than Presideat Nixam, when he took off on his trip around the mrTrt immediately after Apollo 11. Bscause no mattier where hf? went, the main thim in peoples' minds around the world was, this is not President Ntxon of the United f3tat.a. This is President Nixon d tihat country that put the fellows oa the mom1 last week, the Space Task Group submitted a report to the Pretsldmt. I bappened to be talking to Tom Paiae laat Fri&y, cmd I a i d , "Tom, is there going to be any specific announcement by the President on We a r e often asked what a r e the great fallouts of the space program? On this subject, I think we strain too hard to name some specific piece of hardware which i s in being. In my opinion, the bardware hllauk in the space program a r e really not going to be known until many glegrs from now. I knew tbey are there. Bat I would be very mush surprised that anything I wrote down taday, turned out to be the impartant things in the future, And what does the Bible say? You know a s well a s I do. It says that there is a continuing space program. There are several options available, as we all know. And, incidentally, I hope that we can get away from this distinction between manned and unmanned spaceflight, because I don't think it is really a meaningful division at all. But, we know we a r e going to have a very healthy program on earth resources. We know we a r e going to have a space station. And we know we're going to have a space shuttle. You fellow8 have been struggling with those things much more than myself. I know you have differences of opinion. I am not going to t r y and design the thing here this Probably, no single event in ~e history of the world has raised the prestige of any country such ars the ApoUo Program has. Well, this is a real fallout. tbis thing?" He said, "There doesn't have to be. There it irc-them's the Bible." �try get a e b c e to pat arr oar &, so 1 m&W m k e a couple of comme&-a. Let's take the a w e && WJ -m I@ example, , (What I say can apply to @e sthem jt& a# well.) We have our goal. Let's a h sum we dl understand w h 5 that g d is. As 1 K ~ ~ B T B - ~ 5% OU~Pgoal is b make it possible to re-fly W reunse @%s'pace vehloles, &iia transport6Ltbn v&cles, in a way tibat will -give us good txonomfa r&m a& our aB0rt.s and our investment. In tbia r e s p e d theP, a@ it fans out, we dl have our ideas, m y b e some we pretty impWta~t on what it ought to be. Bo we h d to start designing by committee. And, I - k v e heard much raving and rattling about what t h CPDB wmge should be, and what the p a y l d should be ? I'll say this, "1 don't know what they should be. 'I I do say tbat if we try to make everybody happy, 4 eet down requirements that just arenY do-able, we a r e going to end up with another bust. So, let's make sure we know what the requirements are. What the important ones are aad then go on t h t basis. Here again we as etlgontaers, don't fully appreciate the points of view of some very i~ry,oTtant people, like the taxpayers and Catrgress. A d , I think we must face the fact that a very import-aat item in the final gpecifiaatfon, which we are going to end up with, has to be btased u p the remaroes available, I am counting a s r a o u r c e s the people, which, a s you dl h o w , we have plenty 'of. We donLt have much time. We never will And, of ootrpse, we newer h v e e n o w money, So I tl& t&e prqgmrn should be p b s e d on *Cis gaing to the realistic appraisal d the -ding be made avaiktble. And if we s h t , if we put OW sightstoo high, ~w~ jtx~tne'taerget there, a r people wffl get tired of waiting for as lh get there. The other thing to do, W M Bis ~ probably worse, is to set our requirements aaB our go& &Q l h , in which case, technology will oomds mrine; by us and we wlll have another program go. down the drain, as we have had so many other8 in the p w t . Getting b c k to tbis reqtzkrernenh business-I dm% know whether or not space i s going to turn out to be like some of o m experletwe in aircraft, a@ Walter was talking about. I have b m h very few airplanes that ever ended up by beingused for the requirements that were drawn gp to justk€y Wt airplase. Here we a r e a t a situation today with a 3352 being used for low-level bombing. I b o w that any airplane that started out with a low-level bombing requirement never got off tbe ground. And, a s a matter of fact, we don't have ane today. But that is t$e way these things turn out. I think this is the way we have to view these thing& ve 1re tall&= a b u t . They are good jobs, The teobqologyr is right. They are going to turn out to be a W a y program. Walter touclzed an this baaiwss which is the whole the&e of this meettug, motivation. Personally, I would like to say h t I hear the word motivation md apathy kind of used crossway, I would like to make it r e d clear that in my opinion, I know of no szpathy and I know of no people who have an apathetic attitude toward €I& pzwgmm e m t ~ ~ t st .u m .$BeCOB= krtrary. -%Fktay m me hykag Dff at t b zaze we +me.all h$isgoff, %hem IB *%?&&a mwfm&-&* Ikwk T b m az% mvma3 wry -fuuadamM thM@ paWm1&y, in t & basinem. ~ Number me, we have to have a c~nUnllousc h d l e q e . We Bave %p+ to put up somet&ing &tat is redly hard for p@opXar-Q meet. This aaukf be a combimtiom d tdmt& t&n$sl, s&eMed W w , and do&r things. Awl, iacldsnm y , I tSlinlr all t m maag times, we try ab s e p a Q these three eblngs UWla Independent ntmpartmarats. We will b y e a meet- me on S;C-. A M %eaest &$ we will have a me&&@on aost And ths O W day, we w1SL havmnotber m&zqgon pric f ng Aadym wwld think there nuere three entirely different t b g s we are talking about. . . In additiorx, a chaUemgt3 o r a goal ff you will, really 8.rrsnt+do a$,ytBsng:, o r m an mything, unless we have specific ways of mea urina; that, a d have a feedback. Then you b v e tolet the fellow know exactly h.ow he was doing; o r the group on how it was doing. In that r e e e c t , too many times I see us trying to buokshot a whole area. We do it to ourselves. You, our customer, will do it to us. You will send a million people into the plant, and just Mud a;f look the whole thing over. We come up with Wngs like reports on subjects which were never a problem to begin with. I think the m y we ought to h d l e these things is that you fellows ought to be sufficiently on top of us and when we do have a p a k spot, come in and help us, whether we need it or not. But don't try and say, 'WeU, we've going to take a look at Company X today. We a r e going to get a hundred people and look at everything. l t i I think one of the biggest things that we do, and can do an a daily basis, is the sort of thing that is called for in this program and tbert we a r e kind of weak on. It is in the general mea of what I call "discipline. " I am not talking necessarily about military discipline. If you show me a dirty shop, I will show you dirty workmanship! If you show me an engineering office where people come running in and out all hours of the morning and day, I will show you a rather haphazard engineering job1 There a r e so many of these things. I know I have arguments with my people on little things like an expewe account. They will be six weeks in getting an expense account in. Now, you start climbing over their backs, and the attitude becomes, Wee w h . What difference does it make. I am a really important guy and I am really doing my job. And someday I will get it in. And don't worry about it. " You will find out that the guy who is slack in his expense account, probably didn't get much out of that trip. SOit is this type of discipline I'm talking about. You can get people used to doing things a certain way, so that doing them right becomes automatic. �of tbts m w and I thlnhE we all are. I am in the For sample, w i ~ ~ g aorzad h g mr oqganimtioaI always get a sort d out of this-becan@ the ~o do is coma up with lW first thing e v e r y b o d y m t on a ch%. rtnd they argm whether the liaes are to be s o i d lines oy d&hd Urns. Inthevery best organizations I Wise seen, no one eves had to refer to an or$anizp~ti&nehrnrt beewee the people were worktug s o 'WBB together #at they automatically hew where tBe reepcmibiU6les were, and who was r e ~ p a ~ s & l e f a r wliert. And they get that way not because somebody drew lsncwgankzation chart. They got that way beeause peaple had b m n pmt4ciag t o make it work. Encidentally, I mfght say on the s u b j d u f o ~ a i z a t i o a e ~ I always look aX them a sort of like a bikinl, What they reveal is very inter&ing, What they hide is vital 1 You can rrpsnd a seminar on tbis one stbject alone. I think the b y to the whole thing 15 this business of our emmranictttions with our people. When I first went ta North American I was surprised, to put it mildly ,to OMtW our so-called motivation prcgram a d d (and incidentally, it took me about two M o m I could find somebodywho could tell me w W PRlf)E me@&) w m mderthe aegis of our public relations paaple. The pMlosclphy of the thing eeemed to &? t h t every timeaomebody msde a mistake in the shop, yougo tothe PRpeople andtell them about it, and they put gUt anew poster onthe thing. T h e p t e r s a r e effeutim for the first dray they are up, maybe. But motivation takes a whole lot d differen* things. One of the biggest motivation faators I kaow of was when b a e fellows were building a spaoecraft, and the tustmna& would get to h a w them. These fellows h e w that tiwy were respmfble for their lives. You coakb't ptaay better motivation^ that Recantly , b u s e mews got busy in some simulator work, we rrothdafall fnEl in the rated the v i s i t a d the m t r a ~ t u bo w i n g ont there, And all over the place ever* asked, ltEey, how come we don't see Joe Blinks aaymore ln O r , "re've you been?" Thie is a p 8 ~ u l i atool, r coming from this kind of a program, bug it really works. hother aside on this I mi#t mention is oazr methods of written c e & m . I reoognize thst records are aboleftdy necessary. There is nothing better &an a gosd mafigumtisn coatpol and procws spec, rtlzd that eort d Wng. But I'm referring now to tlre type d oommunicstions where we a r e attemptto $& management &atLon. All 200 many times I see a guywb couE.dpmb&bly walk a c r w the corridor avlld ia a fellow, but be doesn't. He sib down writ& lzim a mernoradus2. And y w bow, a r n e z n o m is never read in the frame of mind in which it is mitten. I% ia probably one of the Iousieat ways b eomnaWale wit& people that I can possibly tbi* of. M y main imprwsfcm of memos is that when you first go into a company as a yowrg engineer, you w r i h the rough draft on yellow paper for your boss. F i d y when you get promoted, you get to the point where you can sign it. Then tihe great day comes when somebody e b e signs it and you approvk it. You have really reached the peak when you have somebody sign it for you, and you didn't emu have to read it! I say you can g~ on with taege thing8 all the time. But the mast important thing-Walter lhentioned it, axrd I 'm going to repeat it, beeawe my own experience follows his exactly-is that you have got to go and see the people. Tbey should wt be s h k e d when they see you. Let them talk to you about their Jobs. ~ I remember we were running seven days, three shifts. The talk waa thkt the third shift was always the most ineffiaient and, we ought to put better people on the third shift, because aU the good people were on the first shilFt, a d the mediums on the second shift. But it wasn't so. It waann'tso at all. The people on the third ~hviftwere fully as good as any on the first rshift. But what happened is that all the bosses, and a l l the actionwas going onduring the day time. And a t night nobody was there. T b r e was a kindof W h o cares 3" attitude. For a while there I was just living in the plant. The first readion was one of almost shock. The s e c d reaction was ''What the hell is he looking for?". Finally they got to know that I m t t going to bite &em and I was really intereeted in what they were doing. It was amazing. And then should something happea-1 would take a trip a d I would be gone for two or three days. As soon as I would get back everybody would wont to know where I I d been. It is just not the head man of the division being there, o r anything lib that. Everybody ought to do it. I found &at supervision in general, spends too damn much time in their office. And that is why once I got red Mld aad took everybody's osice away from them. But it didn't last long. I'd like to conclude by say& that the most important specffic examplee in motivation that I h o w of are: (1) Letts have a good pmgram. And I think we have the mrrkings of a good program. But let's know what these goah are, and let's stick to them. Really, this is a job for trs on the top. (2) Letts do a real good job this time in coordinating the performance which we want to try and get; the schedules which we want to try and meet; and the amount of funds we have to spend, so that they all Ue together and form some semblance of a sucoessful program. My own feeling i s that as f a r as the people themselves are concerned, we have confidence to burn. Our job is to motivate t h a e people todo it, by getting a good program. To tell the truth, I think that we have grown so much, that a little of tbis hard trimming might be pretty goad medicine. I Wnk we are going to end up by being a stranger md a more productive industry as a result of it. Thank you very much. �HAROLD J. McCLELLAN General Manager Southeast Division, Aerospace Division The Boeing Company viduda, are spending some d Wir time worrying &out future security while trying; to do the job they hme to do taday , Tadw 1 mujd tke to give you my view8 hl some d the p01ffimm$ihablthat f &Mn, mbeiqytaklea ta provide~&e m ~ &m@anb@d & im-ce to NASA i n the ma* fLtLd yeam +$CE in as spoe proerram, with psUI;i& empha~ison- role thafm a r i m a t a d &magem&at1p urn of the mattn4;1ag+ p r a g r m s have fnblptng baa eha 6;6vem@-enf,and industry obtainthe go&@ $% t b @@re. BUt I thhk b~ d m the employment numberswhich all of us are really doing today-in an orderly, selective fashim in a decisive, straightforward, compssian&te m m e r , much of his Iraaertsinty can be elimiaata8. We ctua reduce the impact of this impediment ta moffvatioh. I W, perhaps, the most fimdwmnu poht is qrtick, straightforward, deeisive wtIOE1 with 8 s b r e attemp$ on the Ijart of a l l of u s to let eaeh employee, whv might be involved, know where he stands. W e hime &m.ltrrprseedd &I & i ~ gof swcemes on W ~ ~ o $ % ~ g r a m - A p o U4o through $1. Our initial $@I on'the mi3an a d returnhg #am tioaed wiSh new perfeation. Naw, the frequency of theb Iaaikhm has bea r~~ch&uP~-stretehed outand.attdia~ta Jpeapk are be- talt~noff the pragram at: mmy ef the locations ~ m g b mthe t country. If we in industry let NASA d m on any of the rem a w Bp0Jf.o miwitma-wd I epe~akd failures of my ccxse~blmce-we will have set back the agency's c b w e fez firtare programs, And in tthe eyes of the public md our work forcewe wiIi have started a whole new round of mcertainf.be and future insecurities. The -we af ~ mom imm bWt B%B &Idly pmbbly .$ding with hem is . u P I ~ . lib& o ~ . ~f a@--prchhlyin itldwtry I thbk there to awry this ~;aUms--& o i ~ i v eaction pmuide gmxl i d o r r ~ l a t i ot?~ peaph with re.ecjpwk to their fdtum fn .the space program. m m & - s h w k d r ~ r n b d ourselve@Bak f&'peredIy re- wi&dsiagthe ma&& parfxmt job o.n W b ~ tW k each be amzomplished in a timely ancl coat manner. 'EBe m w e *.19dh@ng fuWe rtssigmnentss will re& fmp~the pd4eyt p e ~ o r m m ~and e 1%5 effort that is put in m todayTI )@b. Now, during tSPio 5).rtm@trwilto??y period, one of the fmdamenWe that we mas%carefully guard against is the lack of %tte!ltionto crertification of employees for eacb job. During times like these, companies and Ore;mh&~nswithin compmies have to do a oertain e~~mm d tr w f ~ i s a t i s nshnd rw~eignmeatcto fill the WQT~~Z&I&&&!ram,. n&maUy, will i l l . mat gaps where people have departed. I &Ink it is incumW&I ably: out. &* rnomkg. I $tress we cmld axp6~e2-.inam d Ulem ta oce;w-and IS& b~ ~ ~ g h t - bent u p ewb gen;Ue3nanin this room, who has anyhe has an airtight, thiw to do Pvl* it, to h e *enin&-dat ~ ~ x g g m " l a t ~or om groups of ins- 37 �ironclad system for insuring that the worker is certified, trained and put through the sort of scrimmage sessions that Lee James and Rocco Petfone were talking about this morning. That makes you darn sure that he is ready for the ball game. A month before Apollo 11, I wrote a letter to all of our first line supervisors who are involved in our space activities, saying that the chdenge we face for perfect performance-now that the Apollo Program is beginning the operational. --is a s great or greater than the challenge of designhg and building the equipment in the first plaee. I still believe it today. At that time I c d b d on emfi supervisor in our organization to aatiefy himself that each of his employees knew his job, and h e w it instinctively. I have insisted on a rigorouaprogram of checking up on this to satisfy myself that it is done. Two weeks ago, I took one of those factory walkthroughs that Bill Bergen was talking about, and I talked to many of the employees at Michoud working on the first stage. I can assure you that that experience was most rewarding to me personally. Each of the employees that talked to me had the urge to tell about what he was doing and how difficult it was to really train and get ready for his job. He was proud of his certification for being able to do it. He was even proud that there was an inspector making sure that he was doing his work right. I know that we have isolated incidents, but I don't think we have a general letdown in morale within the sphere of workers that I talked to, But I think that we in all levels of management awe the employees frequent and proper communications about the right things. And I think if there is one message I would like the seminar on motivation to carry back-and perhaps to deal with more tomorrow-it is the question of applying o w motivational techniques-ad the extra dimension of comanunication that these Drograms give us-to the various levels of management. - It seems that when I hear about motivation, I usually hear about the fallow that's welding, or about the one that's inspecting, o r doing this or that. I, for one, would like to make s u m that we w e using this tool to carry the message through dl the ranks of management as well. Now, I think there's another pitfall. Although I won't dwell on it, I would like to mention it in passing because of the t i e of this seminar and some of the discussion that has preceded. There is a pitfall into which industry must not fall in the days ahead. It is one of diluting our skills, o r shifting too much of our management attention and emphasis on future NASA programs. I certainly believe that industmy has the clear obligation of helping NASA, through 'studies and their own in-house work, to determine the proper steps for implementing the new programs we have heard about today. However, 1% think this support to the space agency must and should somehow be clearly separated from the ball team that we are putting through scrimmage every week to play that next ball game that is coming up Saturday. I recognize there's some level within a company where this all comes together, but I w ~ d dcertaialx urge that we guard against dmpp&g it tw low, There is aii a q w t about management and motivation that 1 call a flmanager working his feedba~kloop. I would like to talk abmt it for a moment. First, let u@ recornbe and take note again, that we have had eight straight successes on Apollo-six manned successes. Now, why ? What k s made this possible ? Well, I happea to think it is because of the NASA/ industry team af Bia;By motivated people that have been warking om the propam, in addition to the other things &at have been mentioned. I think &is team is typified by some of the people we have heard today-Lee James, Rocco Petrone, and George h e , if he were here. And I could name many, many more. You gentlemen have heard two of them speak. Aad thi5 &am is typified by men who pay great attention to detail. They really know the people and the hardware. They energetically investigate the symptoms of potential problems every bit a s hard, if not harder, than they do the real problems until they ape thoroughly understood and the answer is very clear and completely out of the nag list in their minds. The paper work system, sure, follows up and tells us this is dl cleaned out. But in the time we have ahead of us, that attention to detail is going to be even more important-if that can be true-than it was for the last few flights. I think you owe it to each manager, who is working in your spheres of activity, to point out to him that the really good manager is the one that has himself set up with a good feedback loop of information. It comes not just from paperwork o r staff meetings, but from his people. Ensure he i s energetically using this technique with a real short timeline and thqt he is taking the corrective action withinhis sphere of ability to do it. When done properly he will be able to sense problems which are developing before they become panics. I think thir is probably the most importantpart of our lnscnzrgement challenge today. I would hope that somehow we can utilize the extra tools of our motivational programs to establish this in a more effective manner at all levels in the Apollo Program. If we have-and please don't misunderstand me, I think in the large part we do have, but I think there is also room for improvement-each managsr on the Apo110 Program inindustryworkhg in this mode, he will be so excited and &dlenged and motivated that he won't have five minutes to worry about being;insecure about the future. This brings me to the subject of motivation which I want to cover. I think when worked right, this attention to the feedback loop of information and the f ollowup on it, can be one of our most powerful motivation tools. It should be used even more than it is today. The reason I believe it is because inherent in this mode of operation-this face-to-face communication, beginning at the lowest level and exteading through all �s u c w 8 ~ i v eietwb wf the orgaz&ation--is tbe everlW& MI1 tQ ktwp et it until that p a r t i d a r symptom or problem is clearly d d t with i n a manner that eveqWc3y @an tinderstand. I t h W aur m O t i v & i d projgrms, for 7Khich most compmi8.s have different names undsr the Manned Right A e e n e s banner, ~ &rea very, very important part of t&$s whole prc3cegs. I will confess to feeling the way dames ekpmsse8 it &is mornjag-kind of h@&uGat f&&. And f Itnew tnang. other managera throu&W our 0 m b W o n -re ~ i ~ Timy t , tiw@@t, '%%dl,what. am Wse m ~ olsprograms (of &id%they sea ouW& signs in the way of posters) maUg do?" I OW it h e besa g m e n to my satis; f"&%oittkfittwh&.Yt r e d l y does 1s provide some extra a v a e r s of communfcati~n0x1a subject that one Mivfdud, ar m e group of fndividuals, is trying to get aorms . When we recqptze that each bum= being r e d l y only hears &at part which he wants to hem, and each will hear a t m e thing in different ways, and some lmmm beiqg5 will respond to one method ofpresentatian while &&hers will be totally a e s t i v e , then I think tb ~&&WLadpr-arn wtll give us that &led flexibili*. lf us& bg ~rmmgersproperly, it amplifies th&r &iIEty hcs@ma&at%with the people with wwhom they d d . I would like to suggest that. we attempt to iapmvie the Wlization of o m motivation program in just tbat xnammr. Qne d &e programs we have at B a g that has very mccessfuJ i& the 3-ma.r Roll of %onor. We select d e ; s a m e m p b p s and havg their name and contribution to theApolloPwgx'am rsoarded in abook 'I'his book, whish e o n b M papar &dgrzed tolast 1000years, wfll ba nr&ntained for posterity in the Smithmnian W i t u t i o n and Library of C m ~ e s s , Further, each honored employee receives an engraved doubloon a s d d e a c e &!at his name is being placed on the Lunar Roll d Honor. . has r a a ~ h e dsome people in a very deep and fmad%tmmWway. We had one gentleman f happen to knm of who falt SD strongly about it that he has made provi~ioaein his will for the line of succession of thaw emdentials to his heirs. But I am sure-and I b&g this up only to illustrate-that we have some e m p 1 a y e ~that could probably c a m less about it. It jwt & w 4 5 matifate them a s numb, or give them a s muob of a p ~ e t 3 v ereaction ~s others. Them are obbm thiag;s that r e w h those employees. D i m t coatact wlEh the astrmauts, a s wm stated earlier, i s a certainly me of the most powerful motiv a t i d took we have faund. I think this clearly tndicates the type of motivation that we a r e talking a b u t is this human-being-to-hum=-being relationship, where the person can really identify with another indiviw. Lastly, crtl the subject of moth-ation, I firmly believe tb$t our nmtivsltional programs sometimes overlook the c20-itive nature af most individuals. I #.ink &is is lme in the shops, as weU a s other places. I think eachpersm, with very few exceptions-and these emeptims are usually weeded out pretty rapidlyreally wants to do a goad job. Re wants his co-workers ta b o w 'thd b . i s do* a good job. Of course, he wants hi$ boss to know it. I think taking advantage of this f w e t d human nature in a positive and proper way can be a most powerful tool. I had apersonal experience inthe early days of welding on the S-rC krulkhead at Michoud. I found, much to my surprise, that the information1 was looking for-which wwfd tall u s how bad ~~a r e d l y were-was in our record sy$tttgm. But it was buried sa deep that it took something like s$x to eight hours for somebody to dig it out, summarize it, and get it to me. It suddenly occurred to me that I really wasntt the one that needed it, because I hadn't done any welding since I was in high rschaal. The individuals who really needed to see that data were the ones actually doing the welding. Well, we had quite a psychological seance on the pros and consof that me. We ended up having it introduced by the first level supervisor, explaining the purpose to his e m s in a positive way. We also posted the data, After every shift the data was updated. And to the surprise of mmy, we fouhd that here was the one mostpowerful drives for keeping the defect rate down on those welds. Once in a while a defeot rate would start up. Aboutall it took was the posting of the day's data and it would start back down again. Maybe we were lucky. 'But it is one example out of my experienee that says tbat if you can, in a positive manner, appeal to the competitive nature of the people you might r e d l y have a powerful tool. What is my message on motivation 7 First, I think it is different far every human being, But I think that it has something in common. 1 think basically it boils down to saying that I want to know somebody cares. You want to know somebody cares. A worker wants to know that someme cares. The ability of various people to show that they do care b u t his work and what he's doing can be brought to bear with good management plus the use of the motivational tools that have been developed. However, the communications process needs the advantage of feedback I urge each of you to take back the message that management, on all levels, must be much more active in this area than I think we have been. . W e should remember that the future starts now-this minute. What was said a minute ago i s in the past. And every day the future starts anew. The next big event in the future for most of us in the room-and the people you are goiag to talk to when you leave this room-is Apollo 12. Pete Conrad, Dick Gordon, Allen Bean, and all of the flight crews on subsequent flights must be made to feel that the team represented by us today, a s well a s the people who work with us, view a i r missions with the same single-minded purposefulness for perfectirrn that has typified the Apolla mission successes to date. Let us make sure G t w e carry this message, and other messages from this seminar, back to each member of our respective work forces, both managers and employees alike. . �PANEL DISCUSSION QUESTION: Will the various centers cmtinue to provide p~~jltea-s and motivational xlaaterisls to the contractor? to get themselves all on board is a very good thing bsy&m right now. And certainlywe are mainfor t taining mtcnqp~ltentcontact by g&ting everybody reorie~tecfto something on the new team, even though they have all betin a part of it, one place o r another bdore. MR. SCHNEIDER: I will field that one myself- The answer t o w is yes. QUESTION: We have a question hem for me. Are any funds available for maintenance of facilities d training for contrmtors who a r e essentially all done ? MR. SCHNEIDER: In the AA9 funded a m , if you mem someom like C h q s l e r , for example, w r h we have the launch vehicles in stbpagg, we are marfatrr,inftyz: a crqwbility a t t h w e c o a b t a r r a so that eve can rmotivate thje launch vehicles. Wit&mspect to supporthg s u b tractors and s u p p ~ r &r s all of their equipment is delivered, that decision will be made on a piece-bypieee brawls. We will examine whether o r not it i$ required, and take the appropriate action. QUESTION: Next question is for Lee James. It is from Mr. Trainer of DCASR. How do you maintain top management active support? QUESTION: Now the next question is addressed to Walter Burke, and I thinfr it is a particularly good one. It says, "How do you motivate the people building commercial jets ?I1 MR. BURKE: I guess it is the very same way that we do on W s particular program. To me the thing that gets the best work out of the ~ e o a l eb to diamss with them my problem, and ask ihe?;lh<rw do they think they a n help. The hardest part for me is to keep my mouth shut, while I let them tell me. If you can do #we two, you get the people that are going to be on the job era interested in contributing that the word motivation just tells what t h y m e doing, rather than mything you Instill into them. And csmmsrcid j e k are one of the greatest pieces of engineering that has come d m the road for a long wMle. Nothing is more beautiful than a M=-8 (and I hope a lot of DC-10s). They'll motivate anybody. QUESTION: The next is amotivation question, and it is addressed to Dave Law. It says, "Can we use visits to the Mission Control Center as an inaentive award in the same way aril we would use vlsitrs to the Cape?" MR. JAMES: I really think Bill Bergen, Burke, and some of those people answered that question for me. Certainly a lot of this is direct communicatioa, and communications is one of the toughest problemrs we have. I feel we in NASA a r e working a whole new chain now. And that chain is getting educated; is getting around a great deal. For instance, I have changed jobs, and I have a new deputy. The Saturn boss is now Roy Guthrey , who is here. And they are now going throqgh a cycle of getting ready for the next launch, 507. My deputy (who is new to the program) has been on the West Coast with Roy all week. And Roy himself with his new deputy, Dtck Smith, have been on the West Coast all week going through the flight readiness review cycle to h e sure that all of the things we have been talking about today a r e not going to happen on this next launch. The newness of them in thme jobs, and the attentionto detail that they are having to give MR. LANG: Bill, I am sure that such a motivation device could be arranged. There are regular tours out here at the center that a r e fairly public in which some of the facilities are available, like the simulation facilities in the mission control center. But I am sure you mean during ttn actual mission, and I think with a little preplanning that could be arranged. QUESTION: Next question is addressed to Hal McClellan and it says, llRemembering the old adage 'Once burned, twice shy', do you think the new employees expected in the space program in 1971 and 1972 will be as motivatible as the old team?" �MR, McCLELLAN: planning an 21. clays out of the pad. This ia made pomible became we no longer have cryogenio o r hypergolias tbat we have t~bad slshrd. So we a r e WeU , my answer bthat irr an qualified yes. I trutnk try& b d e ~ o u p l &e e two systems B o ~ t e l there y tZrat the exietiw employees a98 the new emplqees t h a t ~ o o m i3 ~ u r s s p a c f e p ~ ~ isf u ~ capability ~ on Pad 39, such that it ahouldnlt taIly joiniffg; tb~&pragram for a desire ko gmtbipatg becom rany constraint. (The mttwer to the question in m&ttk$%d4sr g;rekted a&veatwm. Naw I t2dt& that is Ifnslmgpythe way I am.) wheaithy rreaazbjeotsdtathe pmsurrsrm isnposdugaa them by $heir wnrk&g e n v i r o m 3 , a d their naanQUESTION: , tftrt ean pPt % e m M w into that. BWt, I . metiwah that underlies pny pkr?aon &at is a part of tlw s p a e w program. Now Bktro is aras for BiU Bergen that, gee, I could hew .ew mymu. Wlt E gwbmb I cEldnlt, It says, 'CL natlce yon said, 'We didn't have enoughwe m ' f k"pbenmgb money. ' A d o cost w w high. Crra the E j U A s r o w e team redly do a program diHehatZy po 1t c a b lws Pv MR. BERQEN: I didn't mean to sey we dididnlt haw emugh money. I said, no matter what that amount of mangy was tbe progmm ahodd be ksflard -so it ie mmpatible with tbe f m d h g . In &her wr&, we s h d d n l t plan on dQtaa rpemaim m y bey;~nBour new. The b b r part ad W quwtioa is, f t Cwe ~.build t?hings for legs m m ~ e y ?The ~ m m r is ~bviowly,"Yes, we Can. W t now yau a& yourerelf, lfWill it b the And this is ths question that we really cm't answer. Are we going ts stick wit31 the philaecyshy t b t ha8 s o f a r barn a wry good one, n philaeophy of 100 percant sucwis8 ? i tkhk \wetregoing to have to maintain very ~trtcs t e a in S W 8 ~-s M certificsttioa, feating, vibmtlQntesting, and yols name it. And thi~ in my Mnitfon is mi- to cost a lot of money. It i s debatable, for example, static testing, is one we alwi~yeQPUC about e l h n i d i n g , aud you can save a lot of mantay. But my kstgue~f4b, though, we are not gaiaig; to let the reliability fmtors take a secondary priority over the cost factor. The next one is for me, and it says, llWould you preferto ham ar r e a c t i v ~ t d W 34 o r 37 at y m r disposal PLP 8 d b ~ h ~ i C0*l€S n g with Ap0u0 ?" MR. KWEIDER: Well first, I am going to lm using Complex 34 o r 37 (we haven't made that dtwision yet) for the hunch d the m w s d vehicles wing tbe S a r a IB. A@hr as Conqhx 39 g w , we a r e doing our bast to deM>upLe BAB from Apollo. In that we will have r Wisated lot d a dedicated bay in the VkB,andwe a* &w.h r h g our system such .that we can do &mo& all of our Cape testing intside of the VAB. We are only not nsspe the Manned F l a h t Awareness Program to a NASA organ kdional level to include all of NASA, unmned as wall as manned?" This is addressed to anyone. MR. SCHNEIDER I will tab the l i b r t y of answering it myself. I think it is a very goodquestion, and I understand there have been some thoughts dong those lines. It is quite possible that it wlll become Space Flight Awareness, rather t b n M a n k d Space Flight Awareness sometime in the future. The next one is addressed to George Meuller, who likswiae ianlt here, and it says, "In the minds af the people of the Unit04 States, the Apollo Program was to put a man on &e mom. Do you have a catch phrase o r brief description of the next goal?" MR. SCHNEIDER: I will field that one, too, and say, of course. I consider the, next goal as Apollo 12, and that is still to land a man on the moon and come back. But ff you mean for the long range, the way we a r e steering the program hopefully, is to a programthat is less epectacular and more undemtandable to people. We are looking for things like thespace statiaa and the space shuttle. You may have heard Dr. von Braun (I understand from reading the newspaper) said, "Well, maybe in 1976 the President of the United States will be able to have a fireside chat." But to have a talk with the nation from spaee. I think 1976 m d d be an awfully ambitious goal. But we are trying to make it such that space flight isn't nearly as specialized a s it is M a y . That is why as I said befare, I think I am in a transitory kind of program trying to lead into that area. Certahly AXP will still be specialized, but we are hoping to get some of the specialty out of our systems and components. QUESTION: For anyone and I will pick Lee James for this one. "Where will the polar apace stastion be launched?" �MR. JAAES: MR. SCHNEIDER: I guess that means WWtt C h ~otr Emt Colast as % launching site? Well, %%em's c%nougbextra eneqgy required for the might y ~ put a in arbit to require, I think, a vehicle someQ3ng on the~o&er of the Saturn V That would be the sfs;rting -win%. And I guess the question lenda itseu to the fa& that if you are doing I will field &at for R w o , and say .Y in the sense d a w e re!scw in the chssic. Sunday Supplement sense, no, tbre L not. However, a s you recognize, s p w e rescue has m a y , m y wpwts. Of cOtErBe, the Apollo Pr08;ram will c6n;tinue a8 the A p d o Program had. In thfa BBP Program we do not have a rescue ca@i%ity per SB, except for the fact that we have retreat m w h n l s m w b r e tlte cnzw can obviously go back into the aammand and service modtrle and come back rtt any time. If the command and service module is the source sf the problem, we have the optlon, at least up until the time when our food and water begins to run out (and incidentally we a r e putting a year's wo&h of supply on there hopefully) of just staying there until the new command and service module is s a t up. And I do have one eommand and service module. Obviously that isn't rescue in the classic sense, but it says, " ~ l r i g h t ,there a r e retrieval capabilities. '' When you get into & e r a of tbe shuttle, then you begin talking about a vehicle that will be reusable and willhave quickturn-around times. And then, of course, the idea of rescuing stranded people becomes practical and something that can be real, including its use on the planetary mgssione. . the polar lautlch, you eitktar utilize an exorbitant amount of energy getting into it, o r else you fly over some South American taountrtes. It would appear to me that inrstead of moving this eatire oomplex to the West Coast, the only o h i c e is to ruegotiah such a launch, if we a r e ever going go have a p o k r m e station. I don't latow &at W is a firm program item right now, so I presume they don't have these negotiations with us right now. a t I think the answer to that has to be the East Coast. There ie the d t e r native, of course, of a northerly launch, where our negotiations a r e closer to home, but so is the first land that you go over. QUESTION: Will Manned Flight Awareness Saturn/Apollo launch honors activity be continued a t #9C 7 QUESTION: MR. SCHNEIDER: The answer to that i s an unqualified yes. Quation for Walter Burke: What should the criteria be in determining what types of jobs should be cmsidered in giving people the FMA Snoopy award ? QUESTION: MR. BURKE: Question for Bill Bergen: Y w mentimed aircraft design. Do you think that a 100 percent reusable booster and spacecraft is feasible on the present time scale ? Or arosldd a tmdmff, i. e., some expemdrrbles, seem to be the mmt p r w t i c d approach, referring of course, to the space shuttle? f thinkif youdisting~ish,at any time, the value of the contribuUon of an individual as compared to another, you will in a seme really i~validate the whole program. Individuals a r e selected to do a neceesary job. And each job that is so necessary requires such perfection that you should reward all on an equal basis, rather than distinguish beween shop personnel, engineering personnel o r flight opertttious personnel. The shop man, from my years of working with them, is om of the most valuable tools that the American economy has, and nothing should be done to make him feel that he gets a second grade award. MR. BERGEN: You a r e very restricuw?wbm y w say 100 percgnt recoverable. In my opinion, the r&yiag of these things ia very &$5nitaLy feasible. As YOU probably know, each one is cheeked out after it rebms, and in none of the f l o m spaecraft have we found any anomalies after flight, There are a few things, for example, that are very sensitive, like perbatteries a d h a d oontroUersl whsah w d d have to be changed, But I tbinkrdtght awl reuse of the present spacecraft is very definitely f w i b l e . QUESTION: Dave La%, eould you field this one, please? When do you Wink the NASA program options proposed to the President will be decided upon and NASA given a firm go-ahead? Do you anticipah significant Congressional opposition ? MR. LANG: Aquestionfor Wocco Petrone. It says, "Space rescue has not beendbcuissed for future missions. Are there any plans owcerning apace rescue in the future?lt Theanswer to that is we have been given no firm date. However, there a r e plans, and we a r e moving out on them. As far as Congressional opposition is con- �c e m d (as in every Congressional action) there will be oppwiaon, and khequwtionis just how strong tbat oppositia will be and to what level. We have no indication a s to which one of the options will be selected, o r how fast it will be selected. Lee, could you add anythhg to that? MR. JAMES: Question for Bill Brgen. It says, "You, a s a prime cmhrwtor, have cited the problems of communicatiw between NASA and yourself a s well as certain of your organizations. How can the second and third team of contractors be stimulated ta do the jab? MR. BERGEN: There is one thing, Bill, that seems like it is worth saying. I find the emotional support that I am aware of in the Cmsrem , and with the public, e k . , to be high for the options given to the President. I think that the real problem, which all of us might as well understand, is that the year end budget is taken up by present day programs, This really doesn't giveus the option of exercisfng one of these new follow-on programs in the time scale that I believe the emotions of the public and the Congress and the President would allow. That is a pretty good question. Baaicdly, I don't think he has a prvblem any different than the prime QUESTION: QUESTION: A question for me. Is AAP fundingsufficient to dlm continuation d the RgtQA system that keyed the ApoUo Program success? Is the same WQA approaeh necessary? Que~ttim for Mr. McClellan. Slowdown in launches has. It d e p d e ugon a e severity of it. In aome cases, we hatre bad a subcontr&ctor who has had a little difficulty here wd there, we have been very, v e w helpful to Mm, whether he likes it o r not, and commaiaate very intimately with them. So here agaln it i~ a xrm8-r of degree. I thinlc communicatiom is a very fa~cinatiagsubject. I could talk about it forever, and we will never solve it. But it is something that you have got to keep working on, all the time. at the Cape must give a disturbing feast o r famine coxdition for €ke launch c r e w ! What a r e you doing to level the workload? MR. MECULLAN MR. SCWNEICrER: We have baea fwdmd in rPkP h a sat&&otorgr manner. We a m not hurting for mmey W year. I hope tbrs same i s true n& yeax. We are in areasonably g d shape, bItt we h v e not elwted to continue dl of p m i w ApoUo RIBd&A practices. Where we a r e ink-& with ApoUO, like the CSM where we waul&'t separate them, we are oontinuitlg RWA effort $d t h ApaUo and AAP will be built on B e same sk-a. Ia amas such as experiments, we are making some rather wide d e v i a t i w from the tditimal W,ApoIlo, RaaQA requfrements. We ape hying B h i l o r the R&$A requirements to fit the n d e . .Taub o w we usually have C&bgory 1, Crew B&@; C&egory 2, Mimion Success; Category 3, Seoo~&ry Qbjec@ve ; and Category 4 seems to have the tltle All Other. I have a new category in AAP mlled Category Experiment. And that just says we a r e treating expetimerb on an individual basis and giving them the R&QAtreatment that is commensurate with the eperirnent. On some of them,we a r e telling the pritlcipd investigator, llDeliver a satisfactory piece Qf equipment to these specifications on such and su& a date." If it doesn't work, we aren't going to fly it. And it is his responsibility to be sure that it works. On other experiments, obvioualy the more complex ones, and ceFtainIy the ones that interface with tlre spaeecrstft o r &e workshop, we don't have thgt &titwb. We have to tailor the requirements to fit the need. The Cape Kannedy area, for our part of the action there, is a Ceting operation. We conduct kunches of Minute Ma,and help NASA with the Saturn launches. The nature of that type of activity is one of peaks and valley&, We reaognfze that, a8 do, I am certain, most of the work force tbatls involved in that activity. ThL does add a complioation, in that particular instance, that when you go into a valley period, we have to call upon people to provide them other opportunities withia the company. To make f m i l y moves, as other companies have, we have move policy. It creates an additional hardship on the people. But so far it has turned out to be a workable situation. I think I can best illusstrate that it does work by my own experience. I have moved every two years ever since I have been on the ApoUo Program, the last seven years. Each one a little bit traumatic. But looking back and summing all of them up, it is quite an experience. QUESTION: Question for Bill Bergen. Will you please amplify on your statement concerning industry participation in NASA studies and other preliminaries ? MR. BERGEN: Well, as I recall, I was trying to make the point that at this stage of the game is where planning, and good �planning really pays off. Take these new p of which I think I cited t k aidkh. T b t h g C o d n is to sit down and esaatbltab bye an w wmmt on what are the p r i m a r ~gds. A& ef let "~lls lZQt clobber up those primary 60- by patbi%in a lot of other things tbatmul.d be &ato hi%%%, or t k x g sibmebody would like us b b v e , m h wej lose trackof what we a r e really trying to do and what we are a&ally doing. there rt formal mlod for mkg who the critical p q t e are, w h m is for fh&ng t b eritical compon e d s l I'm @ng to ask Lee Jamgel if be wmld like to anmer that. MR. JAMES: Well,I don't lorow bow f o r d this @anbe. I guess we will probably have to answer this by example. If Veto Pec%o hem at uth~yeier,who I saw her@!W&yty, will excum me, we might use him. Px&a.bly, the Lee James, I guess yort arethe best qualified t o field this one for ROCCO.It s a p Dr. htrmf$stated the qualification of hardware& a &rough faifwe m d y sis as being assentid f a r the sme6us of the Saturn missions. RSC prcrvides correet eval.uatio&s for failures at the lam& ~ hBut . does R86 akso m11ider the possibility of &he reeurmnce d these hfiums during flight? MR. JAMES: Well, the first part of that isn't m t i ~ e l yaccurate. I think RCKleo would say ' W C irs an engineering onthe-spot activity, and for @om@ failure down there, they do get into it f i s t . l' Tf the program management chain, which I used to bea patrt daa, gets it& tl& right away and finds a deeper analysis sf Ws is required and comes out of the ffSG iaboratoriw, of course, we wait for that analysis. And Racmlshappy to wait for it. What really is done at the Oape is to provide a quick, on-the-spot d y s i s , and as we feed &is back through our charnels to our prime contractors, tf that makes sense, thenwe go&% it. Tf a deeper analysis is required, then we have to take the time to do it. I think simultaae~1sly,thou&, we ought to reJ b e that the paper work through the UCR s y s t ~ m ,etc., is feeding every one 09 these kacrk through the entire system. It goes all way to the primes o r the v a dors (as the case may b)to W e 5ure that the astion that we took wasn't just a lucky one. 80 I ahW we a r e real careful not to let superficial answer that might come up on spot k the final answer, in case that answer might be wrong. QUESTION: It looks a s if we hawetime for one mare qu~stion. Is there one more fmm the f l w r . The quetisn is lFfs placer in our whole system, where the critical @kills dropped the t m s t in- the c x s r e i e , b in t b mnufacture d tEre develop& dearigm for the 6-133 stage of the &turn IB, wMoh is done by Cbrygler. Since that a & ~ t y l w a sskrbd fimt, it quit%nabrally ends be3or-e &erned tJ.m &tarn V wtlvity. And yet these vehiclc&shve to be lannohedwith the necessary backup of an m g i ~ r i u g barnto tbnstnimum depth possible. And backup in manufwturiog is absolutely required and certainly the right checkout people. Mow, I guess our Gowrnmntsl procees, a s Veto would probably be happy 20 tall you, c o m b for doing this rather thoroughly. Every time youget scrubbed down a little bit more in money, ha has to e-he those critical s k i l I ~jnst a little bit mors clmely. He ftlLs probably gone t k w g b tlws ref&mtAmn n s w e us of examining the c r i t b a l eklllsthat he really has tohave ta Bs this fob of coming back up, probably tea o r twenty times by now. And emb time we bave to decide if the budgetary process iis suob, that, QK-we will really make a Judgement here, that we are not going to have a welding problem come baok up that has to be redone, and take a chance an n d beping the weldem. The next time it might be somethfag else. There are certainly ermneprevmed exp&rta,and things like this that we identify that we haw just got tn keep. So the real problem now is h profitably utilize these. I think it w s EJiU Bergen or s~mebodyliere earlier tbat e d d that you oan'tget a soneept prsm motivated and theta just prrt htm on the &elf and say . y r time comes up two years f m m now. Ne haza ppt to be oreatiwe during that time, 60 mceg~uidentify them, the, proper u t i l k d i m of them &ring this drought, is r e d l y s problem. But I think it is an i t e d i v e proceea that we have gone t h r o w now with each of the c o a 0 r a o t a r s - ~ l a ~ North , Amgrican, Being, and Chrysler-enough times to redly ferret out what critical skikillswe just cranlt do away with, eventhough they may not be fully utilized during the low period. �MFA CONCEPT AT W O R K �JOHN W, SMALL Assistant Field Director Space Station Task Group Manned Spaceflight Center Frask Bomm stsked me to express hirr apalogiea to you f o-rnot baingable to attand this m m b g f s wsslon. Ats Dr. Fmi86 said, he was prs-emptd suddenly by the White He,atse. PLB m a y of you know, Frank digeontbued hie active flying status in January d this p m r to &vob his energy to formulating what ttr next major w e mtivity will be. fh asked that I pass on gtFd briefly describe the proo&e &ughts to gram a t we a m n m working on. A kev Pemwt Inthe plan roo heard Dr. Mueller de- a wrih yesWrdg is qGe station module. Recall that he mentimed modules will be playing quite a role i n t b mat sptteaprogr%m! This module will be capable d a wide r m ~ eof wienttfi~aotlviGY 4t e c h logical applioati&s. The space station itself will last for ten years, with Borne resupply by reusable shuttles, that you heard about yesterday, It will a~.ooomm&te a twelre-rnm crew. sad will be kmadmd la& earth orbit tq thie &turn V. TMS p m c d a r d i g u s a t i o n ( F i w a 1)a~tllkesa nuclear energy s m e for prim~ m~ of 26 Mlowa;tts, I t also has a solar cell power syotmn a bttukup c+iZity, - One d the firart tkings we will be doing after we launch a qwme s W o a in1875 will be perfarming an artificial gfxvl& eqxerbenrt, This particular eomept uEilLes a spent $@tarnff m e . By oomcting it with a cable arrange.$nent to the spaoa station module (Figure 2) and by rvt~t;ing this whole affair at &ppfoximat.ely four r w ~ l u t b n sper mimte, wo obtain up to 7/1.0 of $he earth1s gravity at the space statioa module point, The spwe station mduhe will be orbited rn (4eg)dt~ttte Irumcha andwill be joined together ;rtvarta$ stages of a q a c e baeebtrildup which you bard a b u t ye@tt%rday. The space base in this particular configuration (Figure 3) utiiizes an artificial gravity capability by a rotating hub arrangement, Those compartments 1 II 1 �are shown at either end &&twauldprovide the artificial gravity to the men. Over hare, on thefairlydarlc side of the figure, I believe y w can makclee out our space shuttle that is dark& to the slpaeebam. CBviously this is another key tothe next p r q p m - a lowcost, reusable @we shuttle that w d d be able to sustain the spme base activities through refueling and through cargo x e p h ~ e m t . The compartment a s shown in Figure 4 dong the hub axis is a zero g r a d e area ftnd the rotating areas will be the gravity. field eompmtment8. We have f rm flying compartmentsh a t m e c b k & out on the spwe base and can p e r f o m ~ e ~ ~ i experiments 6Ps in orbit around the space base. ibltbmgh we bvsnlt dtea*ckd any adverse bialqical effsct on our astrenaats to date in the zero (3 envirament, when we are talk.txyp;.abwt the 10-r dusaptian mbsfone, my, of a phmetary nature of ypwards of two tr;,three years, we haven4 yet studied the biological prooeases emugh to esEablish what b e e longer term effects will be. The lab, a s you see in the contjepktaf form in Figure 4, is actually zt facility that ccovld check out not only the man and hihi13 oonditioniag (unlike other experiments that we fomd in C&mini and Apoilo which were diacrete) but many aqMcts of t4-mman. It could also check other triads of orgtWsms b stzldy eB&s that gravity wtadly~min *rm-wc w$p s t a d -8. 1 mQght afmg , P&es t.@ h -o~h&edo $ s s ~ ~ T t f a r ie&?b@thgeggE i t M t r g l b r e orient itwE. But, i f you push %tover, and keep it over, ym will get a &a@ d deformed frogs fronz thoae eggs. Same will br Ws*n withot& a y I*, aid there will be oreaturea t S vaz-bs sm. &a there fs a m m b i s m inlife tbt i a gravity-dqxndent. I might also mention &&t car11(41 this yew in March, Dr. Christian Barmaxi had a fear k t e r a t i n g comments to m&e to s m & u w 5 W csf the 3tmw at Representatives &at s e W ka Pt r e j a a n pr-em that we are e q e ~ i e n e i q g & e ~ r s p b t s .EBmPetifely, la@ mm$ioned Wb:&e ceU QZ & d ua are the same, but the m&al atmotar~,%haDraiQ$bat.b i d e f i e cells together, is different. Bnd it appears to be very gravity-oriented. Dr. Bamard has suggested experiments in space to Jeam more Of this phenmenon. I am not sulgge&.isa; that this space base facility could scrlve aU mdtclilll probbma, but I rn sayin$ a t this is a unique fadiity w e e W be utilized L look et varying Q9 gravity ta better uadmtpmd our hE1IE1Etll rneehsnbm. FIGURE 4 Figure 5 skmv~en dtmc&iguraticu1 of a space base, &gain oolliiksting Bgwm-ioua nodules ofthe m e station &tzW Wwther. The artificial gradty effect is created by. a '5r9' wtth a r o k t i n g b b . At the end of each of these we have r pml-r r w t o r Theae atre flying in W s dimtion, and again we hirre the zero G operating arm, md .the gzdrlty weas. Ovew here you see another free flyfng wtrmmisal module which I'd like to s h w on the next figurn. . Figure 8 s h w s the free flying m&ulst d w k d to the spa- baas priar toflyhg out away from the influence of the space base to sbtdngCKld astronautical readings. It has a 120-inch telescope. The module itself is FIGURE 5 �FIGURE 7 p&ad off by mactioa control jets, Them solar panels am a h m iA the atOW& ~.oBfiguration. After cheakout the ment-ntmthe coq-ent. Thisdoor comes op~n, tub3 W ~oan B be made of the miverse, without the a t m o w r e getting in the way. 1'4 like to, with t b next serieer of Rguree, mention a few &at could be dune in spree. Figure 7 is aa BrXi(Btafdwmc~ptimDf certain earth r e l o u re~ mote sensing Qp of equipmeat. Now some of these figures that I'll be sbwing will rqretsent o r typify thrisgs t k t we cgn Be in space. It doesn't neserrsruily mean we'll Xrs doing dl of these things in the space base, but we do i n t a d to complement 8utomabd satellite~.Where tt h e 8 sense, we w i l l send t r a i n 4 base, because the goal not te require the very ~ r o a&Wing s thrrt m ~ t r normally a get. There wW '$e a limited crew ~ w b rbut , tr large capability for transporting scientists of the general variety. thw~ FIGURE 8 Figure 8 is a picture of the Dallas area and I am going to try to pinpoint areasfor you, if you can make them out. There are several reservoirs around that are used for drinking water to service the populace. As you can gee, there is some silt filtering into the reservoir, there. Now that's a very interestingprocess, and the hydrologists can learn a lot about sedimentation flow from a synoptic view from the air. Figure 9 is a Gemini VII film, an infrared picture that Frank Bormantook. This is the ImperialValley, which i s very well irrigated and a very lush areavery cultivated. This is the Rio G r m e River and this is Mexico. Now the infrared film is sensitive to the chlorophyl content of the crops; infact, the redder the red, the greener the crops, and the more healthy they are. You can see over here on the Mexican side of the border, it is not very well cultivated yet. The other bluer areas show uncultivated lands. So we can get an idea of the health content of the crops. �FIGURE 11 Purdue is helping us obtain r e f h t a n c e signature properties in various amps (Figwe 10). The "wv stands for wheat, and the "oft stads fox oats. Over to the right you can see a format that's been established h t eingles atit khe wheat from the oats and relates i t to what $he total resource in wheat would be. Now all this can be geared to a central processing station within the spaee bme complex, and other data need n ~ be t transmitted to the earth to get OUT total wheat resources. Figure 11 is a n ~ t h e rspace picture taken in Apollo. We have a contour of cloud heights. Where it makes sense, we will send eome of the trained weather observers up there to get a better handle on our long range weather forecasting by these contour plots of altitude, leadkg toward our ultimate dream of actually controlling the weather. FIGURE 12 Figure 12 shows a program that we're pursuing'. Yesterday you heard mrioua dements of the Apollo Applications Program, the first three portions of the chart, and today a bit about the space station, which we plan tofly in 1978, and a space shuttle tothe right which will also be operational at that time. All this leads to a space base capability, a facility capability that NASA would provide and the country would have. What this wiIl do is lead toward a general capability of planetary flight. Figure 19, for example, could be a space module, that you see to the right of the picture, that i5 being wsd in a Mars mission. A little bit further to the right you see a conceptual drawing of the Mars landing, and Cwa vehicles further to the right r q r e e e n t Iander~that could be deployed from an orbiting Mars vehicle down to the surface to bring various samples back to the orbiting Mars station. FlGURE 13 �So very briejay, I hope I have given you ~ o m eingight into the aetirlty N a G is presently engaged in, with fairly slzbskxntirif. Mustrkl swo*. I wsatre you it is a very, aery a i p r o u s effort to pravide the nation with a broad ba&wtP4chnological capability in sptice, Iw& like to e n r p h a ~ h that e right now we w e hthe px6grmx1 defint:tion phaw. This is in anticipation of program approval for national commitment in fpme. Ats Dr. M u d e r said yesterday, we are qui* opkimistlc that we wiW get this appmvd. The Vice President has errdwlsad it, we feel optimistic that the P r e d dent will give hie approval. But .the optimism that we have is based on the confideme tBaZ the country has in the space team that ; i c W l y made fieApoIlo 11sa swceso The American public now has been trained to look for m w e s s , following m c e s s They believe &at success will follow sucoew tn the apace program and they continually q e e t us to demonstrate success and rigfitly so. We e m % &ford r failure. We want that program up there. Whether we get it or aot, really depends on you and your team. Y ~ n assamblere, r inspectors, the whole team, Sum WFS~S a phychological slump that we ree-iee right w . We talked about it yesterday. And I @uppose we'll be tsrlkbg about it today. But slump talk r a y breeds slump talk. All the bad effects, and the insecurity that results in below par . . workmanship, that we can't afford. But we have to think positively now. How do we convince the assembler, and the inspector that he owns that part of the spacecraft he is putting together, that he will inherit that program up there? And how do we create an atmosphere of his recognizing his personal contribation toward that program up there ? Now we cannot inspire people to do specific jobs, on nebulous terms like building a national capability for the exploration of the solar system. We have to translate this to what he is doing toward that capability, and make him a part of it. He won't be doing a better job on the next Apollo flight on a nebulous term. So we have to get smarter in our translation. In 1954 Roger Bannister broke the four minute mile, and that was a pretty big milestone. Before that people didn't think it was possible. But racers didn't stop trying to repeat his performance. On the contrary, many people now have &monstrated that capability. In fact, in a good meet, a s many as four starters have finished in less than four minutes. Wit it really depends on the pacer in the race, how fast the race is going to be. And the excellence of the race depends on the pacer. Now the product of this symposium is to develop a methodology of offering individual challenges. And we've got to betha pacers, because we want that program up there. And tomorrow really depends on today. Thank you for your attention. �DR. JOHN CUNDON Director Reliability and Quality Assurance Office NASA Headquarters Good morning, ladies and gentlemen. I would like to talk to you this morning about the relationship between the l k n m d Flight Awareness Program and NASA's Quality Program. Our Quality Program, as you might surmise, is aimed at ensuring that our aeronautical and spaee hardware perform its intended miseion. However, the realization of this d m is not the sole respomibility of Quality Assurance personnel within NASA, or within our Department of Defense support group, or within the contractor organization. This in no way is to belittle the Quality Assurance people, but rather to emphasize that mission success depends on everyone doing his: o r her job effectively and conscientiously. And certainly it is in this context that the Manned Flight Awareness Program has provided vital support to our Quality Program. The efficieat attainment of quality hardware is dependent upon many factors. However, there are two which I would like to talk about this morning. These a r e wmewhat intangible factors, but nevertheless very important; specifically they are : the management environment relative to quality ;and the motivation of individual workers. Now, motivating the individualworker to eliminate errors from his work, and to constantly guard against carelessness, is one of the very fundamental objectives of the Manned Flight Awareness Program. I think it has done a great job in accomplishing that objective. And certainly those of us in the reliability and quality business in the agency feel that it has provided a vital complement to our function. Motivation, and the factors which influence it, is really a subject for the behavioral scientists, if it is pursued in depth. I won't attempt to pursue it to any degree of depth. However, I think most of us have observed the contrast between the presence and absence of motivation, a s reflected in the behavior of individuals. Let me cite a few examples which, at least in my view, indicate the presence of motivation in an individual. e The person who has an open, creative, and responsive attitude toward his job and his coworkers. a The person who enthusiastically searches for better ways to accomplish things and is not satisfied with the status quo. The person who recognizes the capability and experiences of others and is eager to learn from them. The person who finds a way to get the job done efficiently and effectively, in spite of the constraints and obstacles which may seem insurmountable. The person who unselfishly does more than the minimum required. These, I believe, are charact6ristics of motivated people-the type of people who a r e so vital to the attainment of quality hardware for the success of our space missions. The type of people that we have fortunately had in great numbers on the Apollo Program. The Manned Flight Awareness Program has played a vital role, and will continue to play a vital role, in the areas of comznunications and recognition. These are b o key areas in the field of motivation. We must inform the individual of the importance of his job, and of how his job contributes to some total objectives. And we must recognize the individual who has performed superior or outstanding work. I think recognition in particular if3 very important to the individual who has done a fine job. Again, the Manned Flight Awareness Program has provided us very valuable assisfstace in these areas of communication and recognition. I am sure that those of you in industry who have participated in this program have found this to be a significant adjunct to your motivational efforts. �Of equal i m p ~ ~ Wtomthe efficient aataiamezj of quality hardawe ts th% aavimtu~tent regarbing q d i t y . Ewrp day we we fa& with misinbrprektirmns a d Thi- GEomG atwags Eorn8t eeme ox& the w a y w t U theyyiUA&i&&w WEQYo m might lo@cdy & B @ $ s ~ ~ . must be r n ~ f e &&.the a ~ t h i ~ i 6 a m e f proc~i~ ess & c i d w ~ ,indeed. m e iaftuemed . cost, schedule, a d g a ~ s m w l ~ t m s i M i o nP. some cases, managem& &&$ma m y @w the impress i a that qadi@ was &yen a@pmpri&econ.8:idkrration in the decision process. &iknaa;m@nt th.16 has P r e s p ~ i b i l i t tyo iderm the fm%xnm41 involved, af the reaauns for such kek$ dm&Pms, aS aa e-omant canducive to ;thea t W m n e of q d I Q 12&0m io to be suMlEed. Haw a%enyidf aararst $8- bwd tXws m m plJ n t that manegem@&"is o d y iaterwW in mm&hg a s c M d e , " OP "me d;$ kterested in rwtucing eosts ? I f ''They hatre nu ititereat in q d t y ,tfi.eucef&se, why s h d d I be i a b m a ia the quality of the- hardware ?" "Why sb@ 1 wma aihether this pw~ticular discrepancy, of Ws pmip;ticuWdefioiency is properly recorded, appraprhte tmPfi%%ve action taken, d properly ebsed wt PI1 tYIf mwmgem11 d r r e d t cam, why should I care ? l ~1&*pea ~ ~ fm be , emugh a$ an optimist to belime &at rn e~&iZfmswwe. M to firmly believe that. &la& X lave m e r talked t~ a member af the rnaatqeham who has given me cause to reaeb ~ ~ ~ E E &%o B%Be I emttrzwy. P I Wrfntr the ftmdameau prolpfem is W mwmge-misat opten doas not take the%ine? 'ko p t the word & o m the line, so that p q d e w&erg$aM wby a Wis$ran -8 made which may seem to eaafU&witb appropriate C-mi&ation of the qualfQ of the product. ness within the wgdation; d to e o m m i a t t k when appropriate t$e iwmow h;~r &cigiuns that &act that pmd*t, arjdd 3.W 9:ualtq ~f dhst product. fa thka way, p a % m p t h t m your side and atp b e p i t onthe sMeolgmdq\letlitg. The Mamed Eli@&&s\f-@% cantly help& p u fda P ~ c g r r a miua steme m a t meate this typs of d longer duratioa, Aad it i s allrse obviow, or should be, that our quality reguimmeats forh$rclwwa will be more strfaaFent. Tkw el16 need fer highly mrptivatd psrmmal, ooq3led with 0 BIE~IW& x?lm&prn& €!tivfronmmt for q d i t y , wili 60ntime into this w a d b a d e . Certainly the lkm& FligbG A w m w Ragram wiU oontiaw ta be tt vital 8upprt to those of us in the quality business %mk you very much. . �DR. CHARLES HUGHES Director Industrial Relations and Compensation b r v i o e Texas Instruments, Incorporated After spending anumber of years being concernedwith motivation and participating in some research, and looking at all the work thatts been done in achievement motivation, I sometimes get the feeling that this entire spaceprogram was set up just to prove out the theories. It is an amazing example, even down to the kind of language, terminology, and concepts that have been deveIoped, of the kind of motivation program that can turn on the commitment of people to achieve clearly identified g a d s . I am no6particularly concerned about the reaearch and the conc&ts, only with the engineering d s maas application of these ideas within the business organization. When we look around, we came very quickly to the conclusion that motivation comes from having a job in which the g o d s are excruciatingly clear. So that at m y point in time we know what it is we are expected to a c w q l i s h . This bas got to exist from the top, rigM down to the bottom of the organization. From the chief honcho, right to the little girl o r guy who is asse&?-kblhg the anit. Sothe guy's bossturns out tobe the number-one factor that affects this motivation. Although, interestingly enough, we have found that supervisors themselves do not motivate! It is the content of the job. But the supervisor can arrange condition8 in which the job content has enough motivating factors in it so that we can get the kind of commitment that we need to have. So some of these eonditioas of motivation that supervisors affect can be illustrated by Figure 1. If you look first at the bottom b x , it says, !What we really want to get is human effectiveness. If There a r e some criteria that the organization needs to meet. These a r e some suggestions. For example, in a business, profitable growth, because under the free enterprise system, that is your index of how much contribution you are making to that society. Institutions that act responsibly within tkat society do not have to suffer fram em$ssipe third party intervention, which typically follarr irresponsible behavior bath for corporations a d individuals. And one in which the organisatian itself is renewing, so that when it acoomplishes sr god, it <tan continue to be vital and be alive a d contiaue to grow. Because, if i t is not going to grow, it will go cnrt of business, o r d t should l There &re some human criteria that a r e not particularly different: the entrepreneurial concepts, the idea of the organization is that commitment to the god@ neoessary for that organization to grow and survive; so too, the individual has commitment to the goals for himelf axid whatever kind of work career that he expects Co get; and stn environmentwithin the organization of mutual trust, not trust baaeduponblind faith C O W D I I I O N S SATISFIED BY SUPERVISORS EIP+mQMENT H U M A N EFFECTIVE N t S S CONDIT,ONS ORGANUATEONAL CRlTERlA bnmlknad kll-rdna (a WIG -1bla ritlzmmhlp Rwli&la of ptsntiol 1 FIGURE 1 �but the kind & trua &at somias&am ctizdogue, kmmbg that we know wfiat we are eqw& to accompBsh. Now, these kinds of conditiol.is weald be criteria to determine whether or nat the o ~ ~ a is ~&Yw.tive. o n In the research thae hors bean done w I W wr orgWsation and in a number d p h ~ d we , hvebL.i&d to isolate some of the Ia&oea L&0218 @efdlwnced by management ias order t6 g& &%I eonmttmel42 to tihe success of the o q g m i & ~ ta &i@ z~aev-t ccf the goal. One of them &at 1. u$g$iDy-m&@dfail interpersonal confideace. I s+ Wsg &out the old 1930 type of human rel&lms f~a"Wt collCinue to exist in some ort~;rnts:&%w~. T&.baaic theory of pT%qp?ams. these I consider oXjmieu2-e Tm&a 31"&itl.om The idea behind them tfi &a%you ml-e pe@e into productivity. All p w 8s.w C do 50s Qgme oat how to l w e them enough, i~ the right; w w I am talking about interpersmal conftden~e~ w h W is bamd upon a about people, of which different set of a#-Sans the most impolrtmt ons is high expectations. We will expect excellence, a d we will communicate that l We will not accept aery$ki~gless exceIlence in the work of T&emembers d the organization, whwver they a r e l We will grat~ta freedom to act in pursuit of the goal, a c e %w b w e a char m d e r s W i n g of what those gods are4 We w i l l develop authentic relationships, best m p ~ w s &by candor, a9d very clear, dirsct, blmt ~ ~ ] ~ r n Z t R b ~about t & o n what ts! occurring, We win s b w a p e q x s t for the l i n d i v W , (1) because he i~a peoplea 83iEd @) because he can contribute to the s u c m s of the enterprise We w g i encourage ateam oriehtatios in thebest sense of that concept-a group of people arith a aomman god, who must all .pull together and make the oars bend o r we will not get there ! There mast also be a clear under, kind of interpersonal standing d these ~ o n @ t i m s a confideme. Lt s a p ao@g abut m~thexhood. It says nothing about pledge cards. It says this is the job that we must accsnapliwb. = . Another contlItioa, probably Wre mas%singly important one, is g o d s which are meazxingful to the individual who is expected to accomplish them. To do that, they a r e going;-& have to be understandable to him. He has to see them as desirable. They axe going to have ta be c h a l l e m But, they will have to be seen a s attainable. Gods that a r e too remote, too long a term, too dtstwt, and with too little probability & mccess wfB not motivate. But conversely, gods which a r e too easy, toa close, too simple, do not do it either. The evidence on that seems to be quite clear. Wals that are set high enwgh to have a challenge, with &out an $0 percent probability of s u o e e s for tfie individualal,will get the most motimtion, T h m goals must be mutually supported so that in emcution d his job, he is not in conflbt with another goal af the organization. A conflict that has already been mentioned at least twice this morning is time schedule versus quality. That kind of pd-com2ic?t is going to lead to confusion, and possibly disaster. 80 goals rpust be mutually supportive, SQ &at by doing well on one job, the goals of another job are enhanced. And another goal which seems to be critically i~z~portant (if we can engineer it; it is very difficult) is the idea of an . opportunity for d l members af the organization to influence what those g o d s an?. It does not mean that Ule assembly man on the line is going to tell the program director what. w go&@ the program are. But il dates mean that aay per-, & my level, to the degree &at he or e r b has m uppartwitp to really wderstmd, can make a w e inpuQ ts the plan before the pLm is locked in. This will get a much higher level of commitment t~ execute those goals. + knouler thhg W e%w ts hawe been &menstrated mr d o w again i s tfio idisra that systems should help rathmthm msrtrict %e d i e v e m e n t of the goal. Now peagls, mch a s myw& and twxountaats, a r e point& out as papie who rest&& god achievement tbrwgh t b ~eysbns they &wlQp. These systems a m Qftmsem g j y p w t p@@e as elaborlrte Mickey the c o m p u W full of are &bm'dhHe I%@& pflojwt g d r . %y$wmrshould be u m k a M W 1 e tr, &B guy wrho hais to use meht! (which is not the pmgrammer; it is the guy operating the business). They should be controllable by the w r , so that he am have the information and the resoureem aecewaPy to do h t work. Systems should be adaptable to the situation, rather thsn elegant solutims to queatlana th3 have not been addressed. N w that verybrief ketch af the conditiorrs for motivation seems Co be &B to q p l y at any level of the oqgmization! And those are thin#@that could be under the influawe md control of the mpemisor. But the climate of the organizaticin can make this either real o r can make it a facade ust a big game in which no one d n r i t s that they d y do not agree. Now in the authority-oriented orgmizatian (an organiration that runs on the authority of somebody to tell somebody else what to do), this will work, It has been qttfte wccswful. M a y businesses have been built upon this. Many nations have been hilt upon this. The question is whether it is efficient, a s effective as some other mode8 , Let me point out ut couple of things that give the character of an authority-oriented organization. It is basedupon a theory of social organization snd business organization dttsignE4d to handle the industrial revolution, aver a hundred years ago, by a socio1ogiis.tby the name of Weber He called it bureauc m y , at which time it was a good word. Now it is a four le@r w o d . The basic idea behind bureaucracy i r functional epwialization. See Figure 2. They will put function A under one management team, and h c tion B under another management team, and C and D and so on. And we will build el-aboratelong pyramids of people. The onlyproblern with this is thatyouhave to have a very well defined hierarchy of authority in order to operate that way, because the functions do not have a common objective. They do not have a common god. And so in the authority of an organization, you will find evidence of this as usually expressed by some kind of a tree-shaped organization chart that is extremely valuable 'because it tells you -1 . �who can do what to whom. And whether they have to like it or not1 It is bawd upon the same concept of, llYou will play ebllley ball, and you will enjoy it ! l1 Now b a u m od functional specidisation, planning and eQntPd will have to be kept at a very high level. Responeibilities are, for e q l e , separated throughout the organieation in which qaality is the r e m s i bility d the quality department and everybody understands it &;it way. And the authority for it rests entirely with them, beause it is their godand is not the god of the mst of the people. And we see that planning andcontrol is what manag.ers do. Now if we say that is the excludive right of managers-they will plan and they will control-then there i s the third function, doing. Executing the plan, is a function of the people well down in the arganization. They will find a common phenomenon, that the managers are turned on. They are motivated because they have a fun job. They have a job with motivating content. But, thesy cannot understand why the hell the rest of the people a r e not. So motivation as seen in this concept is the right of someone to tell someone else what to do, the relationship between an hdiviclud and a figure of authority. Going;along with itwill be typically a a y s b n of rights and duties of tfieemployws, sometimes expressed as a mion contract, work rulars, and other kind8 of things. and control those people against that plan." Then sommBese ftw below that is a group of people (typically called labor, wage roll, and other obscenities) inwhich the job is to tldo." But don'tplan. Don't think. Don't control. Don't evaluate. And because they don't have that in their job content, it is much tougher for them to bgeome motivated. And we get a gap. And that gap is a p r d l e m . It is a problemthat needs to be solved, in industry, if we are going to get the kind of human effectiveness that we have the right to expect. The question comes down, "Now how can we design jobs so they can be more meaningful? How can we get more people involved in a process of being concerned a b u t the goals of the organization; being committed to the objective; and havingthose kinds of goalswhich any person can relate their job to ?l1 During the space program, up to this point, that was very, very clear. Anybody could understand the! name of the game, and what that one ultimate goal was, and possibly could relate themselves ts it. Unless the space program develops somathingthat is just a5 clear a s put someone on the moon and bring him back safely within a deade-a v q c l e a r god, anyane can relate to thatunless a new one is developed that is as simple and as clear as that (it is in your brain, you don't have to write it down, you don't have to hang it on the wall for people ta know it), we will suffer a loss of motivation clue to the laok of a clear, meaningful goal. MMIIAQL:MEWT/ LABOR DICHOTOMY AUTHORITY ORIENTED ORGANIZATION "uwn" FIGURE 2 This kind of operation will run, if the management accepts the assumption that it has all of the brains, and what it wants is hired hands. But a8 Drucker pointed out, you cannot hire hands. The whole man comeas with it, and you get this kind of problem (Figure 3). It is a statement of a problem, one that is known in industry quite widely, partioulariy in the typical mmufacturfng organization in which up at the top there is planning and control, organizing, the fun thing;s, the motiwting things. And management says, "Thatls my job, and I do that. l1 We come down lower in the organization andwe get a bunch of people called supervisors. We say, "Here is the plan, now go lead FIGURE 3 In doing research and motivation, there has been material developed over the last ten years that has helped to clarify things about industrial motivation. Up to that point, it was generally done with people in mental institutions or with rats in the laboratory, none of which necessarily predict what people do at work. This research has become, I think, a set of guidelines that can be used to tell management what to do in a number of cases. We can test our plans and assumptions against these, with some confidence. This is based on the work originally done by Frederick Herzberg at Western Reserve, which is now having world wide attention as an industrial motivation con- �cept. What it dm8 is eepwate Wr p h w m e n m tnto two distinct fac-tms. Chie set af h t a r s relate to &he environment im -oh tbe work is dmw. And thep de not motivate at all. If they az% yau unhappy and dissatfsfied, md you have 1.ow m o d . If 6%' a r e g-ood, you me jut s o t didsawifid. There is anather mt of fmhrs d%i&, if present, w01e the motivators. And ift-9 me a ~ t p r e ~YOU t , may not be unhappy, 6& gFaiu are no2 motivated either. You a r e just there, sitt&gamand in a warmbath, ladring at each other' s nayel. And management bus ym that they love you, and p r work is iaapartant, while p u put on left haad door h d a s , day deer day in the automobile plant! Figure 4 is a c w q t d -at k W oE organiaabtion we could have. Lat me just pick on%a oauple of tbine;s, so we can see how we might be able to eagkneer a way, on a mass soalew&h Ohousdra ofpmpL, to g@tsome advaqtages L&nPdivid;e,the orgmis&ios k s d upcln goals, otherwise Imm as projwt management. Lea us organize Q h s ~ t i ? m o r g ~ ~ 1 if~ ~ weu cranpossibly n, figure oat haw to, a% oMwr a matrix ot'gmizatktn, o r on a cmc@ ofpmjecErs, d.Mpl%p s o w t s , and tasks. Because Mthh &e kw&s Porn@-projset mamgemnt concept, the pal@ get a lot ebmr tohome. AnB thm the olrg&izaklon &tart 1.d like ~ a PERT ahart, and we burned the rest of #e onas that looked lke little trees because they do not mpre~entwhat happens. In fact this flow elm& type 0s orgmkatiols tells us how the work moves through it, tells us what the gods a r e at each point, and the time, and the other criteria. If we do that, the planning and control aspects of work get closer to the individual who is going to execute the job. . This big wheel shown in Figure 5 (with a shaft through the middle of it) is an artist's reprasenbtion of how you might look at this motivatiw theory. It says in the outer circle, "There are some needs that people have, and if we do not mabtain them they a r e going to be so unhappy you will not be able to operate. And GOAL ORIENTED ORGANIZATION THE JOB / FIGURE 5 they have ta do with physic&l &@, social ~ e e d s , stabs, orientations, se~urity, and some f m of ecmomic need. So we lave p.bysica.1 working oonditiws. I file cafeteria is bad, people are unhappy. So we spend money on the cafeteria. They ape not now motivated-they are just no longer unhappy with the c d e t e r k , So then it's the parking lot. So you improve the park@@ kt. NQWpeople we not unhappy with the parklot. They a r e still not motivated, Companies can evolve elaborate schemes of air conditioning, the esthetic6 of the buildings. If they don't, they will havedissatisfaction. But they somehow say look how much I love you! Lo& what I give you! How come you are not m5timWP The answer to that is, "Look at what you have asked me to do1 That is what turns me on o r turns me off. '' People have social needs. I$ is nice te have a Ghristmas pwty. If you w e gohg to have a Christmas party for the plant, have a g m d C h r i w s party. But don't expect any motivatia frm itE Matter of fact, you might as well not do it. It does not lead to work performance. However, if p q b expect to have a Christmas party, they would be unbppy if you don't do it. And if you give a good enough one, they will temporarily not be dissatisfied . Status ? Status can cauae us problems. Status helps us get that gap. Status is always there. Some jobs are more important than other jobs. That is a fact of life. It is not necessary to create executive dining rooms, however, to reinforce the fact that we are management. 1t is not necessary to measure your office to see whether it i s m e footwider or narrower than the guy's wPkt door, o r to make sure you have the u W a t e status symbol, a secretary that looks good from the front aad. the back l These things inhibit eonamunication. They cause problems. They also waste assets that could be spent in more meaningful ways. Orientation is necePsary. If people don't know what is going on, they will invent what is going on. So we tell them what is going on. We put our brochures and company rumspapers and tell them how great and �wonderful mdimportant their work and the company's business is to this space program. But that does not motivate them todo their work. There is no evidence that it does. But if they do not h o w those things, they will be confused, disoriented, and possibly dissatisfied. So we can remove dissatisfaction through this. We should do it l We should do a good job of it l But we a r e not getting motivation yet. Security? If we a r e insecure in our work, we are going to be unhappy. So we get absolute security! It does not lead to happfness, as manywives will tell you. Now economics is an interesting one. If we don't get paid enough for what we do (or we think we don't) we a r e going to be unhappy. But, when we a m paid enough for what we do (we have a nice base rate) we a r e temporarily not unhappy. But I asaure you, we shall be unhappy again about our pay. We may have had breakfast this morning, butwe will need to eat again. And regardless of how good the breakfast was, we don'twant another one right after it. And a s Herzberg says there is nofood whichwill keap you from eating. So the stuff in that outer circle is environmental. The environment in which the work is done. Let us make the environment good. If we want to get the things that really make it go, it is in the job. And they are the needs for growth, achievement, responsibility, and recognition. Those are the things which motivate. And they come, not from existing, not from being within the plant1 They come from the job we have asked people to do. Growth means that we can continue to improve our skills. We can learn. We can grow. Responsibility means we know, clearly, that we are responsible for making cePtain kinds of things happen. When we know quite clearly that we have that responsibility to get results, this can motivate. Recognition for doing well oan motivate. Aad achievement turns out to be the strongest motivator of all, in any work group studied, whether it is salesmen, engineers, accountants, or ladies on the assembly line. Achievement, a s all the research that has been done overthe last several years says, isthe strongest motivator of all. And achievement comes from long-term involvement. It comes from a career concern in the way of advancing yourself through the organization, through what you do. And it comes primarily from having goals in the work-and in the organization-which a r e visible to everyone. Which a r e clearly understood! And w h i ~ hare seen a s desirable! And when we achieve those goals it almost becomes its own reward. Figure 5 shows examples of things that can take care of these conditions. For instance, under economic, we give insurance, we give holidays. If we don't do that, we don't keep up with the industry. I think we are going to have dissatisfaction. But having nine holidays, and getting a tenth one, never produced any motivation, only an incredible expense and disruption. And automatic increases (which gives everyone the same raise regardless of their level of performance) takes pay out of the motivator category. If you want to put the economic factors into the motivator category, what we would do is tie it to achievement. And the better the achievement, the better the pay; the poorer the achievement, thepoorer the pay. And for no achievement, there shall be no pay! The thing to do with both the authoritarian managers and the non-performers is to place them with your competition, because they are a drag on the organization and they will create dissatisfaction. We have learned this in our organization the hard way. We continue to recreate these studies and to our amazement find that it holds up most of the time. We give free coffee in the morning and afternoon. It does not have anythiig to do with motivation, but if the coffee isn't any good people a r e going to holler. Once upon a time somebody started giving free doughnuts in the morning. Some companies may think that that motivates! I assure you when thedoughnutmachine would break and you got a brokenore0 instead, you cannot believe the kind of dissatisfaction that occurred. So we stopped all of that, and interestingly enough, there has yet to be the first comment about discontinuing thatpractice. And every company has little peripheral practices which are tradition-posters and signs, slogans, company songs. Maybe it sells insurance, but I don't think it'll get a guy on the moon and back, These things, if they are tradition and they don't disrupt things too much, and they amuse the management, they perhaps should go ahead and do them. But let us not confuse, however, the maintenance of the environment, with the content of the work. That is alI . Motivation is in the work itself. Let me just tell you one quick example, from a company that I once worked for. I went to work and they said, llOkay, you're a hydraulic test inspector. fl Now that sounded like a good quality-assurance type job. They gave me a little bottle of purple dye and a stamp and, hot damn, I'm a hydraulic test inspector. Iwent to work with a guy. I said, "Hi, I'm supposed to work with you, but I didn't bring any tools. " He said, "That's all right. You can use mine." (Because he didn't.) For four months he did nothing. And I said, ''What do I do?" He said, "Pick up this casting. Bolt it down to that jig there, and put the a i r hose on it. Drop it in the sink of water. If it doesn't bubble in 15 minutes it's good. Hitit with your stamp, put it in that box. If it bubbles, it's bad. Put it in that box. I said, "Is that it ?I1 He said, "That's it. " And I kid you not that I made 800 percent of standard the first day. And truly, it was explained to me in the parking lot about that, So the next day I worked very slow the first half of the shift. Did nothing at all the second half of the shift, made 200 percent of standard! I put half on my work sheet. The other guy who did nothing, whose tools Iused, got the other half ! And the department was full of about 60 people who did the same thing. And we never saw the supervisor, except when the shop atewa~dwould call him and explain the benefits of behaving himself. Where's the motivation? 1'11 tell you where it was. It was those ten minutes in the morning and afternoon when the bell would ring and they would play Hillbilly music, and we would toss washers in a hole in a board l That was motivating, Why? Because it was under my control. I planned it. I organized it. I evaluated it. I might even win �60 cents at it. f t was grotrrptlr, s e h i ~ y e m a1 t Rserponsibility and rwognikionwere d l p r e s m t . But 20 mfntttes a day? No, wmething wms m o w , BomeWng was really wrong with an orgmfr;ert;2on&at l$ke that. And I assure y w that .fn my organis&tion we can ffnd the same kind of thing. It is a seversprobl~m that needs to be a&tiwked, when people a m givw-i routine, Mickey Moueel stuptd jobs to do. There is ab@e m&rdiag atAT&Tmade by BobBorrcZ who has work& quite a bit on thie They a@k&a el, ' W t 1 s the best thbg about your job?1' Sht? saysl "The money.I1 may. He says, llAU d&t, w h t v s the worsk thing &boaty a w jab?1T T h e money.w We said, llArmtt you c m W i e w purseif?" f i e says, ltNo, itle the best thing, t3nd the w ~ mtfriag, t because it ties me to this stupid job. She rm&atands the motivation theory. . What we need to do is to fwd same way of making work meanbgfd. That is the d y way we Blre piw to get motivation. Fnxl H a ~ ~ b w gwho , originated this researeh tells a veqy great sQry. He mid a c o m p y call& him up md wys, IWe have a mativation problem and want you to mnne d m and see if you can enrich 6hem j&r a d indm them mare motivating. lt fie went dowa and looked rrnd says, lWell, you have got to ehmge ttie job." T h q said, "There ir ao way we can eb@gethat job.It He says, 7tWe11,then, you have these d t e m t t v e ~ :1. Automata i t b e c a w itfs unfit for hmax c~fStiD%Pti@n; 2. Live with it, a d go ri@t abed kiddfsg M e &at heir work is impoPtant. Or have a morale problem. " They said, "1 thought f01x were aa @pertin motivation. He said, ItYou got an expert's a n m e r I t . There is no way ta mativatew-ith impoverished, trivial kinds of tasks There m a t be meftning in the work. It is a problem, particuZaFIyr ia d w h r @ , to do this. It is not easy. We. have buiIt these hinds of jobs. he unims ha6e rsststerd US. And a y or*zatio-ns are r e d u ~ i q t bcoMerat of the jab to a very narrow band of short oycle, highly rejmatable processes. And as Harry Lminrpan my@, 'When a man asks you for a job, he9s a&hg you to t#ll him who he is. So yyeu give him so~n&ircg atupid to do. I guarantee he wiU behave in a stupid mrtaner We have got to get out of this k W of probl~m. . . Figure 6 puts these Wo thing5 together. That gap that s h m s in between labar. You could put that g q between the top manrpe;emeat the middle management just as well, F a r ezmetlj the s u e kinds af reasons. All namag~bmerrtj~bg,j u ~ tW a u s e they carry that title, am not rnaaniagftd, It depends on whether o r not they inm1ve tn a top d m , caseadd, iterated process af ddithe program, plan, and objectives. Izr-001w~eattrtl the $ m i n g procress, nst just W i n g w h k the p b is, but havingk&mdmeate the plan embe very pwerfd am3cam ge& &high degree of commitment to mhieve. achievement motfvation comes from gads, and knw&g what the pals are. Comes froen invo1vement and planning! Bnd that seems to be the mewer. The eqgbeeririg Of this prtxess, 08 a mass organie a t i d &, wili be vite difficult to achieve in iW. W setkiag gays that any job ought ta have plaxmbg itr.it*dobg init* contr~llw o r evaluating. And wbtsver happeaad Q baderrhip? Leadership of the &aimern is becoming lest3 a c ~ e p b b l e . m e r h i p in *e ww m a p a -a w h t she guy above does is involve the p q l e below him in planning. Thatre an operational definition of leadership. It seems to have nokhirg ta do writB p e r d i t y characterietios. It s-ly has to do with high expectations of people. We should think well enough of what they can do for the organization thatwe a r e going to involve them a8 znnch aswe can. T h p would have a series of cirales going &own through the organization, just a s f a r a s we ern engineer it. So &at every job has s e e motiv&ing element, Werwirse, we will just have to tolerate the morale problem, o r an incredibly large cost. me Figure 7 contains some Meas taken out of a book by J o b Gtwcber caIl& W Rmewaf, that I think do relate tothis b a r b s s of e b y b g dive and k q b g the orgaaizatlon gruwing Particularly with the kinds of experiences that mmy people have been involved in the space program 4m r d y must be experiencing at this time. The first is an effective program for the recruitment and development of Went. That goes without saying. . We &odd not acegit 1~8s than w e l t e n c e in the people we bring in, if we have any way of doing it. Swahdly, provide a haepitable envtmnnwnt. That s a p , "Take good a m of the maintenance factors anb then ehu$up about it. Third, prmide an adequate ayetern of iaternal, c ~ m u n i o a k i m laot , in one direction through & diefectric layer of management, but one tb$gem both ways, with the same degree sf speed and accuracy. A tough problem. It flms down so easily, and it does not come back. Fluid internal structure which says orjgmiaartiaal s h c k m e i.s a dqmmdmt v r u l d e . Do not fitpsujgets into the current hmeauoratlc orgmimtian. Change the arganiaatisn any time the godis change. Watah out for becombg a priaomr of your own procedures. That has happaad to all af us. Qnce upon a time I heard of a man who wnt in rtn expense account. ft had rubber BoQts m it-eight dollars. They sent it back ta him saytag the company d-It buy r u w r boots, that's your e x p n m . The thing e r n e right bisck. %matotd, and a note, "Thebaob are in there. T q and find them. I dm heard af an enginemring miwager m e time wha famd an edict whioh said, "Thou s W t n o t buy anymore mimossopes. He says, got to have that ]artiaular microscope, I cannot reach my project ~ d Management ~ . said, ~ "You can'tkve themicroscqe So he filled out @purchase requisition, listed all of the parts, rand the last line said, wPlwacaassemble M o r e delivery. It Now, that is ome way ta y w r creativity. It might be better that it went into the project. ." �THE SELF-RENEWING ORGANIZATION I U I A ( l m M V E C I W U I I I 1 0 1 m r ~ MINT AND I R WT A W rnnmumrn IOI TIE CIOV~DC.A IIOWABU IW#V(DIUL An L D E P U A n UIIO* s v I D 1 w nllcmuL -N+ YUWU)(t A R U l O IKmWLL s IUI w u a IOI -nu4 slnwmmc nr rrroc~uDV wwsv WLll.EcoyECI~OF~I*OCMIIID nu POR Eomrmm rm rmco INTIRUTS 1W1TUQWWWIvUTIWM*IIHlJI~ FIGURE 6 V e W Werests do get created, and they get very probative. M they w e very wasteful of resources. Particularly, human resources. The orgmBation e W d be interested in what it is goiag b became-not what it has been. Never mind d t your p a l wm last year. History is fine, but Gannet do p b n i n g b& on extrapolation from tie p t . Wtth atrowgic planning (glflmn@ with gods) the qaenc0ioa is, where do you want to be 7 Now, let ras work bmWa&s, through our ptoinning cycle, to m e W ~ W W eP rerally get there o r not. T h t ie the way yew f U auk whether the gods are meaningful. N<rt b w i s e w g osmlay a i~txaigghtline ac~o6lcrthe chart a d make it go to to p&t, But, where do we really n d m d w m t tobe? ?eatbe chslle~lgeisto engineer r way of gettfng tbre. Does the organization have g o d s &at a r e visible, desirable, and challenging to ita members 3 FIGURE 7 In s u a m w y we are not going to motivate anybody by loving them with fringe benefits, programs of faked superficial involvement, p l d g e cards, and other obe~o1et.emanipdations. We have got to have good working conditions. Have a good environment for people to work in and do their job. But these a r e not going to motivate. The only thing that is going to rnotivsate is things &tot we ask them to do. Whenever we have a motivation problem, we should & say, "1 wonder what the hell is wrong with that jguy?" A better question is, "I wonder what is wrong with that guy1$ jab?" Because, I assure you, when he i s out playing golf o r bowling, he i n probably so motivated you wouldn't recognize him. But, under those conditions, he has significant opportunities for motivation. If we would engineer that kind of process at work, then we could achieve our organizational goals. Wlt we must take the time and care to have the goals well understood, clear, constantly visible, with realtime feedback through true involvement in the goal setting process. �INNOVATIONS IN MOTIVATION MODERATOR PANEL MEMBERS EUGENE E. HORTON JOHN WILLMOTT Chief Manned Flight Awareness Office Manned Spacecraft Center IBM TOM SCOTT The Boeing Company DWAYNEGRAY North American Rockwell TONY TOCCO TRW HAROLDDURFEE Grurnman Aerospace Corporation GORDON MACKE McDonnell Douglas Astronautics Company ��It was pspnted oink by Seu yesterday, and several af MIF mtamgff~eWt,t-B$:tface-ta-face colifmnnication S s probably the best tool thatwe will ever come up with. So, wtfb &at background, I would like to start by b-tng Bur panel: From my right, John Wilhott of IBM: Torn Eic& representing Boeing Cornpimy, Dwaytxe Gray of North American-Rockwell ; Tony Tmoo, TRW System, Redondo Beach; Harold W e e , Ortfi~wnanAerospaoe Corporation; and, fid l y , G o ~ d 6Ma&e ~ of McDonneU-muglas Astron u t i e s Ccmpmy. WouM &nv of vou like to start thing8 off ? Tom Scott Stmethe panel is discussing innovations, I have found imovatione tobe very effective in some, programs for which 1 have BsLd mqxmsibility. Effective both from the viewpoimt d getting the employee participation; and effective from the viewpoiat of getting the interest of management. It may be more meaningful, though, if I start wt with some of the results we have achieved tbrough innovations of well-established programs. First, in a 1400 man organization, well run, the best record of employee partkipation of any organization waa in Baeiag. They came in with some innovatiow at the direction of the Vice President. And we raised the &tal eost savings from $1,500,000 to $3,500,000 in a p a r i dof one ymr. Dr rather, we changed in ten weeke to that rate, and it was actually accomplished in a y a w , In mother 16,000 man organization, we came up with a very simple innovation that you may w w t to me. last year we had a total eost savings of 42 million dollars, 74 percent over our goal. I attribute the whole thing to one bit of innovation. I have foIls3lued 10 precepts, 10 ideas in motivation. One of them i%innovation itself. But I'd like to recite the ten principles for you. Ftr.st, anybody cosneot8d wlth the program from management on down, must distinguish the difference between pep talks, inspiration, and true motivation. Pep talks can create enthusiam, Inspiration can create de&ermhation. But motivation affwts an attitude change. And that is the thing we must get. dmotivation results in the employee's feeling a proprietary inten=& in the company. A rssponsi$ili%~as a member of f h team, and dedication te ul:tiIrr.ate mission sucGess. Thin& motrvatioa result8 in a permanent and sustainbg effort towards the a t t a h e n t of management gera2s by &e employee, Inspiration and pep talk? The results last a s long as you apply the pressure, and them they drop off. Fourth, moti&ion can be measured to €he extent the employees contribute ideas to management. Many peo3JLsdonftknow how to measure (especially mmagemeat people) md don't understand thatmotivation can be measured. It is measured to the extent that employms cantribute ideas. the extent of the contributions a r e ultimately measured in dollars of cost savings or cost a w o i h e , They are inseparable. east sauinge,achievement reflect the degree af *Owem management shows for motivational pro- m, m, grams. If you show mmagement that they a r e saving money, they get concerned with motivation. And it makes your life easier. Seven$h, a motivatianprogram yielding a million dollar c08t sa-s o r cost a m i d a c e , should have the same level Elf management support and interest as a $20 million contraact in which they a r e anticipating a million dollar profit. I have come up with a theorem of my own on motivation. I say that the motivational results vary directly as the level of management support, times the square of the talented insight of the motivation manager, divided by the physical results of the motlvatim effort. And by the physical results I mean that you divide by the number of charts, posters, and everything else, There is an old Germanproverb that states that the better the carpenter the fewer the chips1 Eighthi the same is true with employee motivational programs. The fewer evidences of motivation effort that the employee discovsrs, the better your motivation effort. The best program in the world would be one that is not a program-the type of feeling you get in your family. Now comes the key to the whole thing that attracts the interest of management. Ninth the program results, measured in dollar cost savings, can be permanently increased at least 100percent, 10weeks after you energetically integrate the individual motivation of employee participation in cost improvement programs. When you eliminate the coxapetition W e e n programs, get them working together, in a period of loweeks you canincrease your results 100 percent. It is just as easy to increase them 100percent a s it is 10 percent o r 5 percent. And you can go beyond 100 percent, if you want. Tenth, motivation appeals must be on the level of interest, and level of comprehension of the employee group to whom it is addressed. Too many programs a r e real fancy programs intended to get the aesthetic approval of management, rather than being a Lawrence Welk type of program that appeals to the employee. Now I think that if you integrate your efforts, and post your results to management intermsof dollar savings, you will get their support, and with the integrated effort accomplish an increased employee participation at the same time. -9 - Mr. Horton: Thank you, Tom. Dwayne, do you have any commentc from North American ? Mr. Gray Well, Gene, I guess I have a little different philosophj in regards to this thing called motivation than a lot of people have. I don't think that it is the tools of the trade that we use. Admittedly, when they a r e used discreetly, I think they can help an awful lot. But I think that there is one thing that rnustbe in any effort, whether o r not we are speaking of a formal motivation program or any type of goal to be obtained, and that is the proper attitude. And I think that this attitude, too many times aims at the employee, at the working level. I think that if we would change our phil~sophj �here a little, and we wouU start s ards a t the highest level of gram aimed at the p e r s o d bstaa&ax$sof &%memhers of management, down t&mugh &% chain of command, I don1t think, we wodd hrv% -to &out o w people too much, other than @vbgh m tfke guidame. Because they will work to t h p ~ o r s -sz ~ that we set. I tbnlr, wke&ex WE use the other twb o r not, if we contin- b maintain and keep these standards in front of a r people, m d then recognize f ~ r&acornthem very meaningeuUy glrd ~ i n ~ e r e l ytheir plishments, whatever t h y &&& t o w d the &andards, I think that will give us m m motivation than all the posters aand awspper dfppinger we a= hang up, And that is p r h e e l y what we a r e basing our motivation effort on a t $he present time in the Space Division. Our stadardh) have been set by the President of Space Division, & all the people a r e aware of &is. It is carried down through the chain of command, and we a r e plotting courses toward achievingthese goals, And we don't have to just speak in terms of e r r o r d r e e performance. Ifowever, we have, a s Mr. Bergen and several of the othw speakers pointed out y e s t d a y , cost axid eoheaules. But whea we start aiming our differeat p m g r m s at W s e different goals, when we e;st to a certain level, we have to qecify exmtly what we m e m and w b t we want from oar people in order to obtain thew g o d . Too mmy times we speak of motiva,tiomin geaeralities And too many timer we fastrata not only the peoplq but supecrisisn. If you are t&fng &wt preveding defects, then you have to to1 them that is what you want them to strive for. H you are talking a b u t saving dollars, you aim your pr-hW;n at that, but you have to be speeifio I we too many rncttivation programs where people tfiidz they can just hang up the word motivation, a d that is going; to take care of all the problems. Well, it's not. And I think that the way the staulms are a& by mamgement, at the highest levels, and communicated down Ehrmp;h the ranks is what is going to determine the success of the program. . . Mr. Macke: Could I get back to the original statement of what we are going to take back with us, if I might 3 I think this seminar is the finest seminar I have aver attended, and I have been to all of them, as you knaw, Gene. And I have found this one to be the most enlightening and the most productive. What I will take back from this seminar is something I hsrd never beea able to take back before. And that is fine messwes from our great wM* father who sat up here yeabrday, and the hlMA great whtb fathers who sat up here yesterday. I aam goingto take all those meaeiages back to our people. They wee to the point. They were objective. I think I m d d sit hem and talk about what we have done with VIP at McBonnell-Dougla~. But I see very mimy fi9nilia.z fmes out there. I think yau all knuw we have a s a c ~ ~ d u l p r o g r a mIf. any of you are not familiar with it, you can write to me at Huntington maah a . we will send you all the brochure material necessary. 1&iak what is important t-y is to talk about what we are wing to do with t;odq7s~liaate-with cutbacks, critical skill loss, ad ma far*. It&&& the message from both industry .dtnd MA&%. pe~&rdaygpve us m e of the mewem. I think p r a b & l ~&& m,W 5namrtan-t thing is for fellows like ousmfws, m the oWd bme, and wr com.terg8TtS throughout. the rest d indwtzy to ktmp ourthinking positive-go w d and generate a gookt olimat&. I have been e q m s d to same of my 00-h* l across the nation, and some of my own pmpZe b k home that have a defeatist attitude. How in the hell are we going to motivate people, thou-& s f them, if we go arownd with a long face. So I think the first objective-to meet tke demanding conditions of the present climate-is for us to start thinking pwikive and to show that we are thinking positive. I d s o think that I wodd like at this time to thank you, Gene, axid dl your coqtexparts, for these excellent presenhticms, and for the type and caliber of persomel who were on this rtatzd. And I would like to for a round of applause to show appreciation to our Ivbumed Flight Awareness counterparts and thank them for the exc8llentpr;mel they designed yesterday. I havebefare me reams ofpaper that say what we a r e going to do, a d I am not going to d m l l on the details, just some of the highlights. We have had a program. We a r e looking; at our programs at MrtDonnell-Douglas and that is quite a bit of ioeking, I'll just pick out a cmple of the highlights. We are guing to remtivate, witfamore emphasis, w w d o r awarenew programp both the mainline a d workshop. We have already developed an i n t e d awareness prop;ram which will get the message and cammunieation down to the grassroots lmal, from the b p down, on the responsibilities of the people, their part of the fob, This has been going on constantly. But we are going to do it in a clarsmom manner until all, everybody on Saturn and Apollo rnrrinline anB workshop, has gone through this. We are going to train their supervisors, because when they hear it from their supervisor, this is more important to them. It's long lasting, that's one thing. The other thing, of course, is the community-the wives at home. I don't think anybody tonchd on that yet. They are going through these pangs of insecurity. More $0 t k a the husbands who are still working. Sa we hatre devised a program to get the message of motivation, morale, and the future of the space industry, through radio statim communication-free time incidentally. And our first attempt-and it's only pham one, subject to be changed each time-was abaut three weeks ago. We negotiaw with radio station KPOL, th r e d quality standard AM/FM in Orange County, &at has &out a 200 mile transmitting range. Within that 20Q miles is of course McDonnell-Douglas, and many of our competitors and many of our team components. So we intend with this program, which will go on for the rest of the year, to get the message out to the community and the housewives. I would like to play the taped message just ts show them what is happening. Before the tape, one grand and glorious thing that happened yesterday is that Mr. Wallerburg, our president, said that he felt the greatest tool of motivation was getting out there in the shop. And believe me, starting Monday morning he had better get himself a new pair �be^, Iwmme be is e o m m i t W m ; but, he is right. Bnd many atber feUms said this yesterday. AMtW's~tk~*zfiaethipg. I t h i n k a l l d w h e r e e a t Wits fathers should k damn grateful &at were her* y t a s t ~ y ,because b y axe committed d m . It mt@t help with the budget sltuatton, gentlemen. So if we a d d have the tape now. d dpollo estromub had barely returned from the moon when ht~ricmulrabegan to a&, 'Tf we a n reach the mom, why can% we settle some of our lesser problems here on earth?" Columnists and commentators pointed to tfre cdlbaeks in the automobik indastry Qf d&&ive ears, short lived applianc~s, and poor quality smtrol in general, aug:p@t;Bdthat perhaps other IndustlPies might learn from the wrospwe industry, how to do it right the first time. The Pentagon, NWA, the Congress, and evan the President had ganged up on contraci tors hthe apace program, and demanded that they do somethinga b t quality control-that was in 1964. In 1969 we reached the moon. The M ~ l k ~ e l l Dazrglas Curp~rrttioareceived last year's award from the .Pmtagon for oatsbrtnding results in the program designed to cut costs m d defects. I tous& the Bmta Mmica p l a t and talked to the people involved in the program, and must admit ttidlt 3 was not only ifilp~e8sedbut overwhelmed. MeDomell-Douglas calls its effort the VIP program. The vice president and gemral manager of the western atvldm d McDamell-Douglast aaFkronautiee division, Jack Logan, explained to me how it works. The b&c grugram that w w designed and developed by Charlie Able, who fs, the chief executive officer d & m u - D o u g l w Astronmtbs, was really d w i m d on a rather simple philosophy. Number we, €hepeople a r e importmt to the tow 'mmagement objectives and that you had to conv&ee them dhert they' are important; and that you have to show vw;r simsre rtppreciakion-for them; and show them &at it does result in benefits to them, to the camp a g ~& Da & country. Peopb tehd to forget in the ratbe af by-to-day &fort, that every job that theydo i e w r y i m ~ o r t & ~We t . in the middle mana g & d , Pn &e G e r management levels have dwlgned a program that contimourlly m i n d s them p post ere, tlsmugh meetings, through awards b t they truly a r e hportasst. And this thing sort ~f works f r ~ m the grassroots on up. Strangely emaugb it cloe~sn'tindude money. But m w t of us think of rnaaey :y being the ultimate reward. TVs more o r less m-ecognition. Is it true that recognition works better than money in this partiouleur i w t a m e ? Mr. Logan: Well, I muid aay this, r ~ ~ p i t i o n w o rgenerally ks a s well a s money. Wow of course we have our etmdtrrd employee suggestion system, in which any employee is eligible to make svggestiorrs towards improvement of the product or reduction of the cost sf the praduct. Aad we do hand out, regularly, mWttur51sl m s d morrey m is result of these suggestions. Hawever, the r d grassroots solution to the psbblem, Ray, in our opinion, is that 9%pement of the people, o r maybe 99.9 percent of the w a t to do the right job, as long as you convince them that top management is truly q p m i a t i v e of the individual effurts. And the ~ w d ofs varims~kinds,a simpk plaque in some eases. Remads b e l m intrinsic value, such a s pen trnd aetar, cigarette lighters, these kinds of things, are just a symbol of the appreciation of mmagemenit. It i~ amaeing haw people react to them. It is really not the thing that you handout $thatis valuable. It is the fact that top management has taken the time to say thanks for a job well done. (Announcer) Would you go so far out on the limb to say that this approach would work in most any industry? Mr. Lagan: Oh, I don't doubt it. I think it's inherent in human w b r e that we all like to be appreciated, and that we a l l will do a better job if the bose will come around and pat us on the back once in a while. ( h m cer) Well, thatvs the magic ingredient, according to But it takes a lot of effort. The VIP Jack Log-. program is everywhwe in evidence at McDomellDouglas plants-goal charts, progrese charts, awards to the group which won last week, and a photsgraph of the group with that individual. One group of VIP winners was flown to Cape Kennedy to watch the Apollo 11 launch while another group newt to Houston to help welcome the astronauts back. The company wants its employees to keep constantly alert to opportunities to improve efficiency in the product. And the company in turn keeps constantly alert to ways to reward these alert employees. The real payoff, of course, is in more Oovernrnentcontracts, whichmeans more prof$t for the company, and more work and more pay for the employees. The Government demanded quality control on the space program. If the general public were half a s fussy about the things we buy, we might be able to encourage the same practice in other industry. �Mr. Horton: What kind of respctnse h v e yau g&m to that. .. Tremendous. CBf mr#e, I ifid a little PR work in W this w w gobg to letting evePybsdy ~ ~ C Eindisapee?kEy be on at 7: 30 on s Sunday night, two weske ago. So I imagiae we had a tsem-s d i m m , and I bet Ulrtt P d w t b 8 n ' t go by tias%smx&ody doom't come by and say, r t M t s a n i e e t l t b . W w i f s d I I i - e d to it, I f &Lad t W aork of Urfng. 80 we &re $a&' on with t h t type d pregnm, espes~idly the c d t i o n s of M a y . Nat a b ~ y the s sme r& &%tion. We have conttwted a few ethers, and t$ew t:@ows are middle of thg Poad%lS. %?eiavert af p t the baGiEgmwd Oil these Mlm%.We can't hawe a lJWt o r a rightist doing this soTt df IMng. Wetm got to hame a middle of the road c o r m m m ~ t om~a%b Wng. So it isworking for us. The ~ e d t a am fine. En them tims, I think it is good to get &b Wea ta toe humwife, 4the general public. I thbk we are.going to accomplish a hell of a lot here. attack our probhmbe ia our ownfashion in dediag with suppliers antP In trying to get message acrm to them that we are g f a m with hum;zn lives. You can't Wtl8 far mything bss thm the very be*. We have yet ta really twist aii arm. W e h v e always gone in as the gue& of the supplief, Wme af this sending a TWX, "I'll Be there an e~ and so, and please try to heve somany bodies. " And this method of going in as a guest has worked wonders for us, evea when there It has enabled us to are same serious pr&l-s. es-lish a rapportwith them. And I think the answer to dealing with your t4rrpplier is simply what was said at the very begbning;, tFCommunieatewith them. I f OW I go k k to an Letdent that I came acroas right after I came onWard this program, right #ter the fire. I went i n t ~a mpp1ierta plant, cmd I came amass a gwdnaotherly type on the assembly line making little boggons, smarts, an4 gizmos. When 1 came around and looked over her shaulder , she s d d , I f You know, Ifvs hen working an this program for 5 years, and this ia the first time anyane has bothered to tell me whare #is thing is going." I have never forgotten that. And I #ink that has sort of shaped all of our efforts. The people wwho w e working on the sub~omponents that go into the b k k boxes that we take and put in our segment of fie Saturn-that the rest of you assemble into the various other stages-have a right Mr. Horton: to lanow what the heck is going an. So we have geared our program to bringing them up-aX,-date information, Before we WEBcpie~ttolafl$zm the audience, I would a s accurate as possible, as soon as pos~ible. In fact, like to swing the dUcus&oa, just for r moment, to I put together what Mitch Sharp has come to call a subcontractor awl v d r r q p l i e r relations. I think Dog and Pony Show. We have been back and forth this is a fairly reprasmEltave group of some of our acrosr thecountry, ishundred$ ~fpresentations at dl major mntractare. Btu W s a , in ~p~alki32$ to us of our major suppliers. And it has paid off for us. It yestemby, poMed 94t W it ibl ~ g r y e@syfor Borneis w r y difficult to measure. But thefeedback we get one who ie, w&ae; en a he& shielA, a d boltbg it from the mppliers management indicates that the mesinto plaae, tQ W ~ t ~ Butait ia ~another , kind d sageis getting across. I had a very interesting bit problem whm yoar have a man w b i s makingtrfovntain of feedback the other day. I wars talking to one of the pen for which he c%m~t see the @pw application, sxeeutives of one of our supplier8 b d he said, You particularly if it it4 an off the ahelf itam. I would know you r e d l y scored with us. He wid, "It got so like to direet this questim to you, John, and also to bad, that we had to stop the non-Saturn people from Tony. 'What do you think carn be done to improve coming to your sessions. If He said, IWe build things the mitxtione, th8t.t yau b e in your plants with your to NASA speeiffeations a d we build things to other subccrntractors andvendors, to t e e them more swam of the efforts and the objsctivcs of the l h m e d Flight W C . The people working on Ure nQn-NBSA hardware would come tnto one of our sessions andgo back Awarsnase Propara ?If f thiak in am#we~iaQ; tUs, you to the floor and raise dl manner of hell with the manmight describe &I us ecmsd the c ~ m u n t c s t i o n l ~ ~ agement. How came we are not building it this way? o r techniques thak a r e employed in your campay a t How come we are doing it this lousy way?" That is this time. the first real concrete evidence that we had down on the floor, that themeasage was getting across in a lasting manner. Now, we like to gage the effectiveMr. Willmott: ness of our supplier visitrs on what we hear from the floor, not what management tells you. Because manWe have for tt#,laat several ysars a t ElM b m engaged agement is dl too pae-particularly if they have a in s very mtive 1upp1iw 8~8r-s effort. AS one contract wtth you-to pat you on the back. "Great time we called them vewb~ai,and wmewhere along job. Come back any time you want to." But it is the the b e it bqgm k?s W in my omw. B e c a u a when I think of @fa word vendor, I ti&& of eornepne ~)8~3afng little comments you get from the people on the floor that make the difference. dong with a push cart of W-doffss or mmetbing of this sort. We ditwtded efiat we would dignify it somewhat and call thm suppliers, So gap, dl our ruppliers Now, we have a program of visiting all of our critiseem to **fa@ this. cality 1suppliers every 6 months, and our criticality 2 suppliers and selectad criticality 3 mppliers once a year. And we hkve managed to adhere to this rather The IBM Corp9mtL~nwo&r ia a ntrmber of different rigorous schedule, and there's only one person in the ways, and because we do wcwk in different ways, and program. And this has worked very very well. But a r e subject to some dmerent restFtctions , we kave to . �facing tBe inbvitabh ~Utb%etOkbth$t 3 are now we ctming, as the remll. of h v h g reached the moon. Ar@ sa, &my cJ;f our i ~ ~ 1 p ~ 1 iae rms aehuttbg Bow23 their &tarn efforts. A d thb beoomm a @l~zn. I bye beem to @ever&phase-out banquets, aoma of those aaarful godbye $ession~1,W pe-qdecmm up toyou and ss$ you, "Why is it Thia is a very tocxgb thing to m e r . You don't wsnt to tdk a b u t 1%but p u have to, What we a r e p tu do is, iii same inBttanoes, go badr to our major suppliers, the iswppliers that we kmm we will be umhg if followon b h s r ck,a~coma-&o ha& tothem on a reductxl e&edatle--to kaep thgm tnfomed a# ts what is going m in the ~ e p We m~ e tga out . dprtxnise them businass, Our procurexmnt p e q l e would olimb dl over as fur that, But, we can keep upen the lines of c.ornmwWia. We ase dm plmaiag ta make a v a i k b l b m i n g ; quatiti- of the aw8tPmess matee r f d dealing wi%hthe follow-on Apdlo snissioas, amiW1t3 our enytpliers fw distribution i n - h m . I &ti& the imprtmt thing that we have f w d at IBM is &at you caa open up a good chamel of c o m u n i cation with pur aup&ere. Them if you do get a pmblerm, ytau cm in Wt it in a mature, gentlemanly fashioa wbthwt beating each other m r the b e d . 'We want to keep t h s s channels of commuaica-eimrs Bpen. t a t . I have the Ieermg that Dr. Hughes said it dl. There were w many things that I had in my mind, I said, llThat is what I would like to gay. " And he said them. But I w d d like to h e one other point, and tha0 i s , "It is important to tell the man he has a job with god@ Thdtt today, here and now, there is a more important concern and that is about having a job with gods. ." I think we are living in somewhat a state of euphoria alter the ecuemes d Apollo 11. And I also think that maybe we a r e whistlhg in the dark about how things are and bow we can w i l y make this transition from Apollo 11 to A p l b 13, and beyond. I think that it is human to put .vested personel interest, the basic emotions, the basic drives before national interest. And, I think this a fact of life. This is something we are going to have to face. Now, I would agree that this has been very enlightening for us. Certainly, it has be0n enlightening for me to hear s m e of the things that have been reported here today, and yesterday, about hon-goiag program plms. But, I think we have to ask o w e l v ~the s same question that the drunk would a& lean* up against the lamp post, "Are we here for enlightenment or support ?" Mr. Durfee: Mr. Hartan: Tony, would you like to comment on this, o r speak to a a o t b r poht . Mr. Tocco: Well, let me comment on this one first. We have had limited experience with the program as itaEfects our suppliers. Rowever, this experience has included factoring in our quality data system into the overall supplier p r o g r m f o r zero defects and Manned Flight Awareness. I think that the point to be made here is that we have to look at all of these things that we do, in the way of motivation, quality, and reliability, as interdependent activities, rather than monolithic efforts in our company. Because, if they work together a s a kind of research network, the results seem to have a much larger payoff. NOW,mother thing we have been doing for some time is develop a Vendor Rating System. Based on this Vendor Rating System we will shortly have recognition d certain selected suppliers. We went through the gambit of calling them vendors, and then suppliers. And thatworked so well that we now call them speciality suppliers. That works even better. But, we do have a kind of network of things that we do that a r e aimed at our subcontraotors to intensify their awareness of their role in helping us produce a quality product, but not only a quality product, but a product on scheduLe, and a t the lowest overall cost. And again, this means it has to be sort of a consortium of activities. Because you can't gat at this total goal without doing other things besides motivating by posters, o r by occasional visits. The element of communication is very impor- I certainly can't add much if anything to all the preceding comments this morning. I think that the profundity that might tie afew things together is a thought of mine-when you have a dozen people, you have a dozen different personal reactions to adiff erent situation. I think that one of the main things to keep in mind in motivating our people is the fact that Joe likes his silver Snoopy. He is extremely proud of it. All of the people are. Joe may be a little more proud of it. Maybe express a little more personel appreciation than the next guy. We, in Grumman, t r y to diversify the motivation of our people. We do try to assist our management in carrying out the precepts that Dr. Hughes mentioned this morning, and the other speakers talked about earlier. At the same time, our contract with the members of the NASA team, that deal in motivation provides us with a gimmickery the importance of which mustnot be minimized. But, at the same time, we must be careful that we don't concentrate on it to the exclusion of recognizing what lies in the motivation coming from adult, mature, intelligent treatment by our management. We hold our Snoopy presentations regularly. Our management gets on the floor regularly. Our management pats the men on the back regularly. We think that ours is abalancedprogram. It does incorporate, to a reasonable degree, all of the elements that have been discussed here. I'm proud of this. We think that in this way, our people who appreciate the gimmickery, feel that they are recognized. I feel that, with the other approaches, the serious engineer feels that his work is recognized, because his boss and the bosses over him express this recognition. �Mr. Gray: I would liketo elahorate ozr cmepoWthat Tonybrougbt up. I think W s is a g d time1 a d a goad envirmment for us dl to kind ~f sbphwk zLnd We a look at whatwe aredotrig in: our moti~o%tm program. Z Wak for the pa& few p r m WB hoe dl been more o r less driving forwakdgretty forcefully and awfully hard with a lot of new idsnew cancepts and new etppreaches. And, I thirnlc fiat wmetimers if we lsok deep enough, we will find certain Uliags that caa be just a s demotivatdng tct our p e q l e , as they a m motivating. I think t h i ~ b a gsod time to ~eev-aliltate what wefre doisg in th%@ field, b d e m r e that We weed these things oat a d keep it on the posiMve side. Mr. Horton: Before we go into quwth>ns f m m the audience, I would like to see a shm bf WPPB f tho%eof ysu who represent organizations that, at %birr time, have something o r someone that you could identify a s the Mgnned Flight Awareness element within yous organization. That is rather impressive to me. I don't know how many of you a r e representing the Ekpartglmt of Defense, industrg or otber centers, but if we candouble this number by the wlrt mesting of this sort, I think we should have a very meirningfuf awareaess effort. Well, a t this time, I m l d like to have the mikes move to those who have questions. I would like to ask a weetkon. With respect to this meeting again, I think that a meeting b to have a product to be successful. I would like to rase a question, 'What is th% p d u a t of this meeting?" Is it a one-event kind of thinp; where we have met, we havediscussed, a d we will go away, md take n o w except some information with us, that may o r may not be worthwhile in an implementing standpoint? Or, can we go away from this me&% with an action planned? Something that we can work on, so that this will be the first st= uf a continuing proceas to make the iVbmwd FlQht Awareness Prugmn a living program in all c d our orgmizatiom. And if we can agree an the latter being the h t k r approach, then how do we do about doing that? This has been my first opportunity to interfwe with my counterparts. And t b t is re-grdWle, beetruse in this kind of situation, I h v e not been able to talc43 advantage of the lessons l e a n 4 in other amas, and eome sf the innovations that have come about in other companies and other ~gaakak.ions.So we need totalk to each other more. Wtt, there has to be a mechanism that provides the opportunity to do this. It can't be a random thbg. Maybe we need to set ~p some task forces o r some study g r o u p , but a t least some planned approach to make this firart step meaningful in improving the overall performanos on Manned Flight Awarenerss, so that the end objectives of the customer and ourselves can be met, and, a s I say, in a verydiffioultenvironment, One of the cqtains of indrrstry who spoke yesterday, is laying offpeople at the rate of about 1000 a month. In this enviranment, it is difficult to c0nvinc.e the employees of the objective of Zero Defects or Manned F l i a t Awareness. The individual is not a s much concerned, if you will, with Apollo 12 as he is with October 12. Will he have a job on that day, when Re M a the etrearn that is going out the gate and handing in their badges every day? Mow, this is a nervous environment we are in. And I think it is a shame to gloss over the realities of it. I don't think that we can appeal to the American worker by saying, 'Well, the American worker is dedicated to craftsrnen~hip.~'This is not true inmany, many instances. Our consumer products I think abundwtly attestto the fact that pride in workmenship has in many areas disappeared. So perhaps I am asking a psychotic question here. Where do we go from here in a very difficult enviro m e n t where funding has been cut. In the letter of imitation I received from Dr. Gilruth, it was stated that there is concern about a degradation of quality, and the personal eeal to excel in this program on irrdiviciual jobs. It is not going to be easy to get that answer. But I think we have to design a blueprint for some action, other than just a discourse of the problem and an illumination of the future plan of NASA. What I asking for here is some effort toward that objective of admitting a team that will make this a going program in the months and years ahead-recognizing the tremendous problems that we face. �MANNED FLIGHT AWARENESS THEMES AND PROGRAM CONTINUITY �CENTRAL THEMES AND AWARDS A 1 CHOP Headquarters West Coast Representative Manned Flight Awareness Office You know, I've b n sitting herelistening to tap manqx%bentrqrmsentatives, snd the more successful m t i w t i o n directors, and the m e thfag that strikes n ei ad ~ D wS a t h a d dl the way through this area ob mrA'f9d M L v i & ~i ~ the,£act W w e need to mmnmicata. That is not a new problem. Go back @xmt Ijat.Wv pare, when man flrst crrtwfjed out upon to t& to his feilow man. But he f&e had;- slnd M wrttttsn lan@@ge, He could not put down a l;a~wg,~%atsgbt.Plratead Qf We shflity to write,he did earn@ up wi& tha ability to draw, And even today oar ~ ~ e o l ~exploring; ~ r f scave%will find drawings on the cavern waUa-man desperately atbmpting to put d h something that will last, and give the benefit of his thoughts. Now today we have a written ltuiguage, a d through f3m @ace pmgxpm we have oommunications that a r e werldwidh. You would thhk we wouldn't have any problem t@bg ta e&ah dher But obviously we. do. I t$i&. st 1$8t14t &ma of our top maaagement people w l h w&A&y mM, '%&we neeti to d~is comnunieate s lit& btt be&fmwith worker. They recognize a e p m m s , Ws too in NASA have a problem of corn., We b v e to oorammbcltewith i m y thQY8 ; Wd m1tW&6&0fr8. We have to try to get our mes- . B - hi@&& -t@amto your w o r k e r s - d thous;pgPZ ef there a r e several them. And when the M d P$t@ Awaremera p r o w tried to build a little fire ~&Ier mr efforts in #is area, &out two and a half years sga, one of the things we r@csgniaad?slacking was a .central theme. We knew that everybody had m~tfvationalprog;l.nuns in the field. But they w&re~'t k 9 I l ytaking NASAfsr massage. They weren't tarlk%qgt b g t our astronauts*and our mission a d s . $0 we bAed-to put to$e&br alittle_c8ntrJ theme, and Z ,ams w e you a r e all fmDierr with our f f o o p y the Aatxs~wiuV~ program. f d a f t want30 go into it..too because we don't have much W e . But there a r e a few little thing@ I would like to mention about S n q y the Astronaut. Snoopy is not a motivation grolpsun, and there ham b e several remarks in that dirwtion today. I h o p no one lock? upon Snoopy the Astronaut, a s a motivation program. Snoopy sems two purporserr He is a visual symbol of commanication, and he serves a s an award, or recognition program, for use of the astronauts themselves. Those are his only two r o h s . Hehas abeblukly nothing to do with your motivation program. A good motivation program has been spelled out here pretty distinctly today. But, Snoopy is an aestst. He is at001 for you, if you care to use him. A good motivation tool. He has bees extremely effective. I think most everyone relates to Snoopy, in one way o r another. But people do relate to cartoon@, ever since that dim day in the geological past. People do fYmn-onlT to a good cartoon. We have been caxrying Snoopy a s a communicatiom symbol for approximately two years now. When we firat made our contact with United Features, which owns this copyright, and with Mr. Charles Schulz ,we made some agreements with them. I would like to q e l l these out go that if yo^ have any doubt in your m h d you know exactly what you can, and what you csnnot do, with this symbol. . Number o w : M r . Schuk and United Features both agreed &at they do not want company personnel artists i n the art department drawing Snoogy, a d using that image tB& they draw on posters, decals, cards or angrthing else. The reason for this, no two artists wilI &raw hinoopy exactly alike. Pretty soon, when a million different Snoogys appear, he looses his identity. If you want to use Snoopy in a particular way, or if you need a particulardrawing, all you have to do Ihl ask fox it, And I'll tell you how to do that. ~ d if we a use Snoopy in any form on posters, cards, eta., we will carry the United Features copyright. Just a small Ifcffin a circle followed by United �Features Syadicde, lW9 (smd that w i l l &mge to 1970). The reason f o r a a t is a v e q gmd w. If a p r c d u ~ e r of materids that a r e sold *Q tb public ean prove ip oourt that tl &tlsaeter lib; qppxd%housands bf times witbout. a ,then3t bbecmm public property. This fs P wry d&1e piece of prcqerty we me &Uowd .t@ we a;t no wst to o.i think the Zesrst we ctwr do i s be d~olubalywsre taat when we use it id sur eaiqgqy pspers there is o c ~ y l " i g h t u w b m e athe&ctary. ~ Bw%f&st,we a h o a assllz"e that @ pfckrre i&E bwbemfurniled to us by Mr. &hul&, at.covers postere, deode, and silver pin has a copp5gM m &e hwk, B we h v e Ederz~in which we wish to w e m g . o a other items, we m e t , under mr ag~reasext, -it tbe~e-to Mr. James Aememey at B~&m=es. My expertenca with him hirs~tbsrd~h.asapp~a.lped 100p%rcenEdeve@W i we hawe asked h3m far. & Xhis i8 M) pmbbm either. I% does want t~ hfmwhat we me doing wit31 his prapmty. a m tha basic @ourid W for using Ehmpy-. z@ a a e oa @waeWeyrrtC w t is ovaiiable to you. All T Q P .tso~do~b ,tlWmit your idea as to h0r\kr wtsh ko w e thiW Iff& chmwter, give me a rcmgh &W, am3 I w i l l have Mr. Schulz draw it for you. afe dm do u%etemqthiag be has d r a m before. For &-I@, tbe oaI*toms that @pparedisn fakp them tla& hse theao, ,w*wsl'fe &-tic pr-d af muram th& we use the ewp&. Bo tlutt&ollld be n,problam. We have dlQIi‘q$ many ~ ~ Chr8 ~ , ~ again, d y cm@k@a h m p y aa an astmwut. That's iqwtm&. &a w e of c-ne 1s very eBecWe have found t2ve. I think a kt af gm do like &e ;SMopy cartoms apd da umfe the?. E&mevw, & m e QT the mmqmnfear do n ~mum t t~ be w%&Sm~py.C & w I b w of, bwww Eboog,~WM wed in a car & @ p t l w on tdeW&a. 1 f&& it ww, ad Ford Cbg2.W~that ulaedt.8e &@e pm.w%y 4$mg. TBis paI.tEcaIar Supplier mtakss mwtber b m Bf car, @awe him, %ha&gwdness, $Wrwc)gn* k.BBs2 &@repa 80ma @dwwl help in ttre cwt.oo~merm. I would to s_Bm.you aezwlmn h t h f b~ m~ drm by ~ L woria S famous ct~&anist, at3&htdZWQt&%b~mBIhb (!Ygure 1). Ithinltyoudll9fl~ . the Am&c;m p p l e Tkey have all g ~ at real good sense of humor, and they get the message real fast. Cartooning a s a basic form of communication is extremely effective. This is all we're trying to do with these characters, turd we don't use them loopercent. A%you all know, we put out a great many posters. They are not all cartoons. We use our astronaut pictures. We use that have no trace of ~ t marry things , humor in them. But we liketo intersperse alittle bit of humor, because we think it gets a hold on people. We get our message across just a little bit better. I believe we have Mr. Hrt in the audience with us, and I would like to introduce Johnny. I wish you would come up and say hello, Johnny. I'd like to have you all meet him, and then we will go over the ground rules of Qur agreement with Johnny. af %a little eluarr- 'W, '+ d3mwa by Jaha$ m. f gatfss ae a to jwlnars i s toThar whar9de~thwbel. I am v w htri@d*@ Johnnyt@8pad pad=. $&m%yhas LBm& to 13 us uae his f E % 1 c$maw fez xis. We OB -d&~, or in rn dber can m e P watfr .la which he d eppmva. We &.laa@a~have * faf -6 8%-t ~~~ &ar &@ ~ O S ~ S . Mr. Stmt.\cvozadlike3W %oamw i%eOWa ~ t & t T Sd~t?, % &@& SO& b ~ &' @& MkEXpWy doing &i4. &a@%&* wUl I~aee-th%ir mt&nf&y. tand their d : W e @!'~WQ %I, FIGURE 2 �of you will come up with some good ideas for cost reduction, using Johnny's characters. You can also look at new technology, or dress up otherwise very dull engineering standards reports. Johnny's working on a bunch of them for us now. He will work in any area that is approved by NASA. So we hope to put Mr. Hart: 1'11 be verybrief. When youareas short a s 1 sun, you a r e pretty h r i d in the first place. But I am just proud and happy to be given the opportmity to work on this very noble program. Thank you very much. Mr. Chop: Let me tell you a little more about this guy. So you will know the type of guy you a r e working with. When I talked to him about coming down here to virit with you all, 1 offered to attempt to get invitational travel orders so that NASA would pick up his travel cost. He said, "No, that is too much trouble, I will just pay my own way. " And he did, a l l the way from Eadicatt, New York, and back. That will give you an idea of the sinoerity that he brings to this program. The g r m d ruler again, I q l a i n e d to Johnny how we operate with the United Features and with Mr. Sohulz, Mr. I-& has Preatiss Hall. Is that right, Johnny? He like8 our existing arrangement. A single source of cow&&, whioh will be my office. Otherwise he would get afload of letters and he would have to pick and choose himself to decide which are most import m t and that would take up all his time. One of the things bis -nay fs insisting on, is that we do not He has a job to do. He makes his o v e ~ ~ o him. rk money cartooningfor the Syndicate. You make nothing cartooning f a r NASA. The groundrulethen is usethe single point of contact for your request, and that will be my d i c e . The mcond is that the company artists will nat dram $he liMe characters. Johnny will do that for us. And third, if we have anything outside of pWteTs and decals we want to produce, we will have to ieubmit it for approval. I want to digress just a minute. With Mr. Bolger in Tom Stafford's office the other day we had a little discussion about astronaut plant visits. As you may know,' Tom has just been assigned to the job of Chief Astronaut. That was previously held by Alan Shepard. Tom kind of threw up his hands while we sat there and said, "You know, I get letters from everybody asking for an astronaut to visit a plant. I get phone calls, notes that a r e scribbled, messages from the chief's secretaries. " He said, llYouknow, we've got to put this thing on the right road. " He said, "I want everything in writing, and I want it from one single source." And, he said, "1 want a 30-day lead time, minimum. And Iwant an alternatedate. 'I Mr. Bolger thought that was reasonable. He turned to me and said, "Alright, you do that." And, so, I have that one teo. If you want an astronaut to visit your plant, drop your NASA MFA guy a letter. He will acknowledge and forward the letter to me atNorthAmericanRmlrwell Spaee Division, Downey, California. My address is 12214 Lakewood Fbulevard. Attention: A1 Chop/RESPO Qffice. We must have about a 30day lead time, and an alternate date, Tom said he would honor everything he can. You must keep in mind the words that Stu Roosa had for us yesterday. 71 �MANNED FLIGHT AWARENESS WORKING TOOLS EUGENE E. HORTON Chief, Manned Flight Awareness Office Manned Spacecraft Center In the hierarchy oS hounds, there is one who stands scarf and g w l e s above the rest (Figure 1). He is the only beagle to reach the moon, and he even got k r e W o r e that sttpid cat next door. He isa p l l ~ t , p h i l q h r , moflteur, the quintessence of quixotic q a d q e d s . He is the master stroke of c h m n i r t Charkes '"SpaFYEjrWSchulz. His name, of couroe, is Szmapy. Thew is _amagic about this mutt that has e n d e a r 4 him to mmi9220ns. Snoopy appears in newspapers z@&mdthe globe, in dozens d languages. He grin8 a t us from sweatshirts, flight bags, pennants, s u e d toys, decals, coloring books. And even, thaaks t~ Colonel Ton Stafford, from space. Hz is a household word. Perhaps we love him because we relate to him.. We a l l lead a dog's life. Whatever his magic, he i e one of the most powerful communie&tors of aur a p . TMs is why he katc beonmr: apart of our Mam& Plight Awareness PPogrm. Bnd, like Smoky the Bear, who served to p r ~ t e c tour forests for some 28y@us,he is an important symbol. Snoopy, in his astrcmmt's garb, i s the astronautsrmatscot. He has h o r n ttr.8 accepted symbol of quality and of erncellence d worth and craftsmttnship in everything associ~tedw i a the Manned Spaceflight program. we attach a lot of importance to Snoopy. He is our standardbearer for quality and for professionalism. His work is impo-t. His job is really our job, to held the team together. And one way bo hold the team together is to create meaningful work. This is the job for management. But it takes more than this. It also takes close cmmunication, up and down and acrross the organization. And it has to take many forms, because people a r e different and are motirated in different ways. One motivator that has universal appeal (and we have discussed this these two days) is dissemination of understandable information, from the top-straight talk. Evidence from the boss that the workwedo each day is important; that someone cares that the job is done right, and done right the first time! (Figure 2.) Now, the value of ~ymbolsshould nst be mhimized. In Suly, there was a flag placed td the surface of the moon. Lt: w m not just a flag, W m r , it was an American sag! It symbolized. It was the standard of a free p@@s. It was Mt .anth& nakd, far-away rock to say m-. It has a message &?out imwination, courage, a d %ete@hnolagic.al prowess. And, as our Prestdent soon P o d , this measage had been heard in evgry laad he visited. The flight s f Apollo 11 is etched farever in hie-. Yet, the m e event that will burn most vividly in the minds of men, i s the raising of Old Glory on the lunar surface. A symbol. A lot of people attach importance to symbols. And FIGURE 1 �FIGURE 3 FIGURE 2 There are many ways to communicate. When Snoopy joined our program, we introduced him to a few Did you know that Snoopy, assisting our Manned Flight Awareness Pragrafn, rwohee the Department of Defense, the airlines that carry our carrgo, and some 200 contra~tors? Did you h o w that in three years MFA has distributed 90, a00 posters, a quarter of a million photographs, 900 individEEEal awards, 40,000 safety deods 3 Also, produced a monthly newsletter to all contmc-tors, WAS and MU oenter8, and seven films on M@ Flight Awareness wxi quality; &own exhibits to 155,000 ;films to 100,000 ; sent astronauts to 53 plants; hosted some 600 honorees at Cape Kennedy? I &ink it a p p ~ o p r i dour Snoopy's reply, "Good grid l (Figure 3. ) . This is a plcCm typifying wtivitles of theastronauts in support of the Manned Flight Awareness Program. Figure 4 shows aertronaut I h 8 W tyhweikart at Grumman, Bethpage appearingbefom the workers who assembled the hardware for his flight. And, we a r e hoping that dw* the months ahead, these visits will continue and will be conducted on a eelectivebasis in order to equitably serve the interests of dl contractors, with the astronauts appearing in plants throughout the nation where critical hardware is produced. As mentioned a moment ago, we have a poster program. It is unique perhaps in the sense that only through NASA, it is possible to obtain the Snoopy DO IT RIGHT. GUARANTEE A SUCCESSFUL '1- w m u ' P FIGURE 4 FIGURE 5 ��So, a findpointmade yesterday. This ie not the end, it's the begimiag. There L sm orderly, balanced program ahead of us, with work thatwill carry usfer generations tocome. Thebenefits are just emerging. New technology will be a m a W , and new jobs. With the space station, and shuttle, and mission^ to Mars, the challenge to the creative individual i s just now opening up. Bappfness is lentwing them is a future. This is fundamental to aur motivational effort. We know mut3h better aa a r e d t of this oonference, and the programs t a t we have seen over the p ~ s ttwo days, what the challenge is. Now, let us go home and spread a little happiness. FIGURE 8 . - . . - oF THE BEG\UN\NG! BUT TNE END . :<*,. FIGURE 11 - -. . " -- .. i S &L. �C L O S I N G R E M A R K S I wfll just take a minu&?of your time i$ closing before co~lef.udingour meetJng. We have been an the phone here f s r semral bars trytag to rw&Frmk Bomm in Mew Ya*. We was schedded k3 b with us, and wantad to be here, but unfortunately becaws of some gmbIerns inNew York he is behind schedule, and won't be uriM us. We will miss the oppostaznityto hear from him. Tkio L unfortunate s i w e he is a s vitally interest& iatMs wsrk as we are and one af o w strongest stlpywJ*o and Avoea&s. I @@t wmW to say a fm words about the purpose of M was to bring you here, introduce you to ma'RABA@ms for the Euhre, and to reemphasize the c a a e p t of a team Mort we have htd from the beghming of the apaee program. Every man in the aerospace f a r m that works on these space pprofpims is a member ~f that team. That of courae is what we have beean & y i i to emphasize with our Manned Plight Awareness Program all along. And finally, we wanted to reiterate the requirement for quality workmanship. We ham dme this bwause we are qarleaeing?; an ira%vit&1%slump, o r leaown, after the major effort to get C the mom with -10 11. And it concerns us all, You h v e haard of tb ooncern d NASA and contract and mzxnwsmnt ye@terday. We want to combat this letdam amd the ioxwred morale that we sae in a l ~ tcrf csur p l a t @ ,beau- of the cutbacks, by a m r i n g that the people who are motivating and talking to the workers intheir plants understand what our plsannw i~ and k m that we are going ahead with a p m g r m for &e Atbre. To do Sis we have brought to you whatwe & h k i@afaisly goodcast sfchaweters to sped--top N W and iadustry m$Lnagement. And thme people bfe come because they are concerned. They we qxken of their concern h t this letdown ad f w t Wt this b r e d s burnan error and indiffezem to d d i l , An4 Of course with that we a r e d@d of ageriaicing g fdlure of some kind which could kiU some ef our programs. I fu5twa.at f~ W e one momsat to r e d a statement by krzy M e r e r ,whom most of you know. He spent 35 or 440 years a8 Mr. Flight Safety f o r the United Itia$eta, a d he i s k n m around the world. He unfortuatsly had an operation rmently and then a minor h& atfa&, so he cddntn't wma doma here. Luckily he isba& on hisfeet a d wellen his way to recovery. S t Jerry says, in a short statement, Dr. Wfge Mueller , in a cIwsic statement a tbe ra~wes&d splashdown on Apollo 11 sdd, 'In this moment of man's greatest achievement, it is timely for us to dedicate ourmlvee to the unfinished work so nobly b e g o m by three of us, to rewlve that this nation, under Gad, will join with all men in the pursuit .of the destiny of mankind that will lead the way to the planets.' These words propose a powerful bacon to guide the future of mamed space flight. But to reach this god, a vast sucaession of intermediate problems must be solved. Not the least of these is the motivation of craftsmen toward perfection. The Achilles heel of spacecraft can be the man a t the bench. Success thus far is attributed to human integrity, the basis of product integrity. The natural inclination of most mm to conduct themselves with integrity has been superbly supported by the MFA progrrams which you individually, and collectively, have conceived and implemented. However, the psychological environment has ahangal. Apollo 11 was a tremendous suwesi. Complacency feeds on sumess. Thousands of craftsmen are being laid off-creating a problem of morale. The future is uncertain-creating-a problem of discipline, Dr. von Braun addressed himself to thase problems at the Honorees Reception on the eveningof July 15. He affirmed his confidence in the success of Apollo 11. Whatworried him, he said, was not Apollo 11, but Apollo 12, 15, 16, a d on down the line. It is for this readson you have gathered here. The exceptional originality of your previous programs may need additional creativity to maintain the momentum of the past. I am confident that this will happen. Iregret that I runnot present to hear the liveIy discussions and unique ideas that will be presented. Jerry Lederer . I want to thank you dl for coming, for giving us your time, and for participating. I know it is a sacrifice to you comingfrom your work. We felt that the fairly overwhelming agreement in the need for this reunion and participation was very gratifying. We have over 400 people that participated. And finally we want to thank the MSC, Dr. Gilruth, and the rest of his staff for being hosts to us here today. That's it, gentlemen, t+t concludes the meeting and thank you very much for coming. PHILIP H, BOLGER � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000053 Title A name given to the resource "After the Moon - What? Minutes of the Manned Flight Awareness Seminar." Description An account of the resource The seminar was held at the Manned Spacecraft Center, September 25-26, 1969. Creator An entity primarily responsible for making the resource United States. National Aeronautics and Space Administration Date A point or period of time associated with an event in the lifecycle of the resource 1969-09-26 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Manned space flight Project Apollo (U.S.) Saturn Project (U.S.) Space flight to the moon Space vehicles Type The nature or genre of the resource Minutes (administrative records) Text Source A related resource from which the described resource is derived Saturn V Collection Box 33, Folder 14 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000051_000074 https://digitalprojects.uah.edu/files/original/20/1155/spc_stnv_000071.pdf b1640a68a7f1bcbf1b664bdfa25ace14 PDF Text Text . J I k @ NATIONALAERONAUTICS AND SPACE ADM*lSTRATlON TELS WASHINGTON,D .C. 20546 WO 2-4155 W 0 3-6925 FOR RELEASE: ~ D I A T E m y 7, 1969 RELEASE NO: 69-68 PROJECT:&pow 19 SATURN !-llSTORY DOCUMENT University of Alabama Research lnstitcrk History of Science G. Technology G ~ w ------- - - - DOC.NO. Date S *S ------a- GB#ERALWSE--------------------------------------------1-7 WSSIOM oBJgc~s-----------------------------------------~-lo A ~ U X ) 10 ~~~~~---------------------------------------11-1 HISSIOBi CPWAJECTORY AND MHBWER DESCRImION----------------14 Launch Evenes-------------------------------------------15 m r s l o n E;vants---------------------------------------------l6-18 m t h ]Pa** Opblt-------------------------------------19 Wan8l-r Injection-------------------------------------19 Tranarposition, Daoklng and $;leetion---------------------- 19 'pransl-r Coaet-----------------------------------------2Q L m r Orbst Im%erti~n------------------------------------20 Lunar Parking Orbit L W-Autive Rendezvous---------------20-22 K I Transearth Injecti~n------------------------------~-------22 wasearth Caa~t----------------------------------------22 mtrg mding--------------------------------------------22 O~~TIQ~S--------------------------------------APOLLO 10 A L ~ A T MIISJSIOH~--------------------------------~~-~~ E ABORT MoDES------------------------------------------------29 Deep Smae Abort@---------------------------------------- 29-31 APOLLO 10 a0/#0-80 DBCISIOM POImS------------------------ 32 O m R D mf;EfISIOM----------------;.----c-------------------APOLm 10 PBQmQRAPHIC TASKS------------------------------3 MHAR DESCRIPTION------------------------------------------35 pol lo Lunar mdiw ~ites-------------------------------36-37 COMMAND M D SBFtVICE MODULE STIPFICTURE, SYS'PElrtS---------------38-39 Y CSH Systees---------------------------------------.----.39-41 S~UCSTTL;ZES, UEIG~----------------------------~~ Ascent St;age-------------------------------------------- L W HOW ~ I)escent Stwe-------------------------------------.----. m w Module System------------------------------------A448 �Conteats Continued SAmRH W U W C R VEHICLE DESCRIPTIOM & OPERATIO&----------- 4 9 pipst Stage--------------------------------------------49 Second Stage--------------------------------------..----49-50 Stags---------------------------------------------50-51 nt Unit-----------------------------------------Ina 51-52 on----------------------------------------------Pro 52-53 Munch Vehicle Instrumentation and Communication---------53 Restapt-------------------------------------------S54 -55 APOEW 10 CRW-----------------------------------------------56 L i f e Support Equipment Space Suits--------------------56-57 - Heala---------------------------------------------------2;-62 Personal mgiene----------------------------------------$upviva& aeap--------------------------------------------63-64 Biomedical Lnflight lulsnitoring---------------------------a Regt-Wopk Cgcles------------------------------------------& waAnbg--.-----------------------------------------------65-66 Crew B&~gratphres-----~------------------------~---------67-72 &BI.uNcHQPEWONS-r,---------------------------73 Prelamch Preparakions----------------------------------73-75 u u H c R @omem39------------------------------------------76 a h i e l e Assembly m%ld$ng-------------------------------77-78 h m e h Control Center-----------------------------------78-79 Mob$le Launchep-------------------------------------------79-80 ABOLLX) T~~nsporker------------..---------------------------------80-81 Cpawlemaye-----------------------------------------------8l Mobile Service Stmewre---------------------------------81-82 Water mbwe System--------------------------------------82 m n e k and Deflector--------------------------------82-83 Pad areas------------------------------------------------83-w Mfasfsn control Centep---------------------------.--------84-85 ~~1aw" WC~WORK---------------------------------~~-~$ p ations ~etwork------------------------------8$-89 teps---------------------------------------- 89-90 Ships-----------------------------------------90-91 Xnrstrumentrttion Aircraft (ARIA)-------------91 0110 lo-----------------------------92 ye----------------------------------93 Is---------------------------------9 -95 luraJor Apollo/Saturn V Cont~actors-----------------------2-97 98 102 APOLLO GLOS ----,-,i,---------------------AI? ACRO A m mBRNmTxONS---------------------------103-l& CO SIOW ~s----------------------------.------------105 106 - - �LI Y N A T I O N A L AERONAUTICS AND WASHINGTON,D SPACE ADMINISTRATION .C. 20546 TELS' W O 2-4 155 W 0 3-6925, FOR' RE1 R E ~ S ENO: 69-68 APOLU) 10: MANt S NEAREST LUNAR APPROACH Two Apollo 10 astronauts w i l l descend to within eight nautical miles of the Moonls surface, the closest man has ever been to another c e l e s t i a l body. A dress rehearsal for the first manned lunar landing, Apallo 10 is scheduled for launch Mag 18 at 12:49 p.m. EMP f r o m the National Aeranautfca and Space Adlainistration's Kennedy Space Center, Fla. !?he eight-day, lunar orbit mission will mark the first time the complete Apollo spacecraft has operated around the Moon and the second manned flight for the lunar module. Pollowlng c l o s e l y the time line and traJectory t o be flown on Apollo 11, Apollo 10 w i l l Include an eight;-houp eequence o f lunar module (W)undocked a c t i v i t i e s during which the c o m d e r and Ijl p i l o t w i l l descend t o within eight nautical milea o f the lunar surface and later rejoin the colllmajld/aervice module (CSM) I n a 60-nautioal-mlle circular orbit. �MOON AT EARTH LANDING TRANSEARTH INJECTION ENTRY & LANDING TRANSPOSITION LUNAR ORBIT INSERTION MOON AT EARTH LAUNCH APOLLO LUNAR MISSION �A l l a s p e c t s of Apollo 10 w i l l d u p l i c a t e conditions of t h e l u n a r landing mission as c l o s e l y as p o ~ ~ i b l e - - S u angles n a t Apollo S i t e 2, t h e out-and-back flight path t o t h e Moon, and the time l i n e of mission events, Apollo 10 d i f f e r s from Apollo 11 i n t h a t no landing w i l l be m d e on t h e Moon's surf ace, Apollo 10 is designed t o provide a d d i t i o n a l operational experience f o r t h e crew; space vehicle; and mission-support f a c i l i t i e s during a simulated lunar landing mission. Among d e s i r e d data p o i n t s t o be gained by Apollo 10 a r e 3.44 systems operations a t lunar d i s t a n c e s a s well as o v e r a l l mission o p e r a t i o n a l experience. The was s u c c e s s f u l l y checked - out i n Earth o r b i t i n Apollo go i n c l u d i w a rendezvous sequence simulating l u n a r o r b i t rendezvous. Space navigation experience around t h e Moon is another b e n e f i t t o be gained from f l y l n g a r e h e a r s a l mission before making a l u n a r landing, More knowledge of t h e l u n a r p o t e n t i a l , o r g r a v i t a t i o n a l e f f e c t will provide a d d i t i o n a l refinement of Manned Space F l i g h t Metwork tracking techniques, and broad landmark t r a c k i n g w i l l b o l s t e r t h l s knowledge, �- Analysis of l a s t Becemberls Apollo 8 l u n a r o r b i t mission t r a c k i n g has aided refinement of t r a c k i n g and navigation techniques and Apollo 10 should reduce e r r o r margins s t i l l f u r t h e r . Apollo 10 crewmen a r e Commander Thomas P. S t a f f o r d , Command Moudle P i l o t John W e Young and Lunar Module P i l o t Eugene A. Cernan. The mission w i l l be t h e t h i r d apace f l i g h t f o r S t a f f o r d (Gemini 6 and 9 ) and Young ( ~ e m i n i3 and l o ) , and t h e second f o r Cernan ( ~ e m i n i9 ) . t h e Apollo 7 backup crew. The three were recycled from The Apollo 10 backup crew i a Com- mander L. Gordon Cooper, Command Moudle P i l o t Donn F. E i s e l e and Lunar Module P i l o t Edgar D, Mitchell. S t a f f o r d i s an A i r Force Colonel; Young and Cernan are Navy Commanders. If necessary, t h e backup crew can be s u b s t i t u t e d f o r t h e prime crew up t o about two weeks p r i o r t o a n Apollo launch. During t h i s period, t h e f l i g h t hardware and software, ground hardware and software, f l i g h t crew and ground crews work as an i n t e g r a t e d team t o perform ground simulations and o t h e r tests It i s necessary t h a t t h e f l i g h t crew of t h e upcoming mission. t h a t w i l l conduct t h e mission t a k e p a r t i n t h e s e a c t i v i t i e s , which a r e not repeated f o r t h e b e n e f i t of t h e backup crew. To v do s o would add an a d d i t i o n a l c o s t l y two-week perlod t o t h e prelaunch schedule, which, f o r a l u n a r mission, would r e q u i r e rescheduling f o r t h e next l u n a r window. �-4- The Apollo 10 rendezvous w i l l be t h e f i f t h space rendezvous i n which S t a f f o r d has taken part--Gemini 7/6 and t h e w o r l d ' s first rendezvous, and t h r e e t y p e s of rendezvous with t h e augmented t a r g e t docking a d a p t e r i n Gemini 9 , The Apollo 10 mission time l i n e can be d e s c r i b e d as a combination of Apollo 8 and Apollo 9 i n t h a t i t w i l l be a l u n a r o r b i t mission w i t h a CSM-LM rendezvous, Apollo 8 was a l u n a r o r b i t mission with t h e command/service module only, while Apollo 9 w a s an E a r t h o r b i t a l mission w i t h the complete Apollo s p a c e c r a f t and included a LW-active rendezvous w i t h t h e CSM. Apollo 10, a f t e r l i f t o f f from Launch Complex 39B, w i l l begin t h e three-day voyage t o t h e Moon about two and a h a l f hours a f t e r t h e s p a c e c r a f t is i n s e r t e d i n t o a 100-nautical mile c i r c u l a r E a r t h parking o r b i t . The Saturn V launch v e h i c l e t h i r d s t a g e w i l l r e s t a r t t o i n j e c t Apollo LO i n t o a t r a n s l u n a r t r a j e c t o r y as t h e v e h i c l e p a s s e s over A u s t r a l i a mid-way through t h e second r e v o l u t i o n of t h e Earth. The "go" f o r t r a n s l u n a r i n j e c t i o n w i l l f o l l o w a complete checkout of t h e s p a c e c r a f t ' s r e a d i n e s s t o be committed f o r i n jection. About a n hour a f t e r t r a n s l u n a r i n 3 e c t i o n (TLI), t h e command/service module w i l l s e p a r a t e from t h e Saturn t h i r d stage, t u r n around qnd dock with t h e l u n a r module n e s t e d i n t h e s p a c e c r a f t IlvI a d a p t e r . Spring-loaded l u n a r module holddowns w i l l be r e l e a s e d t o e j e c t t h e docked s p a c e c r a f t from t h e a d a p t e r . �-5- Later, l e f t o v e r liquid p r o p e l l a n t i n t h e Saturn t h i r d s t a g e w i l l be vented through the engine b e l l t o p l a c e t h e s t a g e i n t o a " s l i n g s h o t " t r a j e c t o r y t o miss t h e Moon and go i n t o solar orbit, During the t r a n s l u n a r c o a s t , Apollo 10 w i l l be i n t h e so-called passive thermal c o n t r o l made i n whlch t h e spacec r a f t r o t a t e s slowly about one of i t s axes t o s t a b i l i z e thermal response t o s o l a r h e a t i n g , Four midcourse c o r r e c t i o n maneuvers a r e p o s s i b l e during t r a n s l u n a r c o a s t and w i l l be planned i n real time t o a d J u s t t h e t r a j e c t o r y , Apallo 10 w i l l first be I n s e r t e d i n t o a 60-by-170-nautical mile e l l i p t i c a l l u n a r o r b i t , which two r e v o l u t i o n s later w i l l be circularized t o 60 n a u t i c a l miles, Both l u n a r o r b i t I n s e r - t i o n burns (MI) w i l l be made when Apollo 10 Is behind t h e Moon out of " s i g h t " of Manned Space F l i g h t Network s t a t i o n s , S t a f f o r d and Cernan w i l l man t h e U4 f o r systems checkout and p r e p a r a t i o n s f o r a n eight-and-a-half hour sequence t h a t duplicates--except f o r an a c t u a l landing--the maneuvers planned f o r Apollo 11. The LM twice w i l l sweep within 50,000 f e e t of Apollo Landing S i t e 2, one of t h e prime t a r g e t s f o r t h e Apollo 11 landing. �-6Maximum s e p a r a t i o n between t h e IM and the CSM during the rendezvous sequence w i l l be about 350 miles and w i l l provide an extensive checkout of t h e LPlI rendezvous r a d a r as well as of t h e backup VHF ranging device aboard t h e CSM, flown f o r t h e first t i n e on Apollo LO. When the LM ascent stage has docked w i t h t h e CSW and the two crewmen have t r a n s f e r r e d back t o t h e CSM, t h e LM w i l l be j e t t i s o n e d f o r a ground command ascent engine burn t o prop e l l a n t depletion which w i l l place the IN ascent s t a g e i n t o solar oribt. The crew of Apollo 10 w i l l spend t h e remainder of t h e time i n lunar o r i b t conducting lunar navigational t a s k s and photographing Apollo landing sites t h a t a r e within camera range of Apollo 10's ground track. The t r a n s e a r t h i n j e c t i o n burn w i l l be made behind the Moon after 61.5 hours i n l u n a r o r b i t . During t h e %-hour t r a n s e a r t h coast, Apollo 10 again w i l l c o n t r o l s o l a r heat loads by using t h e passive thermal c o n t r o l "barbecue" technique. Three t r a n s e a r t h midcourse c o r r e c t i o n s are possible and w i l l be planned i n r e a l time t o a d j u s t the Earth e n t r y corridor. �-7- Apollo 10 w i l l e n t e r the E a r t h ' s atmosphere (400,000 f e e t ) a t 191 hours 51 minutes a f t e r launch a t 36,310 feet-per-second, Command module touchdown w i l l be 1,285 n a u t i c a l miles down- range from e n t r y a t 15 degrees 7 minutes South l a t i t u d e by 165 degrees West longitude a t a n elapsed time of 192 hours 5 minutes. The touchdown point i s about 345 n a u t i c a l a i l e s e a s t of Pago Pago, Tutuila, i n American Samoa. (END OF GENERAL RELEASE; BACKGROUND IPIFORMATION FOLLOWS) �APOLLO 10 lunch aB/dTrans Lunar njection Astronauts Board' Apollo Trans Lunar Injection S a t u r n Staging Papollo S a t u r n Separation �P O L L O 10 Trans L u ~ . a rF Apollo Midcourse Maneuver Astronauts a t Command Module S t a r b n s �APOLLO 10 Trans Lundr F Final Course Adjustment Navigational Check �APOLFO 10 Lunar Oroita Lunar Orbit Insertion Television Braadcast 9 I Lunw Landmark Tracking Transfer to Lunar Module �APOLLO 10 Descent Orbit Insertion Lunar LBscent and Ren-dezvous Lunar Mceduie! %tag"sng LM Ascent Engine Firing to Depletion Lunar Landmark Tracking �APOLLO 10 Trans - ~ a r t h njection and F Trans Earth Injection ApsBlas Midcourse Maneu ler Navigational Check Final Reentry Preparations �Earth Reentry and Recovery - Command-Service Module Separation Command Module R e e n t r y Splashdown Recovery �MISSION Ol3JECTIVES Although Apollo 10 w i l l pass no c l o a e r than e i g h t n a u t i c a l miles from t h e l u n a r ~ u r f a c e , a l l o t h e r a s p e c t s of t h e mission w i l l be similar t o the f k r s t l u n a r landing mission, Apollo 11, now scheduled f o r July. The t r a j e c t o r y , time l i n e and maneuvers follow t h e l u n a r landing p r o f l l e . After rendezvous i s completed, t h e Apollo 1 0 t i m e l i n e w i l l d e v i a t e from Apollo 11 i n t h a t Apollo 1 0 w i l l spend a n e x t r a day i n l u n a r o r b i t , Additional LP4 o p e r a t i o n i n e i t h e r E a r t h o r b i t o r l u n a r o r b i t w i l l provide a d d i t i o n a l experience and confidence with t h e IM systems, i n c l u d i n g v a r i o u s c o n t r o l modes of t h e Ul primary/abort guidance systems, as w e l l as further assessment of crew time l i n e s . The mission w i l l a l s o t e s t t h e Apollo rendezvous radar a t maximum range (approximately 350 miles vs. 100 miles during Apollo 9). Apollo 10 w i l l mark t h e first space f l i g h t t e s t of t h e s t e e r a b l e S-band antenna and of t h e landing radar, The LM landing radar has undergone numeroue t e s t s i n Earth environment, but t h i s mission w i l l provide a n opportunity t o check t h e l u n a r s u r f a c e r e f l e c t i v i t y c h a r a c t e r i s t i c s with t h e landing r a d a r , Some 800 seconds of landing r a d a r a l t i t u d e a e a s u r i n g data w i l l be gathered as the IIvI makes two sweeps eight nautical miles above Apollo Landing S i t e 2. !Ehis mission w i l l a l s o provide t h e first opportunity t o check t h e very high frequency (VHP) ranging device aboard t h e CSM which s e r v e s as a backup t o t h e LM rendezvous r a d a r , The Apollo 10 mission p r o f i l e provides f u e l and o t h e r consumable reserves i n t h e rsrl. t h a t are g r e a t e r t h a n those planned f o r t h e first LM t o land on t h e Moon. The l u n a r landing mission i s t h e "design mission" f o r t h e Apollo s p a c e c r a f t , and such a mission has smaller although adequate margins of r e s e r v e consumable~. From l i f t o f f through descent o r b i t i n s e r t i o n , Apollo 10 f o l l o w s c l o s e l y t h e t r a j e c t o r y and time l i n e t h a t w i l l be flown i n t h e landing miss4on. Following t h e eight-mile pericynthion, t h e p r o f i l e c l o s e l y simulates t h e c o n d i t i o n s o f l u n a r o r b i t rendezvous af t a r a landing. �The May 18 launch d a t e w i l l produce l i g h t i n g conditions on Apollo S i t e 2 similar t o those t h a t w i l l be present f o r t h e landing mission. A t t h e low i n c l i n a t i o n t o be flown on Apollos 10 and 11 about 1,2 degrees r e l a t i v e t o the lunar equator-Apollo landing S i t e 3 can be photographed and o p t i c a l l y tracked by t h e crew of Agollo 10 i n addition t o t h e p ~ i m eS i t e 2. -- S i t e 1 waa photographed by Apollo 8 i n last December's lunar o r b i t mission and, together with t h e two s i t e s t o be covered i n Apollo 10, photographic, tracking and s i t e a l t i t u d e data on three s i t e s w i l l be in hand. Among the Apollo 10 obJectlves i s the gathering of a d d i t i o n a l Manned Space F l i g h t Network (MSFN) tracking data on vehicles i n lunslr alpbit. While MSFN experience i n tracking Apollo 8 w i l l benefit Apollo 10, t h e r e a r e s t i l l some uncert a i n t i e s , For example, t h e r e is s t i l l some lack of knowledge as t o what t h e exact lunar p o t e n t i a l o r g r a v i t y f i e l d i s and how it a f f e o t s an orbiting, spacecraft. I n tracking Apollo 8, downtrack, o r o r b i t a l timing e r r o r s projected ahead two revolutions were 30,000 f e e t , and o r b i t a l radtus measurements r e l a t i v e t o t h e center of t h e Moon were off 5,500 f e e t . MSFN tracking can produce accurate position and velocity information i n r e a l time while a spacecraft i s " i n view" from t h e Earth and not occulGed by the Moon, but landing and rendezvous operations w i l l require accurate pred i c t i o n s of p e s i t i o n and velocity several revolutions i n advance of t h e e v m t , The lunar p o t e n t i a l apparently a f f e c t s an o r b i t i n g spacecraft d i f f e r e n t l y depending upon o r b i t a l i n c l i n a t i o n and a l t i t u d e . Apollo 10 w i l l be flown on t h e same i n c l i n a t i o n t o the lunar equator a s the landing mission and w i l l provide iflormation f o r refining prediction techniques. Apollo 8 p o s t f l i g h t a n a l y s i s has produced modifications t o tracking a& position prediction techniques which should reduce downtrack e r r o r s t o 3,000 feet and a l t i t u d e e r r o r s t o l,lC00 f e e t . Apollo 10 w i l l allow mission planners t o p e r f e c t techniques developed as a r e s u l t of Apollo 8 tracking a n a l y s i s , Other space navigation benefits from Apollo 10 w i l l ha gained from combinin$ onboard spacecraft lunar landmark tracking data with ISSFN tracking and from evaluating present lunar landing site maps a t close v i s u a l and camera ranges. �Additionally, LEI descent and ascent engine burns will be monitored by HSFN stations for developing useful techniques for tracking powered Pllgbt in future miaslons. �APOLLO 10 COUNTDOWN The clock for t h e Apollo 10 countdown w i l l start a t T-28 hours, with a six--hour built-in-hold planned a t T-9 hours, p r i o r t o launch v e h i c l e p r o p e l l a n t loading. The countdown i s preceded by a pre-count operation t h a t begins some 4 days before launch. During t h i s e r i o d t h e t a s k s include mechanical buildup of both t h e comandAervice module and Uvl, f u e l c e l l a c t i v a t i o n and s e r v i c i n g and loading of t h e super c r i t i c a l helium aboard t h e LM descent stage. A 5% hour built-in-hold i s scheduled between t h e end of t h e pre-count and start of t h e f i n a l countdown. Pollowing are same of t h e h i g h l i g h t s of t h e f i n a l count: T-28 h r s . O f f l c i a l countdown starts T-27 h r s . 30 mins. I n s t a l l launch v e h i c l e f l i g h t b a t t e r i e s ( t o 23 h r s . 30 mins.) LM stowage and cabin closeout ( t o 15 firs.) T-21 hrs. Top off LM super c r i t i c a l helium ( t o 19 hrs ) . Launch v e h i c l e range s a f e t y checks 15 hrs .) (to T-11 hrs. 30 mlns. I n s t a l l launch v e h i c l e d e s t r u c t devices ( t o 10 hrs. 45 mins,) ~ommand/service module pre-ingress operations T-10 h r s . S t a r t mobile s e r v i c e s t r u c t u r e move t o park s i t e T-9 hrs . S t a r t s i x hour built-in-hold T-9 h r s . counting Clear b l a s t a r e a f o r p r o p e l l a n t loading T-8 hrs. 30 mins. Astronaut backup crew t o s p a c e c r a f t f o r prelaunch checks T-8 ~ P S *15 mins. Launch Vehicle p r o p e l l a n t loading, t h r e e s t a g e s ( l i q u i d oxygen i n first stage) l i q u i d oxygen and l i q u i d hydrogen i n second, t h i r d stages. Continues t h r u T-3 hrs. 38 mins. �T-5 h r s , F l i g h t crew alerted T-4 hrs. 45 mins , Medical examination T-4 hrs, 15 mins. Breakfast T-3 hrs, 45 mins. Don space s u i t s T-3 h r s , 30 mins* Depart Manned Spacecraft Operations Buildi n g for LC-39 v i a crew transfer van T-3 hrs. 14 m i n s . Arrive a t LC-39 T-3 hrs. 10 a n s . Enter Elevator t o spacecraft l e v e l T-2 hrs. b mins. Start f l l g h t crew ingress T-1 h r . 55 mins. Mission Control Center-Houston/spacecraft cornmad checks T-1 hr. 50 mins, Abort advisory system checks T-1hr, 46 mins. Space vehicle Ebergency Detection System T-43 mins. Retrack Apollo access arm t o standby p o s i t i o n (12 degrees) T-42 mins, Ann launch escape system T-40 mins, Final launch v e h i c l e range safety checks (to 35 mins, ) T-30 mins, Launch v e h l c l e power t r a n s f e r test ( ~ m tiest ) LM switch over t o internal power T-20 mins. Shutdown U l o p e r a t i o n a l instrumentation T-15 mins, Spacecraft t o i n t e r n a l power T-6 rnins. Space v e h i c l e f i n a l s t a t u s checks to T-10 rnlns. T-5 mins. 30 set, Am d e s t r u c t system T-5 mins. Apollo access arm fully retracted T-3 mins. 10 sec, I n i t i a t e f i r i n g command (automatic sequencer) T-50 see. Launch v e h i c l e t r a n a f e r to i n t e r n a l power �T-8.9 see. Ignition sequence start A l l engines running Liftoff *Note: Some ckianges i n the above countdown are possible as a r e s u l t of experience gained i n the Countdown Demonstration T e s t (C9M') which occurs about 10 days before launch. �lUCSSION TRAJECPORY AND BUUEWER DESCRIPTION Q Note; Information presented herein is based upon a May 1 launch and is subject t o change p r i o r ta the mission or i n real time during the mission t o meet changing conditions,) Iaunch Apollo 10 vdll be launched fran Kennedy Space Center Launch Complex 39B on a launch azimuth that can vary from 7 2 degrees to 108 degrees, depending upon the t3me of day of launch, The azimuth changes with time of day t o perfnit a fuel-optimum injection frm Earth paI?king o r b i t i n t o a free-return circumlunar trajectory, O t h e r factors influencing thelaunch windows are a daylight launch and proper Sun angles on lunar landing sites. The planned Apollo 10 launch date of Hay 18 w i l l c a l l f o r l i f t o f f a t 12:49 p.m. Efi on a launch azimuth of 72 degrees, Insertion i n t o a 100-nautical-=mile circular Earth parking o r b i t w i l l occur at 11 mlrmtes 53 seconds ground elapsed frun launch (GET), and t h e resultant o r b i t will be,inclZnd 32.5 degrees to the Earth's equator. �FLIGHT PROFILE TRANSEARTH lNJECTlON BURN CSM/LM SEPARATION LM PI-IASING BURN EARTH PARKING ORBIT CSM60N.MI. S-IVB RESTART CSM 60 DURING 2ND OR 3RD ORBIT CM SPLASHDOWN & RECOVERY S-IVB 2ND BURN CUTOFF TRANSLUNAR INJECTiON -IVB RESIDUAL / S/C SEPAR~TION', TRANSPOSITION, DOCKING & EJECTION (SLINGSHOT) 60 N.M. LUNAR OF . LUNAR ORBlT ClRCUlARIZATION �SPACE VEHICLE LAUNCH EVENTS/WEIGH!?'S Hrs. 00 00 00 00 00 00 00 00 00 00 00 00 00 i! 0 3 CC I 00 00 00 00 Time Min. 00 (-)08.9 00 00 12 00 21 01 92 32 02 02 . Altitude Sec. 15 40 41 42 11 03 03 03 07 09 09 09 16 21 39 14 15 18 11 11 43 53 : Event : Ignition F i r s t Motion T i l t Initiation Maximum Dynamic Pressure Center Engine Cutoff Outboard Engines Cutoff S-IC/S-II Separation S-I1 I g n i t i o n S-11 A f t I n t e r s t a g e J e t t i s o n LES J e t t i s o n I n i t i a t e IGM S-I1 Center Engine Cutoff S-I1 Outboard Engines Cutoff S-II/S-IVB Separation S-IVB I g n i t i o n S-IVB F i r s t Cutoff Parking O r b i t I n s e r t i o n Naut ~ e l o c l t y 'deight : Pounds M i . : Knots 0 .OO 0 .033 0.12 7 24 35 36 37 49 51 53 97 102 102 102 103 103 0 "0 *3 1554 3888 5324 5343 5335 5581 5642 5701 10977 13427 13434 13434 15135 15139 6,499,016 6,412,918 . I ) 985 2,43;, 1,842,997 1,465,702 1,465,123 -.. . I , 644,128 471,494 364,429 364,343 295,153 295,008 *First two v e l o c i t i e s are space f i x e d , Others are inertial v e l o c i t i e s . Vehicle on launch pad has i n e r t i a l v e l o c i t y of 408.5 meters p e r second (793.7 knots). The above figures a r e based on a launch azimuth of 72 degrees. a l l g h t l y f o r o t h e r azimuths. Figures w i l l vary �Apollo 10 l i e s i a n Events Event - Qmund Elapsed Time hr8:rIn: 8eC Date 6c lima v Purpose and (Resultant Orbit) Insertion into 100 nm c i r o u l a r EM. Insertion Injection i n t o free-return translunar traJectory with 60 arn pericynthion. CSH separatio?:, docking ?Iard-mating Ejection from SLA Separates CSM-LbI Prom S-IVB/ SLA. SPS evasive maneuver Frovides separation p r i o r t o f-IVE propellant dump and slingshotn mBnBuver. 6 lidcourse 2 correction No. 1 ' ,Midcourse correction No. 2 TJd +9 hrs. % +24 I &a. Ridcourse cormction No. 3 LC1 -22 h r s , Mldcour~ecorrection No. 4 LO1 -5 hre. Of CSM and LSI. * These midcourse corrections have a nomlnal velocity change of 0 fps, but w i l l be c a l culated in r e a l time t o eorr e c t 'PLIT: dispersions. LQCC-3 w i l l have a plane change component t o achieve desired lunar o r b i t Inclination. Lunar Orbit Insertion No. 1 I n s e r t s Apollo 10 i n t o 60x170 nm e l l i p t i c a l lunar o r b i t . huuw Orbit InsertSon No. 2 Circularizes lunar parking o r b i t t o 60 nm. CSlrI-IX undoaklng; separation Establishes equiperiod o r b i t f o r 2 nm separation (mini~ootball). Descent o r b i t insertion (DPB) Lower LH pericynthion t o eight nm (8x60). (SM RCS) , g I �Xvent - Date & The Purpose and (Resultant Orbit1 7Enr) DPS phasing bum Raises JN apocynthlon to 194 nm, allows OSM t o ass a d overt* (8x197. AP8 Insertion gum Siaulates I . ascent I n t o lunar o r b i t a f t e r landing (8~43.6). LH RCS concentria sequenae ini:late (CSI) burit Raises M pericynthion t o 46.2 nm, adjusts o r b i t a l shape f o r rendeevms sequence (42. w46.2) Radially dowmard bum adJusts IA t o constant 15 nm below CSH. 1l1 RCS conatant d e l t a height (om)burn 6 L1I RCS terminal phase 7 (WI) h r n Initiate . I1I thTYLsts along l i a a - O f - s&ht t o w a r d CSM, mldoourse and braking manepvors, a s neoessam. m0-W ~ b s f e back r to E)SM (about 107 om). APS burn ta depletion Poaigrade APS depletion bum near I# perloynthion i g j e c t s X.#l asoent s t q e into heliooentrla orbit. Transearth injection (%I) SP8 bum ~ n j e a t sCSM into Slf-hour transearth t r a j e a t a q . I 5 �Ground Elapsed Tiae hmr:mlm: see Bate h Tirw, (EBT) Midcourse correction Ilo. 5 !fSI +15 hrs. 5/24 5: 09 gas Midoaur~ecorrrrution XQ. 6 m e -~15 ~hrs. 5/25 5: 39 pas Xidcourse oorreotion Ha. 7 &try 5/26 5: 39 w WS?! reparation Entry Interface (400,680 feet) - 3 ~lrs. Parpose and (lle~)ulbntOrbit) -- * Tmwearth mLdoourse earrootloma w i l l be omin real tlma for entry oomidor contwl and for adjusting landing poiat to avoid recover~r area foul weather. Reentry condition. got4 Command module enters BartR(a aenaible ataosphere a t 36,310 fps. an ding: 1,285 na domrsly. iFo1p entry, 15 degree8 seven airmtas South latitude x 165 degrees West longitude. �The crew f o r t h e first t i m e w i l l have a backup t o launch v e h i c l e guidance d u r i n g powered f l i g h t , If t h e S a t u r n i n s t r u ment u n i t i n e r t i a l platform f a i l s , t h e crew can switch guidance t o the command module computer f o r f i r s t - s t a g e powered f l i g h t automatic c o n t r o l . Second and t h i r d stage backup guidance i s through manual takeover i n which command module hand c o n t r o l l e r i n p u t s a r e f e d through t h e command module computer t o t h e Saturn instrument u n i t , Apollo 10 w i l l remain i n E a r t h parking o r b i t f o r one-andone-half r e v o l u t i o n s a f t e r i n s e r t i o n and w i l l hold a l o c a l h o r i z o n t a l a t t i t u d e d u r i n g t h e e n t i r e period. The crew w i l l p e r f o m s p a c e c r a f t s stems checks i n p r e p a r a t i o n f o r t h e t r a n s l u n a r i n j e c t i o n (TLI burn. The f i n a l "go" f o r the TLI burn w i l l be given t o t h e crew through t h e Carnarvon, A u s t r a l i a , Manned Space F l i g h t Network s t a t i o n , 3 Midway through t h e second r e v o l u t i o n i n Earth parking o r b i t , t h e S-IVB t h i r d - s t a g e engine w i l l r e i g n i t e a t two hours 33 minuees 26 seconds Ground Elapsed Time (GET) over f i u s t r a l i a t o i n j e c t Apollo 1 0 toward t h e Moon, The v e l o c i t y w i l l i n c r e a s e f p s ) t o 35,651 f p s a t TLI c u t o f f from 25,593 feet-per-second a v e l o c i t y i n c r e a s e of 1O,O5 f p s , The TLI burn w i l l p l a c e t h e s p a c e c r a f t on a f r e e - r e t u r n circumlunar t r a j e c t o r y f rorn which midcourse c o r r e c t i o n s could be made with t h e SM r e a c t i o n c o n t r o l system t h r u s t e r . Splashdown f o r a f r e e - r e t u r n t r a j e c t o r y would be a t 6:37 porn4 EDT May 24 a t 24.9 degrees South l a t i t u d e by 84,3 degrees E a s t l o n g i t u d e a f t e r a f l i g h t time of 149 hours and 49 minutes, -- Q Transposition, Docking and E j e c t i o n (TM) A t about t h r e e hours a f t e r l i f t o f f and 25 minutes a f t e r t h e TLI burn, t h e Apollo 1 0 crew w i l l s e p a r a t e t h e command/ s e r v i c e module from t h e s p a c e c r a f t l u n a r module a d a p t e r (SLA), thmst o u t away from t h e S-IVB, t u r n around and move back i n f o r docking w i t h t h e l u n a r module. Docking should t a k e place a t about t h r e e hours and t e n minutes GET, and a f t e r t h e crew c o n f i m s a l l docking l a t c h e s s o l i d l y engaged, they w i l l connect t h e CSM-to-W u m b i l i c a l s and p r e s s u r i z e t h e LM with t h e command module surge tank. A t about 4:09 GET, docked s p a c e c r a f t w i l l be e j e c t e d from t h e s p a c e c r a f t LM a d a p t e r by s p r i n g d e v i c e s a t the four landing g e a r " k n e e H a t t a c h p o i n t s , The e j e c t i o n springs w i l l i m p a r t abput one fps v e l o c i t t o t h e s p a c e c r a f t . A 19.7 f p s s e r v i c e propulsion system (SPS e v a s i v e maneuver i n plane a t 4:29 GET w i l l s e p a r a t e t h e s p a c e c r a f t t o a s a f e d i s t a n c e f o r t h e S-IVB " s l i n g s h o t " maneuver i n which r e s i d u a l l i q u i d p r o p e l l a n t s w i l l be dumped through t h e 3-2 engine b e l l t o propel t h e s t a g e i n t o a t r a j e c t o r y passing behind t h e Moon's t r a i l i n g edge and on i n t o s o l a r o r b i t . T �SPACE VEHICLE EARTH PARKING ORBIT CONFIGURATION (SATURN V THIRD STAGE AND INSTRUMENT UNIT, APOLLO SPACECRAFT) �0 10 LUNAR ORB I T INSERTION LUNAR ORB I T 20 80 30 40 50 60 70 90 100 TRANSEARTH 'INJECTION 110 120 130 140 150 LAUNCH 160 170 180 193 200 SPLASHDOWN GROUND ELAPSED TlME (HOURS) SPACECRAFT ALTITUDE VS. T l M E �': 25 VELOCITY3 (MPH x 10 10 36 24 VELOC ITY (FTISEC) (lo3, , 5 0 0 0 40 80 120 160 200 TRANSLUNAR VELOCITY PROFILE 240 �POST TLI TIMELINE T L I + 2 0 SEC -:ORBIT RATE T L I + 2 5 MlN SC INITIAL SEPARATION (1 F P S ) T L I t 2 7 MIN NULL SEPARATION RATE AND PITCH TO DOCKING ATTITUDE LM WITHDRAWAL -20 FPS �T r a n s l u n a r Csast Up t o f o u r midcourse c o r r e c t i o n burns a r e planned d u r i n g t h e t r a n s l u n a r c o a s t phase, depending upon the accuracy of t h e t r a j e c t o r y r e s u l t i n g from the TLI maneuver. If required; the midcourse c o r r e c f i o n burns are planned a t TLI +g hours, TLI +24 hours, l u n a r o r b i t i n s e r t i o n (LOI) -22 hours and LOX -5 hours. During c o a s t p e r i o d s between midcourse c o r r e c t i o n s , t h e s p a c e c r a f t w i l l be i n t h e p a s s i v e thermal c o n t r o l (PTC) o r "barbecue" mode i n which t h e s p a c e c r a f t w i l l r o t a t e s l o w l y about one a x i s t o s t a b i l i z e s p a c e c r a f t thermal r e s p o n s e s p a c s t o t h e continuous s o l a r exposure. Midcourse c o r r e c t i o n s 1 and 2 w l l l n o t normally be made u n l e s s the p r e d i c t e d Mission Control Center 3 v e l o c i t y change i s g r e a t e r t h a n 25 feet-per-second. Lunar O r b i t I n s e r t i o n (WI) The f i r s t of two l u n a r o r b i t i n s e r t i o n burns w i l l be made a t 75:45:43 GET a t a n a l t i t u d e of 89 lllg above t h e Moon, LOI-1 w i l l have a nominal r e t r o g r a d e v e l o c i t y change of 2,974 f p s and w i l l i n s e r t Apollo 10 i n t o a 60x170-nm e l l i p t i c a l l u n a r o r b i t . LOI-2 two o r b i t s l a t e r a t 80:10:45 GET w i l l c3.r- c u l a r i z e t h e o r b i t t o 60 nm. The burn w i l l be 138.5 f p s r e t r o grade. Both LO1 maneuvers w i l l be w i t h t h e SPS engine n e a r p e r i c y n t h i o n when t h e s p a c e c r a f t i s behind t h e Moon and o u t of c o n t a c t w i t h MSPN s t a t i o n s . Lunar Parking O r b i t (LPO) and IN-Active Rendezvous Apollo 1 0 w i l l remain i n l u n a r o r b i t about 61.5 hours, and I n a d d i t i o n t o t h e LEP d e s c e n t t o eight n a u t i c a l m i l e s above t h e l u n a r s u r f a c e and subsequent rendezvous w i t h t h e CSM, e x t e n s i v e l u n a r landnark tracking t a s k s w i l l be performed by t h e crew, Following a r e s t period a f t e r t h e l u n a r o r b i t c i r c u l a r i z a t i o n , t h e LH w i l l be manned by t h e command and l u n a r module p i l o t and p r e p a r a t i o n s begun f o r undocking a t 98:10 GET. Some 25 minutes of s t a t i o n keeping and CSM i n s p e c t i o n of the IM will be followed by a 2.5 f p s r a d i a l l y downward SM RCS maneuver, plati n g t h e I24 and CSM i n e q u i e r i o d o r b i t s w i t h a maximum s e p a r a t i o n A t t h e midpoint of t h e m i n i f o o t b a l l , of two m i l e s ( m i n i f o p t b a l l the descent propulsion system (DPs) w i l l be f i r e d r e t r o g r a d e 71 f p s a t 99:34 GET f o r t h e descent o r b i t i n s e r t i o n (DOI) t o lower LM p e r i c y n t h i o n t o e i g h t miles. The DPS engine w i l l be f i r e d a t 10 p e r c e n t t h r o t t l e s e t t i n g f o r 1 5 seconds and a t 40 p e r c e n t f o r 13 seconds, 7. �LUNAR ORBIT INSERTION 101- 1 LO1 - 2 I EARTH EARTH �LUNAR ORBIT ACTIVITIES LM A C T I V E RENDEZVOUS LM C ; O AND LANDMARK S RN 31 I SEP PHAS STRl P PHOTO 1 AND 2 T g . 0. 33 I h) 0 d 4 LANDMARK TRACKING I I TEI STRIP PHOTO 3 �24.5 DEG PlTCH DOWN FROM LOCAL HORIZONTAL OVER LANDMARK 2 DEG PITCH DOWN FROM LOCAL HORIZONTAL BEGIN 0.3 DEGPEC PITCH DOWN AT A05 'a PITCH DOWN 47 DEG FROM AT, = 296 SEC - a T 2 40 SEC AT3 = 25 SEC A Tq = 25 SEC AOS TO LOS = 3 MIN TOTAL I C S M / L M TYPICAL L A N D M A R K T R A C K I N G PROFILE �APOLLO 10 RENDEZVOUS SEQUENCE �COMPARISON OF F A N D G LM OPERATIONS PHASE RENDEZVOUS MANEUVERS UNDOCKING ilNG I I \ SEPARATION F UNDOCKING G RENDEZVOUS DOCKING INSER LM LIFTOFF RENDEZVOUS MANEUVERS k 8 �@lLM (DO1 DESCENT ORB IT INSERTION MANEUVER I MSFN AOS MSFN LOS SURFACE DARKNESS SC DARKNESS Ib 0 '? T + k/ -, \ (DO11 ' ~ ~ ~ ~ FAND + ~BEHIND '. :TSEPARATION ~ I R E C T I Ok+ N OF MOTION I\ I MOTION OF ~ o ~ "PL1.8 N. MI. / t EARTH LM RELATIVE TO CSM MOON CSM/LM SEPARATION MANEUVER �LUNAR MODULE DESCENT ORBIT INSERTION @ LM DESCENT ORB I T INSERTION (DO1 MANUEVER, RETROGRADE, DP,~S TO d C1 0 I 200 N. MI. I -a LM BELOW A N D AHEAD 1 - 1- LM BELOW -a (PHASING) LANDING SITE 54 000 FT. \ ABOVE LANDING SITE RAD IUS MOON �ORBIT RATE (0.05 DEG/sEC PITCH DOWN) FROM -400 to 200 FROM PERlCYTHlON O€iSERW CANDING SITE (PHOTOGRAPIO CHECKOUT LANDING O8SERVE LUNAR YAW RIGHT180 DEG AND plrcn up NEAR LUNAR SURFACE ACTIVITY MANEUVER 10 RIASlNG BURNATTITUDE �A s t h e W passes over Apollo landing S i t e 2, t h e IN landing radar w i l l be t e s t e d i n t h e a l t i t u d e mode but not i n descent r a t e , About 10 minutes a f t e r t h e pass over S i t e 2, t h e 195 f p s DPS phasing burn a t 100:46 GET w i l l boost t h e IM i n t o an 8x194-nm o r b i t t o allow the CSM t o overtake and pass t h e M , The phasing burn i s posigrade and t h e DPS engine is f i r e d a t 10 per cent t h r o t t l e f o r 26 seconds and f u l l t h r o t t l e f o r 17 seconds, The phasing burn places t h e LM i n a l'dwellll o r b i t which allows t h e CSN t o overtake and pass t h e LPI s o that a t t h e second LM passes over S i t e 2, t h e I24 w i l l t r a i l t h e CSM by 27 nm and w i l l be i n a proper p o s i t i o n f o r t h e i n s e r t i o n maneuver simulating ascent from t h e l u n a r surface a f t e r a landing mission, P r i o r t o t h e 207-fps M ascent engine retrograde i n s e r t i o n burn, the Ilvl descent s t a g e w i l l be j e t t i s o n e d and an evasive maneuver perfo~medby t h e ascent stage t o prevent recontact. The i n s e r t i o n burn w i l l be made a t 102:43 CIET and w i l l lower LM apocynthion t o 44.9 nra s o t h a t t h e LM i s 14.7 nin below and 148 rn behind t h e CSM a t t h e time of t h e concentric sequence i n i t i a t e (CSI) burn. Following IM radar tracking of t h e CSM and onboard computation of t h e CSI maneuver, a 50.5 f p s IM RCS posigrade burn w i l l be made a t a nominal time of 103:33 GET a t apocynthion and all l ~ g s u l ti n a 44.9~44.3-nm fM o r b i t , The IEI RCS w i l l draw from t h e LM ascent propulsion system (BPS) propellant tanks through t h e interconnect valves. A 3.4 f p s r a d i a l l y downward U l RCS constant d e l t a height (cDH) maneuver a t 104:31 GET w i l l place t h e W on a c o e l l i p t i c o r b i t 15 nm below that of t h e CSM and w i l l set up conditions f o r t h e terminal phase i n i t i a t e (TPI) burn 38 minutes l a t e r , The T P I maneuver w i l l be made when t h e CSM i s a t a 26,6degree e l e v a t i o n angle above t h e M a s l o c a l h o r i z o n t a l following continuing r a d a r tracking of t h e CSM and onboard computations for t h e maneuver. Nominally, t h e T P I burn w i l l be a 24.6-fps LM RCS burn along t h e l i n e of s i g h t toward t h e CSM a t 105:09 GET. Midcourse c o r r e c t i o n and braking maneuvers w i l l place the XM and CSM i n a rendezvous and station-keeping p o s i t i o n , and docking should take place a t 106:20 GET t o complete a eight-and-a-half hour sequence of undocked a c t i v i t i e s . After t h e commander and lunar. module p i l o t have t r a n s f e r r e d i n t o t h e CSM, the IM.w i l l be j e t t i s o n e d and t h e CSM w i l l maneuver 2 fps r a d i a l l y upward t o move above and behind the IN a t the t i m e of the W a s c e n t propulsion system burn t o propellant d e p l e t i o n a t 108:39 GET. �LUNAR MODULE PHASING MANEUVER I N. MI. I MOON U\A PHAS ING MANEUVER DPS- FULL THROTTLE LANDING S ITE �LUNAR MODULE INSERTION MANEUVER MSFN I 147 270 N.MI. N. MI. I n I \ 15 N. MI.--/ I (CSI) I MSFN AOS I I (RETROGRADE, APS) \ \ .-4 I --I 51 . I MOON N. ;O *L MI. / @ LM INSERTION MANEUVER INSERTION �LUNAR MODULE CONCENTRIC SEQUENCE INITIATION MANEUVER @cs I MANEUVER ,/-0>. .. / \ 4 ; . - 4 15 - N. MI. '\ MSFN LOS / I / 1 I 147 N. MI. \ (CSI) \\ '15 N.MI~,&, ( T P(CDH) I) AOSt MOON I / ,/ �LUNAR MODULE CONSTANT DIFFERENTIAL HEIGHT AND TERMINAL PHASE MANEUVERS RENDEZVOUS AND @ T P I MANEUVER (MIDPOINT OF DARKNESS) LM RCS 8 cj (0 I BRAKING I -45 75 N. MI. 30 N. M I . 1 I I MINI \ 1\\, 15 N MI \26.b0 TPI LOOK ANGLE TO CSM 36 MIN CDH I-@ CDH MANEUVER �The burn w i l l be ground-coamanded, An estiwated 3,837-Pps posigrade v e l o c i t y w i l l be imparted by t h e APS d e p l e t i o n burn near Uf pericynthion t o place t h e IN a s c e n t s t a g e i n a h e l l o centric orbit, h a d d i t i o n a l 29 hours w i l l be spent i n l u n a r o r b i t before t r a n s e a r t h i n j e c t i o n while t h e crew conducts l u n a r landmark t r a c k i n g t a s k s and makes photographs of Apollo landing sites. TransearBh I n j e c t i o n (TEI) The 54-hour r e t u r n t r i p t o Earth begins a t 137:20 GET when the SPS engine i s f i r e d 3622.5 fps posigrade f o r the TEI burn, L i k e LOI-1 and LOI-2, t h e T E I burn w i l l be made when t h e s p a c e c r a f t i s behind the Moon and out of touch w i t h MSFN s t a t i o n s . Transearth Coast Three c o r r i d o r - c o n t r o l t r a n s e a r t h midcourse c o r r e c t i o n b u m s w i l l be made i f needed: MCC-5 a t TEI +35 hours, MCC-6 a t entry interface (EI=400,000 f e e t ) -15 hours and a t E I -3 hours, Entry, Laodine Apollo 10 w i l l encounter t h e E a r t h ' s atmosphere (400,000 f e e t ) a t 191:50 GET a t a v e l o c i t y of 36,310 f p s and w i l l land some 1,285 nm downrange from t h e e n t r y - i n t e r f a c e p o i n t using the s p a c e c r a f t ' s l i f t i n g c h a r a c t e r i s t i c s t o reach t h e landing p o i n t . Touchdown w i l l be a t l92:O5 GET a t 15 degrees 7 minutes South l a t i t u d e by 165 degrees West longitude. �EARTH ENTRY ENTRY RANGE CAPABILITY * NOMINAL ENTRY RANGE - 1200 TO 2500 N. MI. - 1 2 8 5 N. MI. SHORT RANGE SELECTED FOR NOMINAL MISSION BECAUSE: e RANGE FROM ENTRY TO lANDlNG CAN B E SAME FOR PRIMARY AND BACKUP CONTROL MOPES PRIMARY MODE EASIER TO MONITOR WITH SHORT RANGE WEATHER AVOIDANCE, WITHIN ONE DAY PRIOR TO ENTRY, I S ACHIEVED USING ENTRY RANGING CAPABILITY TO 2500 N. MI. UP TO ONE DAY PRIOR TO ENTRY USE PROPULSION SYSTEM TO CHANGE LANDING POINT r: E' t �VELOCITY AT ENTRY INTERFACE 36.5 x l o 3 LAUNCH W INDOW CLOSED VELOC l TY 4 2I LAUNCH WI NDOW OPEN (FPS 18 20 24 L A U N C H D A T E (MAY) 23 25 �GEODETIC ALTITUDE VERSUS RANGE TO GO 400 NOTE: T I M E T I C K E D E V E R Y 1/2 MLN FROM E N T R Y INTERFACE ENTER S-BAND BLACKOUT 320 240 A3 8 88 h) 0 8 ALTITUDE (1000 FT) 160 E*XIT S-BAND BLACKOUT DROGUE PARACHUTE DEPLOYMENT 80 MAIN PARACHUTE DEPLOYMEN TOUCHDOWN. 0 1400 1200 1000 800 600 400 200 R A N G E TO SPLASHDOWN, (Nautical Miles) 0 �DROGUE CHUTES PILOT CHUTES CHUTE SPLASH DOWN VELOCITIES: 3 CHUTES 2 CHUTES - 31 FT/SEC - 36 FT/ SEC - _ - - -- AFTER TOUCHDOWM -- -- - - -- - - - E A R T H RE-ENTRY AND LANDING �ACTIVITY D A Y 1 REST PERIODS DATE/DAY' ED7 LUNAR REVOLUTION N O . 1 GET 0 1 8 12 12 6 16 20 24 28 6 24 32 36 40 12 44 - I Q 18 52 56 60 I MAY 21 -WEDNESDAY 24 6 64 12:so 68 1 4 LO1 D A Y I MAY 20 -TUESDAY I8 I 3 2 MAY I 9 MONDAY 24 IS 4 - - - MAY SUNDAY I8 12 48 APOLLO 10 SUMMARY FLIGHT PLAN n 18-50 74 I 2 76 78 6 - THURSDAY I I 1MO 18 6 3 4 5 6 7 8 9 10 11 12 13 14 IS 16 17 18 80 82 84 86 88 w 92 94 96 $0 IW 102 IM 106 la, 110 19 112 20 I14 12254 21 116 :8 i 22 23 24 118 ~ z o 122 a? 26 I 4 1% M A Y 24 24 v 28 128 130 29 132 I 7 TEl D A Y I MAY 23 -FRIDAY 24 - - I I MAY 22 24 - :6 5 DO1 DAY - M 134 31 136 I SATURDAY 1250 b 1 8 I8 MAY 25 24 6 - SUNDAY 12 I 9 18 10 MAY 26 -MONDAY 24 6 12.52 32 138 YO I42 144 148 152 156 160 164 168 172 176 180 I84 I@ 192 LM MANEUVER DATA 81. 15.6 SEC AV: 24.6 FPS NO ULLAGE LM (SNOOPY) (CHARLIE BROWN) C S M MANEUVER D A T A 1-5 �RECOVERY OPERATIONS The primary recovery l i n e f o r Apollo 10 i s i n t h e mtdP a c i f i c a l o n g t h e 175th West meridian of longitude above 15 degrees North l a t i t u d e , and jogging t o 165 degrees West l o n g i t u d e below t h e Equator. The h e l i c o p t e r c a r r i e r USS P r i n c e t o n , Apollo 10 prime recovery v e s s e l , w3 11 be s t a t i o n e d n e a r t h e end-of-mission aiming p o i n t . Splashdown f o r a f u l l - d u r a t i o n l u n a r o r b i t mission launched on time May 18 w i l l be a t 5 d e g r e e s 8 minutes South by 165 degrees West a t a ground e l a p s e d time o f 192 hours 5 minutes. The l a t i t u d e o f splashdown depends upon t h e time of t h e t r a n s e a r t h i n j e c t i o n burn and t h e d e c l i n a t i o n o f t h e Moon a t t h e t i m e o f t h e burn. A s p a c e c r a f t r e t u r n i n g from a l u n a r f l i g h t w i l l e n t e r E a r t h ' s atmosphere and s p l a s h down a t a p o i n t on E a r t h d i r e c t l y o p p o s i t e t h e Moon. T h i s p o i n t , c a l l e d t h e a n t i p o d e , i s a p r o j e c t i o n of a l i n e from t h e c e n t e r o f t h e Moon through t h e c e n t e r o f t h e Earth t o t h e s u r f a c e o p p o s i t e t h e Moon. The mid-Pacific recovery l i n e r o t a t e s through t h e a n t i p o d e once each 24 hours, and t h e t r a n s E a r t h i n j e c t i o n burn w i l l be t a r g e t e d f o r splashdown along t h e p r i m s y recovery l i n e . Other planned recovery l i n e s f o r a deep-space mission a r e t h e E a s t P a c i f i c l i n e extending roughly p a r a l l e l t o t h e c o a s t l i n e s o f North and South America; t h e A t l a n t i c Ocean l i n e running a l o n g t h e 3 0 t h West meridian i n t h e n o r t h e r n hemisphere and a l o n g t h e 2 5 t h West meridian I n t h e s o u t h e r n hemisphere; t h e I n d i a n Ocean l i n e a l o n g t h e 6 5 t h E a s t meridian; and t h e West P a c i f i c l i n e along t h e 150th East meridian i n t h e n o r t h e r n hemisphere and jogglng t o t h e 170th E a s t meridian i n t h e s o u t h e r n hemisphere. Secondary landing areas f o r a p o s s i b l e Earth o r b i t a l a l t e r n a t e mission have been e s t a b l i s h e d i n two zones--one i n t h e P a c i f i c and one i n t h e A t l a n t i c . Launch a b o r t landing areas extend downrange 3,400 n a u t i c a l m i l e s from Kennedy Space C e n t e r , fanwise 50 n a u t i c a l m i l e s above and below t h e l i m i t s o f t h e v a s i a b l e launch azimuth ( 7 2 degrees 107 d e g r e e s ) . Ships on s t a t i o n i n t h e launch a b o r t a r e a w i l l be t h e d e s t r o y e r USS Rich, t h e i n s e r t i o n t r a c k i n g s h i p USNS Vanguard and t h e a t t a c k t r a n s p o r t USS C h i l t o n . I n a d d i t i o n t o t h e primary recovery v e s s e l steaming up and down t h e mid-Pacific recovery l i n e and s u r f a c e v e s s e l s on t h e A t l a n t i c Ocean recovery l i n e and i n t h e launch a b o r t a r e a , 14 HC-130 a i r c r a f t w i l l be on standby a t seven s t a g i n g bases around t h e Earth: Guam, Pago Pago, American Samoa; H a w a i i , Bermuda; L a j e s , Azores; Ascension I s l a n d ; M a u r i t i u s and t h e Panama Canal Zone. �Apollo 10 recovery operations w i l l be d i r e c t e d from t h e Recovery Operations Control Room i n t h e Mission Control Center and w i l l be supported by t h e A t l a n t i c Recovery Control Center, Worfolk, Va., and t h e P a c i f i c Recovery Control Center, Kunla, H a w a i i . The Apollo 10 crew w i l l be flown from t h e primary r e covery v e s s e l t o t h e Manned Spacecraft Center a f t e r recovery. The s p a c e c r a f t w i l l r e c e i v e a preliminary examination, s a f i n g and power-down aboard t h e Princeton p r i o r t o offloading a t Ford I s l a n d , H a w a i i , where t h e s p a c e c r a f t w i l l undergo a more complete d e a c t i v a t i o n . It i s a n t i c i p a t e d t h a t t h e s p a c e c r a f t w i l l be flown from Ford I s l a n d t o Long Beach, C a l i f . , within 72 hours, and then trucked t o the North American Rockwell Space Division p l a n t i n Downey, Calif., f o r p o s t f l i g h t a n a l y s i s . �APOLLO 10 ALTmNATE MISSIONS Five a l t e r n a t e mission p l a n s have been prepared f o r t h e Apollo 10, each depending upon when i n t h e mission time l i n e it becomes necessary t o switch t o the a l t e r n a t e , Testing of t h e lunar module and a m - a c t i v e rendezvous i n E a r t h o r b i t a r e p r e f e r r e d over a CSM-only flyby mission. When it is impossible t o r e t u r n t o a low Earth o r b i t with rendezvous, a h i g h - e l l i p s e LM t e s t i s p r e f e r r e d over a low Earth o r b i t test. Where p o s s i b l e , Apollo 10 a l t e . r n a t e missions follow the l w r o r b i t mission time l i n e and have a d u r a t i o n of about 10 days. Apollo 10 a l t e r n a t e missions a r e summarized as follows: A l t e r n a t e 1: Early shutdown of S-IVB during TLI with r e s u l t i n g apogee l e s s than 25,000 n a u t i c a l miles, o r f a i l u r e of S-IVB t o i n s e r t s p a c e c r a f t i n t o Earth parking o r b i t and subsequent SPS contingency o r b i t i n s e r t i o n (COI), and in both cases no LM e x t r a c t i o n possible. A l t e r n a t e maneuvers would inc lude : ' * SPS phasing burn t o o b t a i n ground coverage of simulated * * Simulated L O 1 burn t o a 100x400 nm Earth o r b i t . lunar o r b i t i n s e r t i o n . Midcourse c o r r e c t i o n s t o modify o r b i t t o 90x240 nm end-of-mission e l l i p s e and t o complete SPS lunar mission duty cycle during remainder of ten-day mission. A l t e r n a t e 2: S-IW3 f a i l s during TLI burn and r e s u l t i n g apogee i s between 25,000 and 40,000 n a u t i c a l m i l e s ; no LM e x t r a c t i o n . Maneuver sequence would be: * SPS phasing burn t o o b t a i n ground coverage of simulated lunar o r b i t insertion. * * Simulated LO1 burn t o a semi-synchronous Earth o r b i t . SPS phasing maneuver t o place a l a t e r perigee over o r opposite d e s i r e d recovery zone. * SPS maneuver t o place CSM i n semi-synchronous o r b i t with a 12-hour period. * Deorbit d i r e c t l y from semi-synchronous o r b i t into Pacific recovery a r e a (ten-day mission). �Alternate No burn o r d u l l y extracted, : but TLI T L I apogee less than 4,000 mi success * * * * Simulated LO1 burn to lOOxk.lO-nm o r b i t , + IN-active rendezvous, Simulated descent o r b i t inserstion (DOI) maneuver with IN, Simulated powered descent i n i t i a t i o n (PDI) maneuver. Two SPS burns to c i r c u l a r i z e CSM orbit; t o 3-50 run. * Ground-commanded LM a s c e n t p r o p u l s i o n system (APs) b u r n t o d e p l e t i o n under abort guidance system (AGS) control, similar t o APS d e p l e t i o n burn i n Apo1l.o 9. * Additional SPS burns t o place CSM in 90x2@-nm end-ofmission e l l i p s e and t o complete SPS l u n a r mission duty cycle during remainder of ten-day mission, �A l t e r n a t e 4: E a r l y S-IVB TLI c u t o f f w i t h r e s u l t i n g apogee g r e a t e r than 4,000 nrn b u t l e s s than 10,000 nm, and c a p a b i l i t y of SPS and LM d e s c e n t propulsion system t o g e t h e r t o r e t u r n CSM-LW t o low E a r t h o r b i t without compromising CSM1s a b i l i t y t o r e s c u e LM. * SPS phasing burn t o obtain ground coverage of simulated lunar o r b i t insertion. * F i r s t docked DPS burn out-of-plane s i m u l a t e s d e s c e n t orbit insertion. * * * Second docked DPS burn s i m u l a t e s power d e s c e n t i n i t i a t i o n . * SPS burns tc c i r c u l a r i z e CSM o r b i t a t 150 + LM-active rendezvous. SPS simulated L O 1 burn. Phaslng maneuver t o o b t a i n ground coverage o f simulated powered d e s c e n t i n i t i a t i o n . ma. * Ground-commanded a s c e n t propulsion system burn t o d e p l e t i o n under a b o r t guidance system (AGS) c o n t r o l , s i m i l a r t o APS d e p l e t i o n burn i n Apollo 9 , * A d d i t i o n a l S P S burns t o p l a c e CSM i n 90x240 nm end-ofmission e l l i p s e and t o complete SPS l u n a r mission d u t y c y c l e d u r i n g remainder o f ten-day mission. A l t e r n a t e 5: SPS and DPS j o i n t l y cannot p l a c e CSM-LM i n low Earth o r b i t without compromising a b i l i t y o f CSM t o rescue LPI i n a rendezvous sequence, and SPS f u e l q u a n t i t y is too low f o r a CSM-LM circumlunar mission. * SPS phasing burn t o o b t a i n ground coverage of simulated lunar o r b i t insertion. * orbit. Simulated l u n a r o r b i t i n s e r t i o n i n t o semisynchronous * SPS p h a s i n g burn t o o b t a i n ground coverage o f simulated power d e s c e n t i n i t i a t i o n . * First docked DPS burn o u t o f plane s i m u l a t e s d e s c e n t o r b i t insertion. * Second docked DPS burn s i m u l a t e s power d e s c e n t i n i t i a t i o n and is d i r e c t e d o u t of plane. �* SPS phasing burn t o place a l a t e r perigee over or opposite desired recovery zone. * SPS maneuver to place CSM-LM insemi-synchronous orbit with a 12-hour period, * around-commanded LM ascent propulsion system burn t o depletion under abort guidance system control; poslgrade a t apogee. * Additional midcourse corrections along a lunar mission time line and d i r e c t entry from high ellipse, �ABORT MODES The Apollo 10 rni&lon can b e a b o r t e d at any time during t h e launch phase o r terminated during l a t e r phases a f t e r a successful insertion i n t o Earth o r b i t . Abort modes can b e summarized as follows: Launch phase - -- Mode I h u n c h escape (LEs) tower p r o p e l s command module away from launch v e h i c l e . This mode i s i n e f f e c t from about T-45 minutes when LES i s armed u n t i l L E S ' j e t t i s o n a$ 3:07 GET and command module l a n d i n g p o i n t C ~ J I range from the Launch Complex 39B area t o 520 nm (600 sm, 964 km) downrange, Mode 11 - Begins when LES i s jetti'soned and r u n s u n t i l the SPS can be used t o i n s e r t t h e CSM i n t o a s a f e E a r t h o r b i t ( 9 : 2 2 GET) o r u n t i l l a n d i n g p o i n t s t h r e a t e n t h e A f r i c a n c o a s t , Mode I1 r e q u i r e s manual s e p a r a t i o n , e n t r y o r i e n t a t i o n and f u l l l i f t e n t r y w i t h landing between 400 and 3,200 nm (461-3,560 s m , 741-5,931 km) downrange. - Begins when f u l l - l i f t landing p o i n t reaches 3,200 Mode 111 nm (3,560 sm, 5,931 km) and extends through E a r t h o r b i t a l i n s e r t i o n , The CSM would s e p a r a t e fram t h e launch v e h i c l e , and I f necessary, an SPS r e t r o g r a d e burn would b e made, and t h e command module wol~ld be flown h a l f - l i f t t o e n t r y and landing a t approximately 3,350 nm (3,852 sm, 6,197 km) downrange. - Mode I V and Apogee Kick Begins a f t e r t h e p o i n t t h e SPS could b e used t o i n s e r t t h e CSM i n t o a n Earth p a r k i n g o r b i t from about 9:22 GE2. The SPS burn i n t o o r b i t would b e made two minutes a f t e r -- s e p a r a t i o n from t h e S-IVB and t h e mission would continue as an Earth o r b i t a l t e r n a t e . Mode I V i s p r e f e r r e d over Mode 111. A v a r i a t i o n of Mode I V i s t h e apogee k i c k i n which t h e SPS would be ignited a t f i r s t apogee t o r a i s e p e r i g e e f o r a safe o r b i t . Beep Space Aborts Translunar I n j e c t i o n Phase -- Aborts during t h e t r a n s l u n a r i n j e c t i o n phase are only a remote p o s s i b i l i t y , but if an a b o r t became necessary d u r i n g t h e TLI maneuver, a n SPS r e t r o g r a d e burn could be made t o produce s p a c e c r a f e e n t r y , T h i s mode of a b o r t would be used o n l y i n t h e event of a n extreme emergency t h a t a f f e c t e d crew s a f e t y , The s p a c e c r a f t landing p o i n t would vary with launch azimuth and l e n g t h of t h e TLI burn, Another TLI a b o r t s i t u a t i o n would be used if a malfunction cropped up a f t e r i n j e c t i o n . A r e t r o g r a d e SPS burn a t about 90 minutes a f t e r TLI s h u t o f f would allow t a r g e t i n g t o land on t h e A t l a n t i c Ocean recovery l i n e , �Translunar Coast phase -- Aborts a r i s i n g during t h e three-day t r a n s l u n a r c o a s t phase would be similar i n n a t u r e t o t h e 90-minute TLI a b o r t . Aborts from deep space b r i n g i n t o t h e p l a y t h e Moon's a n t i p o d e ( l i n e p r o j e c t e d from Moon's c e n t e r through E a r t h ' s c e n t e r t o o p p o s i t e f a c e ) and t h e e f f e c t of t h e E a r t h ' s r o t a t i o n upon t h e geographlcal l o c a t i o n of t h e antipode. Abort times would be s e l e c t e d f o r landi n g when t h e a n t i p o d e c r o s s e s 1650 West l o n g i t u d e , The a n t i p o d e c r o s s e s t h e mid-pacific recovery l i n e once each 24 hours, and i f a t i m e - c r i t i c a l s i t u a t i o n f o r c e s an a b o r t e a r l i e r t h a n t h e s e l e c t e d f i x e d a b o r t times, l a n d i n g s would be t a r g e t e d f o r t h e A t l a n t i c Ocean, E a s t P a c i f i c , West P a c i f i c o r I n d i a n Ocean recovery l i n e s i n t h a t o r d e r of preference. When t h e s p a c e c r a f t e n t e r s t h e Moon's sphere of i n f l u e n c e , a circumlunar a b o r t becomes faster t h a n an a t t e m p t t o r e t u r n d i r e c t l y t o Earth. Lunar Orbit I n s e r t i o n phase -- E a r l y SPS shutdowns during t h e l u n a r o r b i t i n s e r t i o n burn (MI) a r e covered by t h r e e modes i n t h e Apollo 10 mission. A 1 1 t h r e e modes would r e s u l t i n t h e CM l a n d i n g a t t h e E a r t h l a t i t u d e of t h e Moon a n t i p o d e a t t h e time t h e a b o r t was performedt Mode I would be a I24 DPS posigrade burn i n t o an Earth-return t r a j e c t o r y about two hours ( a t next p e r i c y n t h i o n ) after an LO1 shutdown during t h e f i r s t two minutes of t h e LO1 burn. %ode IT, f o r SPS shutdown between two and t h r e e minutes a f t e r i g n i t i o n , would use t h e LM DPS engine t o a d j u s t t h e o r b i t t o a s a f e , non-lunar impact t r a j e c t o r y followed by a second DPS posigrade burn a t next p e r i c y n t h i o n t a r g e t e d f o r t h e mid-Pacific recovery line. Mode 111, from t h r e e minutes a f t e r LO1 i g n i t i o n u n t i l normal c u t o f f , would a l l o w t h e s p a c e c r a f t t o c o a s t through one o r two l u n a r o r b i t s b e f o r e doing a DPS posigrade burn a t p e r i c y n t h i o n t a r g e t e d f o r t h e mid-pacific recovery l i n e . Lunar O r b i t Phase -- If d u r i n g l u n a r p a r k i n g o r b i t i t became necessary t o a b o r t , the t r a n s e a r t h i n j e c t i o n (TEI) burn would be made early and would t a r g e t s p a c e c r a f t landing t o t h e mid-Pacific recovery l i n e . T r a n s e a r t h I n j e c t i o n phase -- m r l y shutdown of t h e T E I burn between i g n i t i o n and two m i n u t e s would cause a Mode I11 a b o r t and a SPS posigrade TEI burn would be made a t a l a t e r p e r i c y n t h i o n . Cutoffs a f t e r two minutes TEI burn t i m e would c a l l f o r a Mode I a b o r t - - - r e s t a r t of SPS as soon as p o s s i b l e f o r E a r t h - r e t u r n t r a j e c t o r y , Both modes produce mid-Pacific recovery l i n e l a n d i n g s n e a r t h e l a t i t u d e of t h e a n t i pode a t t h e time of t h e TEI burn. �Transearth Coast phase -- Adjustments of the landing point are possible during the transearth coast through burns with the SPS or the service module RCS thrusters, but in general, these are covered in the discussion of transearth midcourse corrections. No abort burns will be made later than 24 hours prior to e n t r y to avoid effects upon GM entry velocity and flight path angle. �A P O U o 10 GO/NO-GO DECISION POINTS Like Apollo 8, Apollo 10 will be flown on a step-by-step commit point or go/no-go basis in which the decisions will be made prior to each major maneuver whether to continue che misston or to switch 'to one of the possible alternate missions. The go/no-go decisions will be made by the flight control teams in Mission Control Center. ~o/no-go decisions will be made prior to the following events: * * * * * * * * + Launch phase go/no-go at 10 min. GEP for orbit insertion Translunar injection Transposition, docking and LM extraction Each translunar midcourse correction burn Lunar orbit insertion burns Nos. 1 and 2 Crew intravehicular transfer to M CSM-LM undocking and separation Hendezvous sequence I&! Ascent Propulsion system burn to depletion * Transearth injection burn (no-go would delay TEI one or more revolutions to allow maneuver preparations to be completed. ) * Each transearth midcourse correction burn �ONBOAHD TELEVISION On Apol i~ ill, onboard v i d e o will o r i g i n a t e f r o m t h e CM; Plans c a l l f o r both b l a c k tliere w i l l b e no 'CV camera i n t h e LM. arid white arld c o l o r ; V t o b e carried. Tkze b l a c k and white camera i s a 4.5 pound RCA camera equipped w i t h a 60-degree field of v i e w wide angle and lOOmm nine-degree i ' i e l d of' v i e w t,elephoto lens, attached to a 12-foot power/video cable. It produces a black-and-white 227 TV l i n e s i g n a l scanned a t 13 frames a second. Madrid, Goldstone and Honeysuckle C r e e k all w i l l Lave equipment t o make s t i l l photographs o f t h e slow s c a n s i g n a l and t o convert t h e s i g n a l t o commercial TV format. The color TV camera i s a 12-pound Westinghouse camera w i t h a zoom lens f o r close-up o r wide a n g l e use and a three-inch monitor which can be mounted on t h e camera o r i n t h e CM. It produces a s t a n d a r d 525-line, 30-frame-per-second s i g n a l i n c o l o r by u s e of a r o t a t i n g color, wheel. The s i g n a l can be viewed i n b l a c k and white. Only MSC, r e c e i v i n g t h e s i g n a l through Goldstone, w i l l have equipment to colorLze t h e s i g n a l . T e n t a t i v e plannlng i s t o use the c o l o r camera predominately, reverting t o t h e lack and white camera if t h e r e i s difficulty with t h e c o l o r system b u t r e q u i r i n g a t l e a s t one b l a c k and white t r a n s mission t o Honeysuckle Creek. The f o l l o w i n g i s a p r e l i m i n a r y p l a n f o r TV p a s s e s based on a 12:49 May 18 launch: GET - DATE/EDT EVENT T r a n s p)Io s i t i o n & dock Madrid Goldstone Transl u n a r c o a s t Goldstone Goldst one Translunar coast Pre-LOI-1 Qoldstone/Madrld Post LOI-2 Goldstone Post undock; formation Goldstone APS Burn t o Depletion Goldstone Landmark Tracking Goldstone Post -TEI Honeysuckle* Transearth coast Goldstone Transearth coast Goldstone *Transmission from RCA b l a c k and white camera. t o be from c o l o r camera. A l l o t h e r s planned �APOLW) 10 PHOTOGRAPHIC TASKS S t i l l a n d motion p i c t u r e s w i l l be made of most s p a c e c r a f t maneuvers as well as of t h e lunar s u r f a c e and of crew a c t i v i t i e s i n t h e ApolLrs 10 cabin. The t r a n s p o s i t i o n , docking and lunar module e j e c t ion maneuver will b e t h e f i r s t major event t o b e photographed. In lunar orbit, t h e IN-active rendezvous sequence w i l l be photographed from both the command and t h e l u n a r module. During t h e period between t h e LN DPS phasing burn and t h e APS i n s e r t i o n burn, t h e commander and lunar module p i l o t w i l l make still photos of t h e l u n a r ground t r a c k and of landing S i t e 2 from t h e eight-mile low p o i n t of t h e M 1 s f l i g h t path. After rendezvous i s complete and t h e LM APS d e p l e t i o n burn h a s been photographed, the crew w i l l make s t e r e o s t r i p s t i l l phot,ographs of t n e l u n a r s u r f a c e and i n d i v i d u a l frames of t a r g e t s of opportunity. Using t h e navigation sextant" o p t i c s a s a camera lens system, lunar s u r f a c e features and landmarks will be recorded on motion p i c t u r e f i l m . Additionally, t h e camerathrougi-1-sextarli. system will photograph star-horizon and star-landmark c m b i n a ; i o n s a s they a r e superimposed i n v i s u a l navigation signtirgs. The A p o i i u iO przotography plan c a l l s f o r motion p i c t u r e s o f crew a c t i v i t i e s srlch as i n t r a v e h i c u l a r t r a n s f e r through t h e CSN-LV docking t u n n e l and of o t h e r crew a c t i v i t i e s such as prcssdre s u i S donning. Long-dfstance E a r t r i and lunar t e r r a i n photographs w i l l be s h o S w i t h tne ? O w . still cameras. Camera eq:liprnent carried on Apollo 10 c o n s i s t s of two 7Omm Hasselbiad s t i l l cameras, each fitted with 80mm f/2.8 t o f/22 Zeiss P l a n a r lenses, a 250m t e l e p h o t o l e n s stowed aboard t h e connand xodule, and a s s o c i a t e d e q ~ i p m e n tsuch as f i l t e r s , r i n g s i g h t , spotmeter and a n i n t e r v a l m e t e r f o r s t e r e o s t r i p hot0 raphy. One iIaseeltlad w i l l b e stowed i n t h e IN and returned t o he C M a f t e r rendezvo~ls. Easselblad s h u t t e r speeds range from one second t o 1/503 s e c , e s For cotion p l c t u r e s , two Maurer data a c q u i s i t i o n cameras (one i n the CSM, one i n t n e 3.24) with v a r i a b l e frame speed selection .dl1 be ~ s e d . . Motion p i c t u r e camera a c c e s s o r i e s Incflde bayonet-mount l e n s e s of 75, 18, and 5m focal length, a r i s h t - a n g l e mirror, a c m a n d module boresignt bracket, a power c a j l e , and an a d a p t e r f o shooting ~ through t h e s e x t a n t . Apollo 10 f i b . stowage i n c l u d e s s i x '7Omrn Hasselblad magazines---two e x t e r i o r c o l o r r e v e r s a l and f o u r f i n e - g r a i n black and white; and 12 140-foot 16mm maoazbes of motion p i c t u r e film---eight e x t e r i o r c o l o r and Pour interior color--f o r a t o l a 1 1630 feet. �LUNAR DESCRIPTION T e r r a i n - Mountainous a n d c r a t e r - p i t t e d , t h e former r i s i n g thousands of feet and t h e l a t t e r ranging from a few i n c h e s t o 180 m i l e s i n diameter. The c r a t e r s a r e thought to be formed by t h e impact of m e t e o r i t e s . The s u r f a c e i s covered with a l a y e r of fine-grained m a t e r l a l resembling s i l t o r sand, a s w e l l a s small rocks and boulders. Environment - No air, no wind, and no moisture. The temperature ranges from 243 degrees i n t h e two-week lunar day t o 279 degrees below zero i n t h e two-week l u n a r a i g h t . Gravity i s one-sixth t h a t of Earth. Micrometeoroids p e l t t h e Moon ( t h e r e i s no atmosphere t o burn them up). Radiation might p r e s e n t a problem during per3 ods of unusual s o l a r a c t i v i t y . - Dark Side The dark o r hidden s i d e of the Moon no longer i s a complete mystery. It was f i r s t photogre~phed by a Russian c r a f t and s i n c e then has been photographed many times, p a r t i c u l a r l y by NASAJs Lunar O r b i t e r s p a c e c r a f t and Apollo 8. - Ori in There i s s t i l l no agreement among s c i e n t i s t s on t h -IT e o r g i n of t h e Moon. The t h r e e t h e o r i e s : (1) t h e Moon once w a s p a r t of E a r t h and s p l i t o f f i n t o i t s own o r b i t , ( 2 ) i t evolved as a s e p a r a t e body a t t h e same time a s E a r t h , and (3) i t formed elsewhere i n space and wandered u n t i l i t was captured by E a r t h ' s g r a v i t a t i o n a l f i e l d . Physical F a c t s Mameter 2,160 miles (about that of Earth) Circumference 6,790 miles (about Distance from E a r t h 238,857 m i l e s (mean; 221,463 minimum t o 252,710 maximum) Surface temperature +243O~(sun a t z e n i t h ) - 2 7 9 ' ~ ( n i g h t ) Surface g r a v i t y 1/6 t h a t of E a r t h Mass 1/100th ghat of E a r t h Volume 1/50th t h a t of E a r t h Lunar day and n i g h t 1 4 E a r t h days each Mean v e l o c i t y i n o r b i t 2,287 m i l e s p e r hour Escape v e l o c i t y 1.48 m i l e s p e r second & t h a t of Earth) Month ( p e r i o d of r o t a t i o n 27 days, 7 hours, 43 minutes around E a r t h ) �Apollo Lunar Landing S i t e s P o s s i b l e l a n d i n g s i t e s f o r t h e Apollo l u n a r module have been under study by NASA's Apollo S i t e S e l e c t i o n Board f o r more than two years. T h i r t y s i t e s o r i g i n a l l y were considered. These have been narrowed down t o f o u r f o r t h e f i r s t l u n a r landing. ( S i t e 1 c u r r e n t l y not considered f o r f i r s t landing.) S e l e c t i o n o f t h e f i n a l f i v e s i t e s was based on high r e s o l u t i o n photographs by Lunar O r b i t e r s p a c e c r a f t , p l u s close-up photos and s u r f a c e d a t a provided by t h e Surveyor s p a c e c r a f t which s o f t landed on t h e Moon. - The o r i i n a l sites a r e l o c a t e d on t h e v i s i b l e s i d e of t h e Moon w i t h i n 5 degrees e a s t and west of t h e Moon's c e n t e r and 5 degrees n o r t h and s o u t h of i t s equator. !$ The f i n a l s i t e choices were based on t h e s e f a c t o r s : *Smoothness ( r e l a t i v e l y few c r a t e r s a n d b o u l d e r s ) "Approach (no l a r g e hills, h i g h c l i f f s , o r deep c r a t e r s t h a t could cause i n c o r r e c t a l t i t u d e s i g n a l s t o t h e l u n a r module l a n d i n g r a d a r ) "Propellant requirements ( s e l e c t e d s i t e s r e q u i r e t h e least expenditure of s p a c e c r a f t p r o p e l l a n t s ) *Recycle ( s e l e c t e d s i t e s allow e f f e c t i v e launch p r e p a r a t i o n r e c y c l i n g i f t h e Apollo Saturn V countdown i s delayed) "Free r e t u r n ( s i t e s a r e w i t h i n reach of t h e s p a c e c r a f t luanched on a f r e e r e t u r n t r a n s l u n a r t r a j e c t o r y ) -- "Slope ( t h e r e i s l i t t l e s l o p e l e s s t h a n 2 degrees i n t h e approach p a t h and landing a r e a ) �The F l v e Landing S i t e s P i n a l l y Selected Are: Designations - Center Coordinates l a t i t u d e 2' 37' 54" North longitude 34 01' 31" East S i t e 1 is l o c a t e d on t h e e a s t c e n t r a l p a r t of t h e Moon i n s o u t h e a s t e r n Mare Tranq u i l l i t a t i s . The s i t e i s approximately 62 m i l e s (100 k i l o m e t e r s ) east of t h e rlm of C r a t e r Maskelyne, Site 2 l a t i t u d e 0' 43l $" North longitude 23' 38' 51" East S i t e 2 i s located on t h e e a s t c e n t r a l p a r t of t h e Moon in southwestern Mar Tranq u i l l i t a t i s , The s i t e i s approximately 62 m i l e s (100 k i l o m e t e r s ) e a s t o f t h e r h of Crater Sabine and approximately 118 m i l e s (190 k i l o m e t e r s ) southwest of t h e C r a t e r Maskelyne. Site 3 l a t i t u d e o0 22' 27'' North longitude lo 20' 42" West S i t e 3 i s l o c a t e d n e a r t h e c e n t e r of the v i s i b l e f a c e of t h e Moon i n t h e southwestern p a r t of Sinus Medii. The s i t e i s approximately 25 m i l e s (40 k i l o m e t e r s ) west of t h e c e n t e r or' the face and 21 m i l e s (50 kilometers) southwest of t h e C r a t e r Bruce, Site 4 l a t i t u d e 3 O 28' 34" South longitude 36 41' 53" West S i t e 4 i s l o c a t e d on the west c e n t r a l p a r t of t h e Moon i n s o u t h e a s t e r n Oceanus Procellanun. The s i t e i s approximately 149 m i l e s (240 k i l o m e t e r s ) south of t h e r i m of C r a t e r Encke and 136 m i l e s (220 k i l o m e t e r s ) e a s t of t h e r i m of C r a t e r Flamsteed, Site 5 l a t i t u d e lo 461 19" North longitude 41' 50' 20" West S i t e 5 i s l o c a t e d on t h e w e s t c e n t r a l p a r t of t h e v i s i b l e f a c e in southeastern Oceanus Procellanun, The s i t e i s approximately 130 m i l e s (210 k i l o m e t e r s ) s o u t h s e s t of t h e rim of C r a t e r Kepler and 118 m i l e s (190 kilometers) n o r t h n o r t h e a s t of t h e r i m of Crater Flamsteed, �APOLLO LUNAR LANDING S I T E S �COMMAND AND SERVICE MOUDLE STRUCTURE, SYSTEMS The Apollo s p a c e c r a f t for t h e Apollo 10 mission i s comprised o f Command Module 106, S e r v i c e Module 106, Lunar Module 4, a s p a c e c r a f t - l u n a r module a d a p t e r (SLA) and a launch escape system, The SLA s e r v e s as a m a t i n g s t r u c t u r e between t h e instrument u n i t a t o p t h e S-IVB s t a g e of t h e S a t u r n V launch v e M c l e and as a housing f o r t h e l u n a r mcdule. -- Launch Escape System (LES) P r o p e l s command module t o s a f e t y i n a n a b o r t e d launch, It i s made up of an open-frame tower s t r u c t u r e , mounted t o t h e command module by f o u r f r a n g i b l e b o l t s , and three s o l i d - p r o p e l l a n t rocket motors: a 147,000 poundt h r u s t launch escape system motor, a 2,400-pound-thrust p i t c h c o n t r o l motor, and a 31,500-pound-thrust tower j e t t i s o n motor. Two canard vanes n e a r t h e t o p deploy t o t u r n t h e command module aerodynamically t o an a t t i t u d e w i t h t h e h e a t - s h i e l d forward. Attached t o t h e base of t h e launch escape tuwer i s a boost prot e c t i v e c o v e r composed of g l a s s , c l o t h , and honeycomb, t h a t p r o t e c t s t h e command module from r o c k e t exhaust g a s e s from t h e main and t h e j e t t i s o n motors, The system I s 33 f e e t t a l l , f o u r P e e t i n diameter a t t h e base, and weighs 8,848 pounds. Command Module (CM) S t r u c t u r e -- The basic s t r u c t u r e of' t h e command module i s a pressure v e s s e l encased i n h e a t s h i e l d s , cone-shaped 11 f e e t 5 i n c h e s high, base diameter of 1 2 feet-10 inches, and launch weight 12,27'7 pounds. The command module c o n s i s t s o f t h e forward compartment which c o n t a i n s two r e a c t i o n c o n t r o l engines and components of t h e Earth l a n d i n g system; t h e crew compartment o r i n n e r p r e s s u r e v e s s e l c o n t a i n i n g crew accomodatlons, c o n t r o l s and d i s p l a y s , and s p a c e c r a f t systems; and t h e a f t compartment housing t e n r e a c t i o n c o n t r o l engines and p r o p e l l a n t tankage. The crew compartment c o n t a i n s 210 c u b i c f e e t o f h a b i t a b l e volume. Heat-shields around the t h r e e compartments are made of brazed s t a n l e s s steel honeycomb w i t h an o u t e r l a y e r of phenolic epoxy resin as an a b l a t i v e material, S h i e l d thickness, varying according t o hea% l o a d s , ranges from 0.7 inch at the apex t o 2.7 Inches a t the a f t end, The s p a c e c r a f t inner s t r u c t u r e i s of sheet-aluminum honeycomb bonded sandwhich ranging i n t h i c k n e s s from 0.25 i n c h t h i c k a t fo*ard a c c e s s t u n n e l t o 1.5 inches t u c k a t base. CSM 106 and LM-4 are equipped w i t h the probe-and-drogue docking hardware. The probe assembly i s a f o l d i n g coupling and Impact a t t e n t u a t i n g d e v i c e mounted on the CM t u n n e l t h a t mates w i t h a c o n i c a l drogue mounted on t h e Lfvl docking t u n n e l . After t h e docking latches are dogged down f o l l o w i n g a docking maneuver, both t h e probe and drogue a s s e m b l i e s are removed from the v e h i c l e t u n n e l s and stowed t o a l l o w free crew t r a n s f e r between the CSM a n d LM. �APOLLO SPACECRAFT �EARTH LANDING SUBSYSTEM DOCKING M E C H A N I S M STABILIZATION EARTH LANDING ENVIRONMENTAL ( I N BOOST COVER) ROLL E N G I N E S WI*DOW ( 2 PLACES1 ENGINES COMMAND MODULE FLY AWAY UMBILICAL SERVICE MODULE SECTOR I V O X I G I N TANKS 1 I O R O G I N T A N K S L I P S FUEL C I L L S CENTER SECTION S I R V I C I PROPUlSlON SISTEM n f L l u M T A N K S > �LUNAR MODULE COMMAND MODULE DROGUE ASSEMBLY DOCKING RING \ PROBE ASSEMBLY \ LATCH ASSEMBLIES APOLLO DOCKING MECHANISMS �-- S e r v i c e Module (SM) S t r u c t u r e The s e r v i c e module f s a c y l i n d e r 12 feet 10 i n c h e s f n d i a m e t e r by 24 feet 7 I n c h e s U g h , F o r the Apollo 10 m i s s i o n , it w 5 l l weigh, 51,371 pounds a t launch. Aluminum honeycomb p a n e l s one i n c h t h i c k form the o u t e r skin, and m i l l e d aluminum r a d i a l beams separate the i n t e r i o r InCo s i x s e c t i o n s c o n t a i n i n g s e r v i c e propulsion system and r e a e t f o n c o n t r o l f u e l - o x i d i z e r tankage, f u e l c e l l s , c r y o g e n i c oxygen and hydrogen, and onboard conszunables. -- S p a c e c r a f t -LM Adapter (sLA) S t r u c t u r e The spacecrat't LM a d a p t e r 1s a t r u n c a t e d cone 28 f e e t l o n g t a p e r i n g from 200 i n c h e s d i a m e t e r a t the base t o 154 i n c h e s a t t h e forward end a t t h e s e r v i c e module m a t i n g l i n e . Aluminum honeycomb 1.75 i n c h e s t h i c k i s the s t r e s s e d - s k i n s t r u c t u r e f o r the s p a c e c r a f t adapter. The SLA weighs 4,000 pounds. CSM Systems --e -- Guidance, Navigation and C o n t r o l S s t e m D N C S ) Measures caland c o n t r o l s s p a c e c r a f t p o s i t i o n , att t u d e anmelocity, c u l a t e s t r a d e c t o r y , c o n t r o l s s p a c e c r a f t p r o p u l si on s y s t e m t h r u s t v e c t o r , and d i s p l a y s a b o r t data. The g u i d a n c e s y s t e m c o n s i s t s a:' three subsystems: I n e r t i a l , made up of' a n inertial measurement u n i t and a s s o c i a t e d power and data components; computer which p r o c e s s e s i n f o r m a t i o n t o o r from ocher components; and o p t i c s , i n c l u d i n g s c a n n i n g t e l e s c o p e and sext3mt f o r celesl3al and/or landmark s p a c e c r a f t n a v i g a t i o n . CSM 106 and subsequent modules a r e equipped with a VHF r a n g i n g d e v i c e a s a backup t o the LM rendezvous r a d a r . S t a b i l i z a t i o n and C o n t r o l System (SCS) -- C o n t r o l s spacec r a f t r o t a t i o n , t r a n s l a t i o n , and t h r u s t v e c t o r a n d p r o v i d e s d i s p l a y s f o r c r e w - i n i t i a t e d maneuvers; backs up tihe guidance system. It has t h r e e subsystems: a t t i t u d e r e f e r e n c e , a t t l t u d e c o n t r o l , and t h r u s t v e c t o r c o n t r o l , -- Provides t h r u s t f o r l a r g e S e r v i c e P r o p u l s i o n System ( S P S ) s p a c e c r a f t v e l o c i t y changes t h r o u g n a gimbal-mounted 20,500pound-thrust h y p e r g o l i c e n g i n e u s i n g a n i t r o g e n t e t r i o x i d e o x i d i z e r and a 50-Fj0 m i x t u r e o f unsymmetrl c a l dimethyl h y d r a z i n e and h y d r a z i n e f u e l . Tankage o f t h i s s y s t e m i s i n zhe s e r v i c e module. The system responds t o a u t o m a t i c f l r i n g commands from the guida n c e and n a v i g a t i o n system o r t o manual commands from t h e crew. The e n g i n e p r o v i d e s a c o n s t a n t t h r u s t rate. The s t a b i l i z a t i o n and c o n t r o l system g i m b a l s the e n g i n e t o f i r e t h r o u g h t h e s p a c e c r a f t c e n t e r of g r a v i t y . -- The command module and t h e R e a c t i o n C o n t r o l System (RCS) s e r v i c e module e a c h has i t s own independent system. The SM RCS has f o u r i d e n t i c a l RCS "quads mounted around t h e SM 90 d e g r e e s apart. Each quad has f o u r 100 p o u n d - t h r u s t e n g i n e s , two f u e l and two o x i d i z e r t a n k s and a helium p r e s s u r i z a t i o n sphere. The SM RCS p r o v i d e s redundant s p a c e c r a f t a t t i t u d e c o n t r o l t h r o u g h c r o s s - c o u p l i n g l o g i c i n p u t s from the s t a b i l i z a t i o n and g u i d a n c e systems. �Small v e l o c i t y change maneuvers can a l s o be made w i t h the SM RCS. The CM RCS c o n s i s t s o f two independent s i x - e n g i n e sub- systems o f s i x 93 pound-thrust e n g i n e s each. Both subsystems are a c t i v a t e d a f t e r CM s e p a r a t i o n from t h e SM: one is used f o r s p a c e c r a f t a t t i t u d e c o n t r o l d u r i n g e n t r y . The o t h e r s e r v e s i n s t a n d b y as a backup. P r o p e l l a n t s for b o t h CM and SM RC$ are monomethyl h y d r a z i n e f u e l and n i t r o g e n t e t r o x i d e o x i d i z e r with helium p r e s s u r i z a t i o n . These p r o p e l l a n t s are h y p e r g o l i c , i . e . , t h e y burn s p o n t a n e o u s l y when combined w i t h o u t an i g n l t e r . -- E l e c t r i c a l Power System (EPS) C o n s i s t s o f t h r e e , 31c e l l Bacon-type hydrogen-oxygen f u e l c e l l power p l a n t s i n t h e s e r v i c e module which supply 2 8 - v o l t DC power, t h r e e 28-volt DC z i n c - s i l v e r o x i d e main s t o r a g e b a t t e r i e s i n t h e command module lower equipment bay, and three 115-200-volt 400 h e r t z t h r e e phase AC i n v e r t e r s powered by t h e main 2 8 - v o l t DC bus. The i n v e r t e r s are a l s o l o c a t e d i n t h e lower equipment bay, Cryogenic hydrogen and oxygen react i n the f u e l c e l l s t a c k s t o provide e l e c t r i c a l power, p o t a b l e water, and h e a t . The command module main b a t t e r i e s can be switched t o f i r e p y r o t e c h n i c s i n an emergency. A b a t t e r y c h a r g e r r e s t o r e s s e l e c t e d batteries t o f u l l s t r e n g t h as r e q u i r e d w i t h power from t h e f u e l c e l l s . -- Environmental C o n t r o l System (Ecs) Controls spacecraft atmosphere, p r e s s u r e , and t e m p e r a t u r e and manages water. In a d d i t i o n t o r e g u l a t i n g c a b i n and s u i t gas p r e s s u r e , t e m p e r a t u r e and humidity, t h e system removes carbon d i o x i d e , o d o r s and p a r t i c l e s , and v e n t i l a t e s t h e c a b i n a f t e r l a n d i n g . I t c o l l e c t s and s t o r e s f u e l c e l l p o t a b l e water f o r crew use, s u p p l i e s water t o t h e g l y c o l e v a p o r a t o r s f o r c o o l i n g , and dwnps s u r p l u s w a t e r overboard t h r o u g h the u r i n e dump v a l v e . P r o p e r o p e r a t i n g tempe r a t u r e of e l e c t r o n i c s and e l e c t r i c a l equipment i s m a i n t a i n e d by t h i s system t h r o u g h t h e u s e of t h e c a b i n h e a t exchangers, t h e s p a c e r a d i a t o r s , and t h e f l y c o l e v a p o r a t o r s . Telecommunications System -- P r o v i d e s v o i c e , t e l e v i s i o n t e l e metry, and command d a t a and t r a c k i n g and r a n g i n g between t h e spacec r a f t and E a r t h , between t h e command module and t h e l u n a r module and between t h e s p a c e c r a f t and t h e e x t r a v e h i c u l a r a s t r o n a u t . It a l s o p r o v i d e s intercommunications between a s t r o n a u t s . The t e l e c o m u n i c a t i o n s system c o n s i s t s o f p u l s e code modulated t e l e m e t r y f a r r e l a y i n g t o Manned Space P l i g h t Network s t a t i o n s d a t a on s p a c e c r a f t systems and crew c o n d i t i o n , VHP/AM voice, and u n i f i e d S-Band t r a c k i n g t r a n s p o n d e r , a i r - t o - g r o u n d v o i c e communications, onboard t e l e v i s i o n , and a VHF' recovery beacon. Network s t a t i o n s can t r a n s m i t t o t h e s p a c e c r a f t s u c h i t e m s as u p d a t e s t o t h e Apollo guidance computer and c e n t r a l t i m i n g equipment, and r e a l time commands f o r c e r t a i n onboard f u n c t i o n s . �S-band inflight antenna- 7 LM docking light SPACECRAFT AXIS A N D ANTENNA LOCATIONS �Two scimitar VHF omni antennas on SM--I (180deg. apart) axis Rendezvous radar SPACECRAFT AXIS A N D ANTENNA LOCATIONS �The high-gain s t e e r a b l e S-Band antenna c o n s i s t s o f four, 31-inch-diameter p a r a b o l i c d i s h e s mounted on a f o l d i n g boom a t the a f t end of t h e s e r v i c e module. Nested a l o n g s i d e t h e s e r v i c e p r o p u l s i o n system engine nozzle u n t i l deployment, t h e antenna swings out a t r i g h t a n g l e s t o t h e s p a c e c r a f t l o n g i t u d i n a l a x i s , w i t h t h e boom p o i n t i n g 52 degrees below t h e heads-up h o r i z o n t a l , S i g n a l s from t h e ground s t a t i o n s can be t r a c k e d e i t h e r automati c a l l y o r manually with t h e a n t e n n a ' s g i m b a l l i n g system. Normal S-Band voice and uplink,downlink communications w i l l be handled by t h e omni and high-gain antennas. -- S e q u e n t i a l System I n t e r f a c e s w i t h o t h e r s p a c e c r a f t systems and subsystems t o i n i e i a t e time c r i t i c a l f u n c t i o n s d u r i n g launch, docking maneuvers, s u b - o r b i t a l a b o r t s , and e n t r y p o r t i o n s of a mission. The system a l s o c o n t r o l s r o u t i n e s p a c e c r a f t sequencing such as s e r v i c e module s e p a r a t i o n and deployment of t h e E a r t h landing system. -- Detects and d i s p l a y s t o the c d i t i o n s , such as e x c e s s i v e p i t c h o r r o l l r a t e s o r two engines out, and a u t o m a t i c a l l y o r manually s h u t s down t h e b o o s t e r and a c t i v a t e s t h e launch escape system; f'unctions u n t i l t h e s p a c e c r a f t i s i n o r b i t , -- ) Includes t h e drogue and main s t - l a n d i n g recovery a i d s . I n a parac normal e n t r y descent, t h e command module forward h e a t s h i e l d i s j e t t i s o n e d a t 24,000 f e e t , p e r m i t t i n g m o r t a r deployment of two r e e f e d 16.5-foot diameter drogue p a r a c h u t e s f o r o r i e n t i n g and d e c e l e r a t i n g t h e s p a c e c r a f t , After d i s r e e f and drogue r e l e a s e , t h r e e p i l o t mortar deployed c h u t e s p u l l o u t t h e t h r e e main 83.3-foot diameter p a r a c h u t e s with two-stage r e e f i n g t o provide g r a d u a l i n f l a t i o n i n t h r e e s t e p s , Two main p a r a c h u t e s out of t h r e e can provide a s a f e landing. Recovery a i d s i n c l u d e t h e u p r i g h t i n g system, swimmer i n t e r phone connections, s e a dye marker, f l a s h i n g beacon, VHF recovery beacon, and VHF t r a n s c e i v e r , The u p r i g h t i n g system c o n s i s t s of t h r e e compressor-inflated bags t o u p r i g h t t h e s p a c e c r a f t if i t should land i n t h e water apex down ( s t a b l e I1 p o s i t i o n ) . -- Monitors s p a c e c r a f t systems f o r o~t-o a l e r t s crew by v i s u a l and a u d i b l e alarms s o t h a t c r e m e n may trouble-shoot t h e problem. -- Controls and Displays Provide r e a d o u t s and c o n t r o l f u n c t i o n s of a l l o t h e r s p a c e c r a f t systems i n t h e command and s e r v i c e modules, A l l c o n t r o l s a r e designed t o be operated by crewmen i n p r e s s u r i z e d s u i t s . Displays a r e grouped by system and l o c a t e d according t o t h e frequency t h e crew r e f e r s t o them. �WNAR MODULE STRUCTURESy WEIGHT The lunar module is a two-stage v e h i c l e designed f o r space o p e r a t i o n s near and on t h e Moon, The W is incapable of r e e n t e r i n g the atmosphere. The lunar module s t a n d s 22 f e e t 11 inches high and is 31 f e e t wide (diagonally a c r o s s landing g e a r ) , Joined by four explosive b o l t s and umbilicals, t h e asc e n t and descent s t a g e s of t h e LM operate as a u n i t u n t i l s t a g i n g , when the a s c e n t s t a g e f u n c t i o n s as a s i n g l e spacec r a f t f o r rendezvous and docking with t h e CSM. Ascent Stage Three main s e c t i o n s make up t h e a s c e n t stage: t h e crew compartment, midsection, and a f t equipment bay. Only t h e crew compartment and midsection a r e p r e s s u r i z e d (4.8 psig; 337.4 gm/sq cm) as p a r t o f t h e LM cabin; a l l o t h e r s e c t i o n s of t h e LM a r e unpressurized, The cabin volume is 235 cubic f e e t ( 6 . 7 cubic m e t e r s ) . The a s c e n t s t a g e measures 12 f e e t 4 inches high by 14 f e e t 1 inch i n diameter. S t r u c t u r a l l y , t h e a s c e n t s t a g e has s i x s u b s t r u c t u r a l areas: crew compartment, midsection, a f t equipment bay, t h r u s t chamber assembly c l u s t e r supports, antenna supports and thermal and microme teoroid s h i e l d . The c y l i n d r i c a l crew compartment i s a semimonocoque s t r u c t u r e o f machined longerons and fusion-welded aluminum s h e e t and i s 92 inches (2.35 m ) i n diameter and 42 inches (1.07 m) deep, Two f l i g h t s t a t i o n s a r e equipped with c o n t r o l and d i s play panels, a r m r e s t s , body r e s t r a i n t s , landing aids, two f r o n t windows, an overhead docking window, and a n alignment o p t i c a l telescope In t h e c e n t e r between t h e two f l i g h t s t a t i o n s , The h a b i t a b l e volume i s 160 cubic feet. Two t r i a n g u l a r f r o n t windows and t h e 32-inch (0.81 rn) square inward-opening forward h a t c h are i n t h e crew compartment f r o n t face. External s t r u c t u r a l beams support t h e crew compartment and serve t o support t h e lower i n t e r s t a g e mounts a t t h e i r lower ends, R i n g - s t i f fened semimonocoque c o n s t r u c t i o n i s employed i n the midsection, w i t h chem-milled aluminum skin over fusion-welded longerons and s t i f f e n e r s , Fore -and-aft beams a c r o s s t h e t o p of t h e midsection j o i n with those running a c r o s s t h e t o p of t h e cabin t o take a l l a s c e n t s t a g e stress loads and, i n e f f e c t , i s o l a t e t h e cabin from stresses, �DOCKING LUNAR SURFACE SENSING PROBE (4) APOLLO LUNAR MODULE �VHF ANTENNA(2) TRANSFER TUNNEL AND HATCH ALIGNMENT OPTICAL TELESC OCKING TARGET RECESS GASEOUS OXYGEN TANK (2) RENDEZVOUS RADAR ANTENNA AFT EQUIPMENT BAY REPLACEABLE ELECTRONIC ASSEMBLY FUEL TANK (REACTION CONTROL) IQUlD OXYGEN TANK ASCENT ENGINE COVER S-BAND INFLIGHT ANTENNA Q) HELIUM TANK @) HELIUM TANK (REACTION CONTROL) REACTION CONTROL ASSEMBLY (4 PLACES) OXIDIZER TANK (REACTION CONTROL) INGRESS/EGRESSHATCH CREW COMPARTMEN WATER TANKQ) APOLLO LUNAR MODULE - ASCENT STAGE �LM CABIN INTERIOR, LEFT HALF �LM CABIN INTERIOR, RIGHT HALF �The a s c e n t s t a g e engine compartment i s formed by two beams running a c r o s s t h e lower midsection deck and mated t o t h e f o r e and a f t bulkheads. Systems located i n t h e midsection include t h e LM guidance computer, t h e power and servo assembly, a s c e n t engine propellant tanks, RCS prop e l l a n t tanks, t h e environmental c o n t r o l system, and t h e waste management section. A tunnel r i n g a t o p t h e a s c e n t s t a g e meshes with t h e command module l a t c h assemblies. During docking, t h e r i n g and clamps a r e aligned by t h e LM drogue and the CSM probe, The docking tunnel extends downward i n t o t h e midsection The tunnel is 32 Inches (0.81 cm) i n diameter and is used f o r crew t r a n s f e r between t h e CSM and LFnl by crewmen. The upper hatch on t h e inboard end of' t h e docking tunnel hinges downward and cannot be opened with t h e pressurized and undocked. 16 inches (40 cm). A thermal and micrometeoroid s h i e l d of multiple l a y e r s of mylar and a s i n g l e thickness of t h i n aluminum s k i n encases t h e e n t i r e ascent s t a g e s t r u c t u r e . Descent Stage The descent s t a g e c o n s i s t s of a cruciform load-carrying s t r u c t u r e of two p a i r s of p a r a l l e l beams, upper and lower decks, and enclosure bulkheads -- a l l of conventional skin-and-stringer aluminum a l l o y construction. The c e n t e r compartment houses the descent engine, and descent propellant tanks a r e housed i n the four square bays around the engine. The descent stage measures 10 f e e t 7 inches high by 14 f e e t 1 inch i n diameter. Pour-legged t r u s s o u t r i g g e r s mounted on the ends of each p a i r of beams serve a s SLA a t t a c h points and a s "knees" f o r the landing g e a r main s t r u t s . Triangular bays between t h e main beams a r e enclosed i n t o quadrants housing such components a s t h e ECS water tank, helium tanks, descent engine c o n t r o l assembly of t h e guidance, navig a t i o n and c o n t r o l subsystem, ECS gaseous oxygen tank, and b a t t e r i e s f o r the e l e c t r i c a l power system. Like the ascent stage, t h e descent s t a g e is encased i n the mylar and aluminum a l l o y thermal and micrometeoroid shLeld. The I;M e x t e r n a l platform, o r "porch", is mounted on the forward o u t r i g g e r j u s t below t h e forward hatch. A ladder extends down t h e forward landing gear s t r u t from t h e porch f o r crew lunar s u r f a c e operations. ��I n a r e t r a c t e d p o s i t i o n u n t l . 1 a f t e r t h e crew mans t h e LM, t h e landing g e a r struts a r e e x p l o s i v e l y extended and provide l u n a r s u r f a c e landing impact a t t e n u a t l o n W 4 e ma i n s t r u t s a r e f i l l e d with c r u s h a b l e aluminum honeycomb f o r absorbing compression l o a d s . Footpads 37 inches ( 0 . 9 5 m) I n diameter a t t h e end o f each landing g e a r provide v e h i c l e " f l o a t a t i o n " on t h e l u n a r s u r f a c e , . Each pad i s f i t t e d with a l u n a r - a u ~ f a c e s e n s i n g probe which s i g n a l s t h e crew t o s h u t down t h e d e s c e n t engine upon contact with the lunar surface. LM-11 flown on t h e Apollo 10 mission w i l l have a launch weight o f 30,849 pounds. The weight breakdown is as follows: Ascent s t a g e , d r y 4,781 l b s . Descent s t a g e , d r y 4,703 l b s . RCS propel l a n t s DPS propel l a n t s 612 ~ b s . 18,134 l b s . APS p r o p e l l a n t s Lunar Module Systems E l e c t r i c a l Power System -- The LM DC electrical system masts of s i x s i l v e r z i n c primary b a t t e r i e s -- f o u r i n the d e s c e n t s t a g e and two i n t h e a s c e n t s t a g e , each w i t h i t s own e l e c t r i c a l c o n t r o l assembly (ECA) Power f e e d e r s from a l l primary b a t t e r i e s pass through c i r c u i t b r e a k e r s t o e n e r g i z e t h e LM DC buses, from which 28-volt DC power i d distributed through c i r c u i t b r e a k e r s t o a l l LM systems. A? power (117v 400Hz) i s s u p p l i e d by two i n v e r t e r s , e l t h e r o f which can supply s p a c e c r a f t AC load needs t o t h e AC buses. . Environmental Control System -- C o n s i s t s c f t h e atmosphere r e v i t a l i z a t i o n s e e t l o n , oxygen supply n - - and cabin pressure c f ~trcl s e c t i o n , water management,-heat t r a n s p o r t s e c t i o n , and o u t i e t s f o r oxy en and water s e r v i c i n g o f t h e F o r t a b i e L i f e Support, Sys tem TPLSS). �Components of t h e atmosphere r e v i t a l i z a t i o n s e c t i o n are the s u i t c i r c u i t assembly which c o o l s and v e n t i l a t e s t h e pressure garments, reduces carbon d i o x i d e l e v e l s , removes o d c r s , noxious g a s e s and e x c e s s i v e moisture; t h e c a b i n rec l r c u l a t J o n assembly which v e n t i l a t e s and c o n t r o l s c a b i n atmosphere temperatures; and t h e steam f l e x d u c t which v e n t s t o space steam from t h e s u i t c i r c u i t water e v a p o r a t o r . The oxygen supply and cabin p r e s s u r e s e c t i o n s u p p l i e s gaseous axygen t c t h e atmosphere r e v i t a l i z a t i o n s e c t i o n f o r maintaining s u i t and c a b i n p r e s s u r e . The d e s c e n t s t a g e oxygen supply provides d e s c e n t f l i g h t phase and l u n a r s t a y oxygen needs, and t h e a s c e n t s t a g e oxygen supply provides oxygen needs f o r t h e a s c e n t and rendezvous f l i g h t phase. Water f o r d r i n k i n g , cooling, f i r e f i g h t i n g , food p r e p a r a t i o n , and r e f i l l i n g t h e PLSS c o o l i n g water s e r v i c i n g tank i s s u p p l i e d by t h e water management s e c t i o n . The water i s contained i n t h r e e n i t r o g e n - p r e s s u r i z e d bladder-type tanks, one o f 367-pound c a p a c i t y i n t h e d e s c e n t s t a g e and two of 147.5-pound c a p a c l t y i n t h e a s c e n t s t a g e . The heat t r a n s p o r t s e c t i o n h a s primary and secondary water-glycol s o l u t i o n c o o l a n t loops. The primary c o o l a n t l o o p c i r c u l a t e s water-glycol f o r temperature c o n t r o l o f cabin cnd s u i t c l r c u i t oxygen and f o r thermal c o n t r o l of b a t t e r i e s and electronic components mounted on cold p l a t e s and r a i l s . If' the primary loop becomes i n o p e r a t i v e , t h e secondary loop c i r c u l a t e s c o o l a n t through t h e r a i l s and c o l d p l a t e s only. E u i t c i r c u i t c ~ o l i n gd u r i n g secondary c o o l a n t loop o p e r a t i o n ?s provided by the s u i t loop water b o i l e r . Waste h e a t from b o t h l o o p s is v e n t e d overboard by water e v a p o r a t i o n o r subllrnators. Zomunlcation System -- Two S-band t r a n s m i t t e r - r e c e i v e r s , two VHF t r a n s m i t t e r - r e c e i v e r s , a s i g n a l processing assembly, and a s s o c t a t e d s p a c e c r a f t antenna make up t h e LM communications system. The system t r a n s m i t s and r e c e i v e s v o i c e , t r a c k i n g and ranglng d a t a , and t r a n s m i t s t e l e m e t r y d a t a on 281 measurements and TV s i g n a l s t o t h e ground. Voice communications between t h e TLM and ground s t a t i o n s i s by S-band, and between t h e LN and CSM voice i s on VHF. �Real-time commands t o t h e l u n a r module are r e c e i v e d and encoded by t h e d i g i t a l u p l i n k assembly--a black box t i e d i n t o the S-band r e c e i v e r . The d i g i t a l u p l i n k assembly w i l l be used on Apollo 10 t o arm and f i r e thg a s c e n t propulsion system f o r the unmanned APS d e p l e t i o n burn following f i n a l docking and LM j e t t i s o n . LM-4 w i l l b e t h e l a s t s p a c e c r a f t t o be f i t t e d with equipment f o r a c c e p t i n g r e a l - t i m e commands from t h e ground. The d a t a s t o r a g e e l e c t r o n i c s assembly (DSEA) i s a f o u r channel voice r e c o r d e r with timing s i g n a l s w i t h a 10-hour recording c a p a c i t y which w i l l be brought back i n t o t h e CSM for r e t u r n t o Earth. DSEA r e c o r d i n g s cannot be "dumped" t o ground s t a t i o n s . rsJI antennas a r e one 26-inch diameter p a r a b o l i c S-band s t e e r a b l e antenna, two S-band i n f l i g h t antennas and two VHF I n f l i g h t antennas. Guidance, Navigation and Control System -- Comprised o f six s e c t i o n s : idance and n a v i g a t l o n s e c t i o n (PGNS), a b o r t guidance radar section, control electronics s e c t i o n (CES), and o r b i t a l r a t e d r i v e e l e c t r o n i c s f'or Apollo and LM (ORDEAL). * The PGNS i s a n i n e r t i a l system a i d e d by t h e alignment o p t i c a l t e l e s c o p e , a n i n e r t i a l measurement u n i t , and t h e r e n dezvous and landing r a d a r s . The system provides i n e r t i a l r e f e r e n c e d a t a f o r computations, produces i n e r t fa1 alignment r e f e r e n c e by feeding o p t i c a l s i g h t i n g data i n t o the LM guidance computer, d i s p l a y s p o s i t i o n and v e l o c i t y d a t a , computes TA-CSM rendezvous d a t a from r a d a r i n p u t s , c o n t r o l s a t t i t u d e and t h r u s t t o maintain d e s i r e d LM t r a j e c t o r y , and c o n t r o l s d e s c e n t engine t h r o t t l i n g and gimbaling. * The AGS i s an independent backup s y s t e m f o r t h e PGNS, having i t s own i n e r t i a l s e n s o r and computer. *. The r a d a r s e c t i o n i s made up of t h e rendezvous radar which provldes CSM range and range r a t e , and l i n e - o f - s i g h t a n g l e s f o r maneuver computation t o t h e LM guidance computer; t h e landing r a d a r which provide a l t i t u d e and v e l o c i t y data t o t h e TSJI guidance computer during l u n a r l a n d i n The rendezvous radar has an o p e r a t i n g range from 80 f e e t t o 4 6 n a u t i c a l miles. The range t r a n s f e r tone assembly, u t i l i z i n g VKF e l e c t r o n i c s , i s a p a s s i v e responder t o t h e CSM VHF ranging device and i s a backup t o the rendezvous r a d a r . d �+ 217e CES c o n t r o l s I24 a t t i t u d e and t r a n s l a t i o n about a l l axes. I t a l s o c o n t r o l s by PGNS command t h e automatic o p e r a t i o n of t h e a s c e n t and d e s c e n t engines., and t h e r e a c t i o n c o n t r o l t h r u s t e r s . Manual a t t j t u d e c o n t r o l l e r and t h r u s t - t r a n s l a t i o n controller commands are a l s o handled by t h e CES. * ORDEAL, d i s p l a y s on t h e f l i g h t d i r e c t o r a t t i t u d e i n d i c a t o r , is t h e computed l o c a l v e r t i c a l i n t h e p i t c h a x i s during circular, Earth o r lunar o r b i t s . Reaction C o n t r o l System -- The LM has f o u r RCS engine c l u s t e r s o f four 100-pound (45.8 kg) t h r u s t engines each which use helium-pressurized hypergollc p r o p e l l a n t s . The o x l d l z e r 1s n i t r o g e n t e t r o x i d e , f u e l i s Aerozlne 50 ( 5 0 / 5 0 blend of hydrazine and unsymmetrical dimethyl h y d r a z i n e ) . P r o p e l l a n t plumblng, valves and p r e s s u r i z i n g components are i n two p a r a l l e 1, independent s y s terns, each f e e d i n g h a l f the e n g i n e s i n each c l u s t e r . E i t h e r system is capable o f m a i n t a i n l n g a t t i t u d e a l o n e , b u t if one supp3.y system f a i l s , a p r o p e l l a n t c r o s s f e e d a l l o w s one system t o s u p p l y a l l 16 engines, A d d i t i o n a l l y , i n t e r c o n n e c t valves permit t h e RCS system t o draw from a s c e n t engine p r o p e l l a n t t a n k s . The engine c l u s t e r s a r e mounted on o u t r i g g e r s 90 degrees a p a r t on t h e a s c e n t s t a g e . The RCS provides s m a l l s t a b i l i z i n g Impulses d u r i n g a s c e n t and d e s c e n t burns, c o n t r o l s LM a t t i t u d e d u r i n g maneuvers, and produces t h r u s t f o r s e p a r a t i o n , and ascent/deseent engine tank u l l a g e . The system may be o p e r a t e d i n e i t h e r t h e p u l s e o r s t e a d y - s t a t e modes. Descent Propulsion System -- Maximum r a t e d t h r u s t o f t h e d e s c e n t engine i s g,tjq(O pounds (4,380.9 kg) and is t h r o t t l e a b l e between 1,050 pounds (476.7 kg) and 6,300 pounds (2,860.2 kg). The engine can be gi-nbaled s i x degrees i n any d i r e c t i o n f o r o f f s e t c e n t e r of g r a v i t y trimming. P r o p e l l a n t s are heliumpressurized Aerozine 50 and n i t r o g e n t e t r o x i d e . -- The 3,500-pound (1,589 kg) Ascent Propulsion System t h r u s t a s c e n t engine i s n o t gimbaled and performs a t f u l l t h r u s t . The engine remains dormant u n t i l a f t e r t h e a s c e n t s t a g e s e p a r a t e s f r o & t h e d e s c e n t s t a g e . P r o p e l l a n t s are the same as are burned by the RCS engines and t h e d e s c e n t engine. Caution and Warning, C o n t r o l s and Displays -- These two systems have t h e same f u n c t i o n aboard t h e lunar module as t h e y do aboard t h e command module. (see CSM systems s e c t i o n . ) �Tracking and Docking Lights -- A flashing tracking l i g h t (once per second, 20 milliseconds duration) on t h e front face of the lunar module i s an a i d f o r contingency CSM-active rendezvous IH rescue. V i s i b i l i t y ranges from 400 n a u t i c a l miles through the CSM sextant t o 130 miles with the naked eye. Five docking l i g h t s analagous t o a i r c r a f t running l i g h t s a r e mounted on the IN f o r CSM-active rendezvous: two forward yellow l i g h t s , a f t white light, p o r t red l i g h t and starboard green l i g h t . All docking l i g h t s have about a 1,000-foot visibility. �SATURN V LAUNCH VEHICLE DESCRIPTION AND OPERATION The S a t - ~ r nV, 363 feet t a l l with the Apollo s p a c e c r a f t i n place, g e n e r a t e s enough t h r u s t t o place a 125-ton payload i n t o a lO5-nm c i r c u l a r o r b i t of t h e Earth, It can boost about 50 t o n s t o l u n a r o r b i t . The t h r u s t of t h e t h r e e prop u l s i v e s t a g e s range Prom almost 7.6 m i l l i o n pounds f o r t h e booster t o 230,000 pounds f o r t h e t h i r d s t a g e a t operating a l t i t u d e , Including t h e instrument u n i t , t h e launch v e h i c l e without t h e s p a c e c r a f t is 281 feet t a l l , F i r s t Stage The first s t a g e (s-IC) w a s developed j o i n t l y by t h e National Aeronauties and Space Administration's Marshall Space p l i g h t Center, Huntsville, A l a . and t h e Roeing Co. The Marshall Center assembled f o u r S-IC stages: a s t r u c t u r a l test model, a s t a t i c test version, and t h e first two f l i g h t stages. Subsequent f l i g h t s t a g e s are assembled by Boeing a t t h e Michoud Assembly F a c i l i t y , New Orleans, The S-IC s t a g e destined f o r t h e Apollo 10 mission w a s t h e second f l i g h t booster s t a t i c t e s t e d a t t h e NASA-Mississippi Test F a c i l i t y . The f i r s t S-IC test a t MTF w a s on May 11, 1967, and t h e t e s t of t h e second S-IC t h e r e -- t h e booster f o r Apollo 10 -- was completed Aug. 9, 1967. E a r l i e r f l i g h t s t a g e s were s t a t i c f i r e d a t t h e Marshall Center. The S-IC s t a g e boosts t h e space v e h i c l e t o a n a l t i t u d e of 35.8 nm a t 50 nm downrange and i n c r e a s e s t h e v e h i c l e ' s v e l o c i t y t o 5,343 knots i n 2 minutes 40 seconds of powered flight. It then s e p a r a t e s and f a l l s i n t o t h e A t l a n t i c Ocean about 351 nm downrange (30 degrees North l a t i t u d e and 74 degrees West longitude) about nine minutes a f t e r l i f t o f f . Normal propellant flow rate t o t h e f i v e F-1 engines i s Four of t h e engines a r e mounted on a r i n g , each 90 degrees from i t s neighbor, These f o u r are gimballed t o c o n t r o l t h e r o c k e t ' s d i r e c t i o n of P l i g h t . The f i f t h engine i s mounted r i g i d l y i n t h e center. 29,522 pounds p e r second. Seccnd Stage The second stage (S-11), l i k e the t h i r d stage, u s e s high performance 3-2 engines t h a t burn l i q u i d oxygen and l i q u i d hydrogen. The s t a g e ' s purpose is t o provide s t a g e boost n e a r l y t o Earth o r b i t , �SATURN V LAUNCH VEHICLE 5,031,023 LBS. FUELED 294,200 LBS .DRY / LM \ PROPE LLANTS l NSTRUMENT LIQUID OXYGEN (3,258,280 LBS.) RP-I (KEROSENE) (1,417,334 LBS .) (S- IVB . 1,074,590 isS FUELED 84,367 LBS. DRY tf / SECOND STAGE PROPELLANTS LIQUID OXYGEN (829,114 LBS .) LIQUID HYDROGEN . 261,836 LBS FUELED ST STAGE (S-IC) PROPE LLANTS LIQUID OXYGEN (190,785 LBS .) LlQUlD HYDROGEN (43,452 LBS .) NOTE: WEIGHTS AND MEASURES GIVEN ABOVE ARE FOR THE N O M I N A L VEHICLE CONFIGURATION FOR APOLLO 10. THE FIGURES M A Y VARY SLIGHTLY DUE TO CHANGES BEFORE LAUNCH TO MEET C H A N G I N G CONDITIONS. �A t outboard engine cutoff, the S-I1 separates and, following a b a l l i s t i c t r a j e c t o r y , plunges i n t o t h e Atlantic mean abmat 2,400 nm downrange from Kennedy Space Center (31 degrees ~ o p t hl a t i t u d e and 34 degrees west longitude) about 20 minutes a f t e r l i f t o f f , Five J-2 enaines power t h e S-11, The o u t e r four engines a r e equally spaced on a 17.5-foot diameter c i r c l e . These four engines may be glmbaled through a plus o r mlnus sevendegree square p a t t e r n f o r t h r u s t vector control. A s on t h e first stage, t h e c e n t e r engine (number 5) i s mounted on the s t a g e c e n t e r l i n e and is f i x e d i n position, The S - I 1 c a r r i e s t h e rocket t o an a l t i t u d e of about 101,6 nm and a distance of some 888 nm downrange, Before burnout, t h e vehicle w l l l be moving a t a speed of 13,427 knots, The outer 5-2 engines w i l l burn 6 minutes 32 seconds during t h i s powered phase, but t h e c e n t e r engine w i l l be c u t off a t 4 minutes 59 seconds of burn tine, The Space Division of North American Rockwell Corp, builds t h e S-I1 a t Seal Beach, Calif, The c y l i n d r i c a l vehicle i s made up of t h e forward s k i r t t o which t h e t h i r d s t a g e attaches, t h e l i q u i d hydrogen tar&, the l i q u i d oxygen tank (separated from t h e hydrogen tank by a common bulkhead), t h e t h r u s t s t r u c t u r e on which t h e engines a r e mounted and an i n t e r stage s e c t i o n t o which t h e first stage attaches. The common bulkhead between t h e two tanks i s heavily insulated. The S-I1 f o r Apollo 10 was s t a t i c t e s t e d by North American Rockwell a t the NASA-Nississippi Test F a c i l i t y on Aug. 9, 1968, This stage was shipped t o the t e s t s i t e v i a t h e Panama Canal f o r the t e s t f i r i n g , Third Stage The Ehird stage (s-M3) was developed by t h e McDonnell Douglas Astronautics Co, a t Huntington Beach, C a l i f , A t Sacramento, Calif., t h e stage passed a s t a t i c f i r i n g t e s t on O e t , 9, 1967 a s p a r t of the preparation f o r t h e Apollo 10 mission. The stage was flown d i r e c t l y t o t h e NASA-Kennedy Space Center, Measuring 58 f e e t 4 inches long and 21 feet 8 inches i n diameter, t h e S - N B weighs 25,750 pounds Qry, A t first i g n i t i o n , i t weighs 261,836 pounds, The i n t e r s t a g e s e c t i o n weighs an a d d i t i o n a l 8,081 pounds, The s t a g e 1s 5-2 engine burns l i q u i d oxygen and l i q u i d hydrogen, �The s t a g e provides propulsion t w l c e during t h e Apollo 10 mission, The first burn occurs e d i a t e l g after separat%on from the S-XI, It w i l l last long enough (156 seconds) to Znsert t h e v e h i c l e and s p a c r c r a f t i n t o a c i r c u l a r W r t h parking o r b i t a t about 52 degrees West longitude and 32 degrees North l a t i t u d e , The second bum, which begins a t 2 hours 33 minutes 25 seconds after l i f t o f f ( f o r first opportunity t r a n s l u n a r inj e c t i o n ) o r 4 hours 2 minutes 5 seconds ( f o r second TLI opport u n i t y ) , w i l l plaee t h e stage, instrument u n i t , and spacecraft i n t o t r a n s l u n a r t r a J e c t o r y . "The burn w i l l continue u n t i l proper "nI end conditions are m e t , The f u e l tanks contain 4?,452 pounds of l i q u i d hydrogen and 190,785 pounds of IiquLd oxygen a t first i g n i t i o n , totalling 234,237 pounds of propellants, I n s u l a t i o n between t h e two tanks i s necessary because t h e l i q u i d oxygen, a t about 293 degrees below zero I?, is warm enough, r e l a t i v e l y , t o heat t h e l i q u i d hydrogen, a t 423 degrees below zero F, r a p i d l y and cause i t t o t u r n I n t o gas. Instrument Unit The instrument u n i t (IN) i s a cylinder t h r e e f e e t high and 21 f e e t 8 inches i n diameter, It weighs 4,254 pounds and contains t h e guidance, navigation, and c o n t r o l equipment which w i l l s t e e r t h e vehicle through its Earth o r b i t s and i n t o t h e f i n a l t r a n s l u n a r i n j e c t i o n maneuver, The IU a l s o contains telemetry, communieations, tracking, and crew s a f e t y systems, along with i t s own supporting e l e c t r i c a l power and environmental c o n t r o l systems, Components making up the "brain" of t h e Saturn V are mounted on cooling panels fastened t o t h e i n s i d e surface of t h e instrument u n i t skin, The "cold p l a t e s " a r e p a r t of a system t h a t removes heat by c i r c u l a t i n g cooled fluid through a heat exchanger t h a t evaporates water from a separate s u p p l y i n t o t h e vacuum of space. The six maJor systems of the instrument u n i t a r e s t r u c t u r a l , thermal control, guidance and control, measuring and telemetry, r a d i o frequency, and e l e c t r i c a l . The instrument u n i t provides navigation, guidance, and c o n t r o l of t h e vehicle; measurement of vehicle performance and environment; data transmission with ground s t a t i o n s ; radio tracking of t h e vehicle; checkout and monitoring of vehicle functions; i n i t i a t i o n of stage functional sequencing; detection f o emergency s i t u a t i o n s ; generation and network d i s t r i b u t i o n of e l e c t r i c power system operation; and p r e f l i g h t checkout and launch and f l i g h t operations. �A path-adaptive guidance scheme i s used i n t h e Saturn A programmed t r a j e c t o r y i s used i n t h e V instrument u n i t . i n i t i a l launch phase with guidance beginning only a f t e r t h e v e h i c l e h a s l e f t t h e atmosphere. This i s t o prevent movements t h a t might cause t h e v e h i c l e t o break a p a r t while a t t e m p t i n g t o compensate f o r winds, J e t streams, and g u s t s encountered i n t h e atmosphere. If such a i r c u r r e n t s d i s p l a c e t h e v e h i c l e from t h e optimum t r a j e c t o r y i n climb, t h e v e h i c l e d e r i v e s a new traJ e c t o r y . C a l c u l a t i o n s are made about once each second througho u t t h e f l i g h t . The launch v e h i c l e d i g i t a l computer and d a t a a d a p t e r perform t h e n a v i g a t i o n and guidance computations. -- The ST-124M i n e r t i a l platform t h e h e a r t of t h e navigat i o n , guidance and c o n t r o l system -- provides space-fixed r e f e r e n c e c o o r d i n a t e s and measures a c c e l e r a t i o n a l o n g t h e t h r e e mutually perpendicular a x e s of t h e c o o r d i n a t e system. I n t e r n a t i o n a l Buuiness Machines Corp., i s prime c o n t r a c t o r f o r t h e instrument u n i t and i s t h e s u p p l i e r of t h e guidance s i g n a l processor and guidance computer. Major s u p p l i e r s of instrument u n i t components a r e : E l e c t r o n i c Communications, Inc., c o n t r o l computer; Bendix Corp., ST-124M i n e r t i a l platform; and IBM Federal Systems Division, launch v e h i c l e d i g i t a l comp u t e r and launch v e h i c l e data a d a p t e r . Propulsion The 4 1 r o c k e t engines of t h e S a t u r n V have t h r u s t r a t i n g s ranging from 72 pounds t o more t h a n 1.5 m i l l i o n pounds. Some e w i n e s burn l i q u i d p r o p e l l a n t s , o t h e r s use s o l i d s . The f i v e F-1 engines i n t h e f i r s t s t a g e burn RP-1 (kerosene) and l i q u i d oxygen. Fngfnes i n t h e f i r s t s t a g e develop approximately 1,536,197 pounds of t h r u s t each a t l i f t o f f , b u i l d i n g up t o 1,822,987 pounds b e f o r e c u t o f f . The c l u s t e r of f i v e engines g i v e s t h e first s t a g e a t h r u s t range from 7,680,982 m i l l i o n pounds a t l i f t o f f t o 9,114,934 pounds just b e f o r e c e n t e r engine c u t o f f . The F-1 engine w e i ~ h salmost 10 t o n s , i s more t h a n 18 f e e t h i a h and has a n o z z l e - e x i t diameter of n e a r l y 14 f e e t . The F-1 undergoes s t a t i c t e s t i n g f o r a n average 650 seconds i n q u a l i f y i n g f o r t h e 160-second run d u r i n g t h e S a t u r n V f i r s t s t a g e b o o s t e r phase. The engine consumes almost t h r e e t o n s of p r o p e l l a n t s p e r second. �The first stage of t h e Saturn V f o r t h i s mission h a s e i g h t other rocket motors, These are t h e s o l i d - f u e l r e t r o rockets which w i l l slow and separate t h e s t a g e from t h e second stage, Each rocket produces a t h r u s t of 87,900 pounds f o r 0.6 second. The main propulsion f o r t h e seaend stage i s a c l u s t e r of f i v e 3-2 engines burning l i q u i d hydrogen and l i q u i d oxygen, Each engine develops a mean t h r u s t of more than 205,000 pounds a t 5,0:1 mixture r a t i o ( v a r i a b l e from 184,000 t o 230,000 i n pbases of f l i g h t ) , giving t h e stage a t o t a l mean t h r u s t of more than a m i l l i o n pounds. Designed t o operate i n t h e hard vacuum of space, t h e 3,500-pound 5-2 i s mere e f f i c i e n t than t h e F-1 because it burns t h e high-energy f u e l hydrogen. F-1 and 5-2 engines are produced by t h e Rocketdyne Division of North American Roekwell Corp . The second s t a g e has f o u r 21,000-pound-thrust s o l i d f u e l rocket engines. These a r e t h e u l l a g e rockets mounted on t h e S-IC/S-11 i n t e r s t a g e section, These rockets f i r e t o s e t t l e l i q u i d propellant i n t h e bottom of the main tanks and help a t t a i n a "clearn" separation from t h e first stage, they remain with t h e I n t e r s t a g e when it drops away a t second plane separation. Four retrorockets are located I n t h e S-IVB a f t i n t e r s t a g e (which never separates from the S-11) t o separate t h e S-I1 f r m the S-IVB p r i o r t o S-TVB i g n i t i o n . Eleven rocket engines perform various functions on t h e t h i r d stage. A s i n g l e 5-2 provides t h e main propulsive force; t h e r e a r e two J e t t i s o n a b l e main u l l a g e rockets and e i g h t smaller engines i n t h e two a u x i l i a r y propulsion system modules. Launch Vehicle Instrumentation and Comrnunloation A t o t a l of 2,342 measurements w i l l be taken I n f l i t on t h e Saturn V launch vehicle: 672 on the first stage, 9 6 on '?f the second stage, 386 o n t h e t h i r d stage, and 298 on t h e i n s t r u ment u n i t . The Saturn V has 16 telemetry systems: six on t h e first stage, s i x on t h e second stage, one on the t h i r d stage and t h r e e on the instmment u n i t . A C-band system and command system are a l s o on t h e instrument u n i t , Each powered stage has a range s a f e t y system a s on previous f l i g h t s , �S-IVB R e s t a r t The t h i r d s t a g e of t h e Saturn V rocket f o r t h e Apollo 10 mission w i l l burn t w i c e i n apace, The second b u m places t h e spacecraft on t h e t r a n s l u n a r t r a j e c t o r y , =Thefirst opportunity f o r t h i s burn is a t 2 hours 33 minutes and 25 seconds after JLauach,, The second opportunity f o r TLI begins a t 4 hours 2 minutes and 5 seconds after l i f t o f f , The primary p r e s s u r i z a t i o n system of the propellant tanks f o r t h e 5-nr13 restart uses a helium heater, I n t h i s sytem, nine helium storage spheres i n t h e l i q u i d hydrogen tank contain gaseous helium charged t o about 3,000 p s i , This h e f h m is passed through t h e h e a t e r wh%chh e a t s and expands t h e gas before it e n t e r s t h e propellant tanks, The h e a t e r operates on hydrogen and oxygen gas from t h e main propellant tanks, The backup system c o n s i s t s of f i v e ambient helium spheres mounted on t h e s t a g e t h r u s t s t r u c t u r e . This system, controlled by t h e f u e l repressurization c o n t r o l module, can repressurize %he tanks i n case t h e primary system fails, !Phe r e s t a r t w i l l use t h e primary system. If t h a t system fails, t h e backup system w i l l be used. The t h i r d stage f o r Apollo 10 w i l l not be Ignited f o r a t h i r d burn a s on Apollo 9, Following spacecraft separation i n t r a n s l u n a r t r a j e c t o r y , the s t a g e w i l l undergo the normal 5-2 engine chilldown sequence, stopping j u s t short of r e i g n i t i o n , On Apollo 10 t h e r e i s no requirement f o r a t h i r d burn, and t h e r e w i l l not be s u f f i c i e n t propellants aboard, most of t h e f u e l s having been expended during the tranalunar i n j e c t i o n maneuver, Differences i n Apollo 9 and Apollo 10 Launch vehicles Two modifications r e s u l t i n g from problems encountered during the second Saturn V f l i g h t were incorporated and proven successful an t h e t h i r d and f o u r t h Saturn V missions. The new helium prevalve c a v i t y pressurization system w i l l again be flown on the first (s-IC) stage of Apollo 10, New augmented spark I g n i t e r l i n e s which f l e w on t h e engines of t h e two upper s t a g e s of Apollo 8 and 9 w i l l again be used on Apollo 10, �The major first s t a g e (s-IC) d i f f e r e n c e s between Apollo 9 and 10 a r e : 1. pounds, Dry weight was reduced from 295,600 t o 294,200 2. Weight a t ground i g n i t i o n increased from 5,026,200 t o 5,031,023 pounds. 3. Instrumentation measurements were increased from 666 t o 672. S-I1 s t a g e changes a r e : 1. Nominal vacuum t h r u s t f o r 5-2 engines i n c r e a s e w i l l change maximum s t a g e t h r u s t from 1,150,000 t o 1,168,694 pounds. 2. The approximate empty weight of t h e S-I1 has been reduced from 84,600 t o 84,367 pounds. The S-IC/S-11 i n t e r stage weight was reduced from 11,664 t o 8,890 pounds. 3. Approximate s t a g e g r o s s l i f t o f f weight was increased from 1,069,114 t o 1,074,590 pounds. 4. to 986. 975 Instrumentation measurements increased i ~ m Major d i f f e r e n c e s on t h e S-IVB s t a g e of Apollo 9 and 10 a r e : S - N B dry s t a g e weight increased from 25,300 t o T h i s does n o t include t h e 8,084-pound i n t e r stage section. 1. 25,750 pounds. 2. S-NB 8r o s s s t a g e weight a t l i f t o f f increased from 259,337 t o 261, 36 pounds. 3. Instrumentation measurements were increased from 296 t o 386. �APOLLO 10 CREW L i f e Support muipment - Space S u i t s Apollo 10 crewmen w i l l wear two versions of t h e Apollo space s u i t : an i n t r a v e h i c u l a r p r e s s u r e garment assembly worn by t h e command module p i l o t and t h e e x t r a v e h i c u l a r press u r e garment assembly worn by the commander and the lunar module p i l o t , Both versions a r e b a s i c a l l y i d e n t i c a l except t h a t t h e e x t r a v e h i c u l a r version has an i n t e g r a l thermal/ meteoroid garment over the b a s i c s u i t . From the s k i n o u t , the b a s i c pressure garment c o n s i s t s of a nomex comfort l a y e r , a neoprene-coated nylon pressure bladder and a nylon r e s t r a i n t l a y e r , The o u t e r l a y e r s of t h e i n t r a v e h i c u l a r s u i t a r e , from t h e inside o u t , nomex and two l a y e r s of Tef lon-coated Beta c l o t h . The e x t r a v e h i c u l a r i n t e g r a l thermal/meteoroid cover c o n s i s t s o f a l i n e r o f two l a y e r s of neoprene-coated nylon, seven l a y e r s o f ~ e t a / K a p t o nspacer laminate, and an o u t e r l a y e r o f Teflon-coated Beta f a b r i c . The e x t r a v e h i c u l a r s u i t , t o g e t h e r with a l i q u i d cooling garment, p o r t a b l e l i f e support system (PLsS), oxygen purge system, e x t r a v e h i c u l a r v i s o r assembly and o t h e r components make up t h e e x t r a v e h i c u l a r m o b i l i t y u n i t (EMU). The EMD provides an e x t r a v e h i c u l a r crewman with l i f e support f o r a , f o u r hour mission o u t s i d e t h e l u n a r module without r e p l e n i s h i n g expendables. EPlIZ t o t a l weight i s 183 pounds. The i n t r a vehicular suit weighs 35.6 pounds. Liquid cooling garment--A k n i t t e d nylon-spandex garment w i t h a network of p l a s t i c tubing through which cooling watelr from the PLSS i s c i r c u l a t e d . It i s worn next t o the s k i n and r e p l a c e s t h e constant wear-garment during EVA only. Portable l i f e support system--A backpack supplying oxygen a t 3.9 p s i and cooling water t o t h e l i q u i d cooling garment. Return oxygen i s cleansed o f s o l i d and gas contaminants by a l i t h i u m hydroxide canister. The PLSS i n c l u d e s communications and telemetry equipment, d i s p l a y s and c o n t r o l s , and a main power supply. The PLSS i s covered by a thermal i n s u l a t i o n Jacket. (one stowed i n LM). Oxygen purge sys tern--Mounted a t o p t h e PLSS, the oxygen purge system provides a contingency 30-minute supply of gaseous oxygen i n two two-pound b o t t l e s p r e s s u r i z e d t o 5,880 p s i a . The system may a l s o be worn s e p a r a t e l y on the f r o n t of t h e pressure garment assembly t o r s o , It serves as a mount f o r t h e VHF antenna f o r the PLSS. (Two stowed i n LM) . ��HOLD DOWN STRAP ACCESS FLAP L U V Y lAPt SHOULDER DISCONNECT \ CONNECTOR COVER CHEST COVER SUNG LASSES +--SHELL -+iNSUlATION +-LINER PENLIGHT POCKET TYPICAL CROSS SECTION LM RESTRAINT BELT ASSEMBLY LITY POCKET SLlDE FASTENER DATA LIST POCKET WRIST CLAMP ASSIST STRAP URINE TRANSFER CONNECTOR AND BIOMEDICAL INJECTION P ! LOOP TAPE L U U P IAPE ACTIVE DOSIMETER POCKET ENTRANCE SLIDE FASTENER FLAP a ------I/, '\I , L ASSISTS SCISSORS POCKET CHECKLIST POCKET �-56~- BACKPACK SUPPORT STRAPS OXYGEN PURGE SYST CKPACK CONTROL BOX SYSTEM ACTUATOR PENLIGHT POCKET CONNECTOR COVER COMMUNICATION, VENT1 LATI ON, AND LIQUI D COOLING PURGE SYSTEM LM RESTRA lNT R ING INTEGRATED THERMAL METEOR0 I D GARMENT UR INE TRANSFER CONNECTOR, DOS IMETER ACCESS FLAP AND DONN I NG LANYARD POCKET UTILITY POCKET �Extravehicular v i s o r assembly--A polycarbonate s h e l l and two v i s o r s with thermal c o n t r o l and o p t i c a l coatings on them, The EVA v i s o r i s attached over t h e pressure helmet t o provide impact, micrometeoroid, thermal and l i g h t protection t o t h e EVA crewman. Extravehicular gloves--Built of an o u t e r s h e l l of Chromel-R f a b r i c and thermal i n s u l a t i o n t o provide protect i o n when handling extremely hot and cold o b j e c t s , he f i n g e r t i p s a r e made of s i l i c o n e rubber t o provide the crewman more sensitivity. A one -piece cons tan%-wear garment, similar t o " long johns", is worn as an undergarment f o r the space suit in i n t r a vehicular operations and f o r the i n f l i g h t coveralls. The garment 5s porous-knit cotton with a waist-to-neck zipper f o r doming. Biomedical harness a t t a c h points are provided. During periods out of the space s u i t s , crewmen w i l l wear two-piece Teflon f a b r i c i n f l i g h t c o v e r a l l s f o r warmth and f o r pocket stowage of personal items. Communications c a r r i e r s ( " ~ n o o p yh a t s " ) with redundant microphones and earphones a r e worn w i t h the pressure helmet; a lightweight headset i s worn with the i n f l i g h t coveralls, Meals The Apollo 10 crew has a wide Pange of food items from which t o s e l e c t t h e i r d a i l y mission space menu, More than 60 items comprise the food s e l e c t i o n l i s t of freeze-dried rehydratable foods. I n addition, one "wet pack" meal-per-man per-day w i l l be stowed f o r a t o t a l of 27. These meals, cons i s t i n g of foil-wrapped beef and potatoes, ham and potatoes and turkey chunks and gravy, a r e s i m i l a r t o the Christmas meals c a r r i e d aboard Apollo 8 and can be eaten with a spoon. Water f o r drinking and rehydrating food is obtained from three sources i n the command module a dispenser f o r drinking water and two water spigots a t the food preparation s t a t i o n , one supplying water a t about 155 degrees F., the other a t about 55 degrees F, The potable water dispenser s q u i r t s water continuously as long a s the t r i g g e r i s held down, and the food preparation s p i g o t s dispense water i n one-ounce increments. -- �Command module potable water i s supplied from s e r v i c e module f u e l ce 11 byproduct water, Three one - p i n t " p i c n i c Jugs", o r p l a s t i c bags, w i l l be stowed aboard Apollo 10 f o r drinking water, Each crewman once a day w i l l f i l l a bag with water and then s p i n it up t o s e p a r a t e t h e suspended hydrogen gas from t h e water so t h a t he w i l l have hydrogenl e s s water t o d r i n k t h e following day. The suspended hydrogen i n t h e f u e l c e l l byproduct water has caused i n t e s t i n a l d i e comfort t o crewmen i n previous Apollo missions. A continuous-feed hand water dispenser similar t o t h e one i n the command module i s used aboard the l u n a r module f o r cold-water rehydration of food packets stowed aboard t h e M. A f t e r water has been i n j e c t e d i n t o a food bag, it is kneaded f o r about t h r e e minutes, TZle bag neck i s then c u t o f f and t h e food squeezed i n t o t h e crewman's mouth. A f t e r a meal, germicide p i l l s attached t o t h e o u t s i d e of the. food bags a r e placed i n the bags t o prevent fermentation and gas formation. The bags a r e then r o l l e d and stowed i n waste d i s p o s a l compartments, The day-by-day, meal-by-meal Apollo 10 menu f o r each crewman f o r both t h e command module and the l u n a r module i s l i s t e d on t h e following pages. �MEAL Day 2, 6, 1 0 Day I*, 5, 9 A Peaches Bacon Squares (8) Cinn Tstd Bread Cubes (4) Grapefruit Drink Orange Drink F r u i t Cocktail Sugar Coated Corn Flakes Bacon Squares (8) Grapefruit Drink Grape Drink B Salmon Salad Chicken & Rice** Sugar Cookie Cubes (4) Cocoa Grape Punch P o t a t o Soup Chicken & Vegetables Tuna Salad Pineapple Fruitcake (4) Orange Drink S (D I Day 3, 7, 11 Peaches Bacon Squares (8) Strawberry Cubes (4) Cocoa Orange Drink Cream of Chicken Soup (Turkey & Gravy Wet Pack) Butterscotch Pudding Brownies ( 4 ) G r a p e f r u i t Drink - F r u i t Cocktail Sausage P a t t i e s Bacon Squares (8) Cocoa Grape Drink P o t a t o Soup Pork & Scalloped P o t a t o a Applesauce Orange Drink & \O I C - (Beef & Potatoes Wet pack) Cheese Cracker Cubes (4) Chocolate Pudding Grange-Grapefruit Drink *Day 1 c o n s i s t s of Meal C only **Nev spoon-bowl package Spaghetti & Meat Sauce** (Ham & Potatoes Wet pack) Banana Pudding Pineapple-Grapefruit Drink - Pea Soup Beef StewY* Chicken Salad Chocolate Cubes (4) Grape Punch Shrimp Cocktail Chicken Stew** Turkey B i t e s (4) Date Fruitcake ( 4 ) Orange-Grapefruit Drink �APOLLO 10 (YOUNG) MEAL Day l*,5 , 9 Day 2, 6, 10 A Peaches Bacon Squares (8) Cinn Tstd Bread Cubes ( 4 ) Grapefruit' Drink Orange Drink F r u i t Cocktail Sugar Coated Corn Flakes Brownies ( 4 ) Grapefruit Drink Grape Drink B Salmon Salad Chicken & Rice** Sugar Cookie Cubes (4) Cocoa Grape Punch Potato Soup Tuna Salad Chicken & Vegetables Pineapple Fruitcake ( 4 ) Pineapple-Grapefruit Drink '3 CD I C - (Beef & Potatoes Wet pack) Cheese Cracker Cubes ( 4 ) Chocolate Pudding Orange-Grapefruit Drink *T)sy 1 c o n s i s t s o f Meal C: only **Nev spoon-Sow1 psckage S p a g h e t t i & Meat SauceY* (Ham & P o t a t o e s Wet pack) Banana Pudding Grange Drink - Day 3, 7, 11 Peaches Bacon Squares (8) Strawberry Cubes ( 4 ) Cocoa Orange Drink Cream of Chicken Soup (Turkey & Gravy - Wet Pack) Butterscotch Pudding Grapefruit Drink Beef StewY* Chicken Salad Corn Chowder Chocolate Cubes ( 4 ) Grape Punch F r u i t Cocktail Sausage P a t t i e s Bacon Squares (8) Cocoa Grape Drink Pea Soup Pork & Scalloped P c t s t o e s Applesauce Orange D r i n k Shrimp Cocktail Chicken Stew** Turkey Bites ( 4 ) Date Fruitcake (4) Orange-Grapef r u i t Drink �MEAL Uay l * , 5, 9 Day 2, 6, 1 0 A Peaches Bacon Squares (8) Cinn T s t d Bread Cubes (4) Orange Drink Orange-Pineapple Drink F r u i t Cocktail Sugar Coated Corn F l a k e s Bacon Squares (8) Orange Drink Grape Drink B Salmon S a l a d Chicken & Rice** Sugar Cookie Cubes ( 4 ) Cocoa Grape Punch P o t a t o Soup Tuna Salad Chicken & Vegetables Brownies (4) Orange-Grapefruit Drink Day 3, 7, 11 Peaches Bacon Squares (8) Strawberry Cubes ( 4 ) Cocoa Orange Drink Cream of Chicken Soup (Turkey & Gravy Wet pack) Cinn T s t d Bread Cubes ( L ) B u t t e r s c o t c h Pudding Pineapple-Grapefrui t Drink - Day 4, 8 F m i t Cocktail Sausage P a t t i e s Bacon Squares (8) Cocoa Grape Drink P o t a t o Soup Pork & Scalloped P o t a t o e s Applesauce Orange Drink Y I ui I-' I C Cream of Chicken Soup Wet pack) (Beef & P o t a t o e s Cheese Cracker Cubes ( 4 ) F r u i t Cocktail Orange-Grapefruit Drink - *Day 1 c o n s i s t s of Meal C only **New spoor-'mwl package S p a g h e t t i & Meat Sauce** (Ham & P o t a t o e s Wet pack) Banana Pudding Orange Drink - Pea Soup Chicken S a l a d Beef Stew** Grape Punch Shrimp C o c k t a i l Chicken Stew** Turkey B i t e s (6) Chocolate Cubes (6) Orange-Grapefruit Drink �-62- APOLLX) 10 ZM MENU Meal A F m it Cocktail Bacon Squares ( 8 ) Brownies ( 4 ) Orange Drink Grape Punch Meal I3 Beef and Vegetables Pineapple F r u i t c a k e (4) Orange-Grapefruit Drink Grape Punch Meal C Cream o f Chicken Soup Beef Hash Strawberry Cubes (4) Pineapple-Grapefruit ."I Drink 2 man-days only L meals p e r overwrap Red and Blue Velcro �Personal Hygiene Crew personal hygiene equipment aboard Apollo 10 i n cludes body c l e a n l i n e s s items, t h e waste management system and one medical k i t . Packaged with t h e food a r e a toothbrush and a two-ounce tube of t o o t h p a s t e f o r each crewman. Each man-meal package contains a 3.5-by-four-Inch wet-wipe cleansing towel. Additionally, t h r e e packages of 12-by-12-Inch dry towels ape stowed beneath t h e command module p i l o t ' s couch. Each package c o n t a i n s seven towels. Also stowed under t h e command module p i l o t ' s couch a r e seven t i s s u e d i s p e n s e r s containing 53 t h r e e p l y t i s s u e s each. S o l i d body wastes are c o l l e c t e d i n Gemini-type p l a s t i c d e f e c a t i o n bags which contain a germicide t o prevent b a c t e r i a and gas formation. The bags a r e sealed a f t e r use and stowed i n empty food c o n t a i n e r s f o r p o s t - f l i g h t a n a l y s i s . Urine c o l l e c t i o n devices a r e provided f o r use while wearing e i t h e r the pressure s u i t o r the f n f l i g h t c o v e r a l l s . The u r i n e i s dumped overboard through t h e s p a c e c r a f t u r i n e dump valve i n the CM and s t o r e d i n t h e LM. The 5 x 5 ~ 8 - i n c hmedical accessory k i t i s stowed i n a cornpartment on t h e s p a c e c r a f t r i g h t s i d e w a l l beside t h e lunar module p i l o t couch. The medical k i t c o n t a i n s t h r e e motion sickness i n j e c t o r s , t h r e e pain suppression i n J e c t o r s , one twoounce b o t t l e f i r s t a i d ointment, two one-ounce b o t t l e eye drops, t h r e e n a s a l sprays, two compress bandages, 12 adhesive bandages, one o r a l thermometer and two s p a r e crew biomedical harnesses. P i l l s i n t h e medical k i t a r e 60 a n t i b i o t i c , 12 nausea, 12 s t i m u l a n t , 18 pain k i l l e r , 60 decongestant, 24 d i a r r h e a , 72 a s p i r i n and 2 1 sleeping. Additionally, a small medical k i t containing four stimulant, e i g h t d i a r r h e a , two s l e e p i n g and four pain k i l l e r p i l l s , 12 a s p i r i n , one b o t t l e eye drops and two compress bandages i s stowed i n t h e lunar module f l i g h t d a t a f i l e compartment. Survival Gear The s u r v l v a l k i t i s stowed i n two rucksacks in the r i g h t hand forward equipment bay above t h e lunar module p i l o t . Contents of rucksack No. 1 are: two combination s u r v i v a l l i g h t s , one d e s a l t e r k i t , t h r e e p a i r sunglasses, one r a d i o beacon, one spare r a d i o beacon b a t t e r y and s p a c e c r a f t connector cable, one k n i f e i n sheath, t h r e e water c o n t a i n e r s and two cont a i n e r s of Sun l o t i o n . ��Rucksack No. 2: one three-man l i f e raft with CO i n f l a t e r , one sea anchor, two s e a dye markers, t h r e e unbonnets, one mooring lanyard, t h r e e manllnes, and two a t t a c h brackets. 5 The s u r v i v a l k i t is designed t o provide a 48-hour postlanding (water o r land) s u r v i v a l c a p a b i l i t y f o r t h r e e crewmen between 40 degrees North and South l a t i t u d e s . Biomedical I n f l i g h t Monitorin4 The Apollo 10 crew biomedical telemetry d a t a received by the Manned Space F l i g h t Network w i l l be relayed f o r Instantaneous d i s p l a y a t Mission Control Center where h e a r t r a t e and breathing r a t e d a t a w i l l be displayed on the f l i g h t surgeon's console. Heart r a t e and r e s p i r a t i o n rate average, range and d e v i a t i o n a r e computed and displayed on d i g i t a l TV screens. I n a d d i t i o n , t h e instantaneous h e a r t r a t e , real-time and delayed EXG and r e s p i r a t i o n a r e recorded on s t r i p c h a r t s f o r each man. Biomedical telemetry w i l l be simultaneous from a l l crewmen while i n the CSM, but s e l e c t a b l e by a manual onboard switch i n the LM. Biomedical data observed by t h e f l i g h t surgeon and h i s team i n the L i f e Support Systems S t a f f Support Room w i l l be c o r r e l a t e d wlth s p a c e c r a f t and space s u i t environmental data displays. Blood pressures a r e no longer telemetered as they were i n the Mercury and Gemini programs. Oral temperature, however, can be measured onboard f o r d i a g n o s t i c purposes and voiced down by the crew In case o f i n f l i g h t i l l n e s s . Rest-Work Cycles A l l t h r e e Apollo 10 crewmen w i l l s l e e p simultaneously during r e s t periods. The average mission day w i l l c o n s i s t of 16 hours of work and e i g h t hours of r e s t . Two crewmen normally w i l l s l e e p i n t h e s l e e p s t a t i o n s ( s l e e p i n g bags) under t h e couches, w i t h t h e t h i r d man i n the couch. During r e s t periods, one crewman w i l l wear h i s communications headset. The only exception t o t h i s s l e e p i n g arrangement w i l l be during the r e s t period on lunar o r b i t i n s e r t i o n day, when two crewmen w i l l s l e e p i n the couches s i n c e the docking probe and drogue assemblies w i l l be stowed i n one o f t h e s l e e p s t a t i o n s . When poss'ible, a l l t h r e e crewmen w i l l e a t together i n onehour e a t p e r i o d s during which o t h e r a c t i v i t i e s w i l l be held t o a minimum. �The crewmen of Apollo 10 have spenlt; more than f i v e hours of forrnal crew t r a i n i n g f o r each hour of t h e l u n a r - o r b i t missiont s e i g h t -day d u r a t i o n . Almost 1,000 hours of t r a i n i n g were i n the Apollo 10 crew t r a i n i n g s y l l a b u s over and above t h e normal p r e p a r a t i o n s f o r the mission--technical b r i e f i n g s and reviews, p i l o t meetings and study. The Apollo 10 crewmen also took p a r t i n s p a c e c r a f t manuf a c t u r i n g checkouts a t the Nosrth American Rockwell p l a n t i n Downey , C a l i f . , a t Orumman A i r c r a f t Engineering Gorp,, Bethpaga, N.Y., and i n prelaunch t e s t i n g a t NASA Kennedy Space Center. Taking p a r t i n f a c t o r y and launch a r e a t e s t i n g has provided t h e crew with thorough o p e r a t i o n a l knowledge of the complex vehicle. Highlights of s p e c i a l i z e d ApoPlo 10 crew t r a i n i n g t o p i c s are: * Detailed s e r i e s of b r i e f i n g s on s p a c e c r a f t systems, operation and modifications. * Saturn launch vehicle b r i e f i n g s on countdown, range s a f e t y , f l i g h t dynamics, f a i l u r e modes and a b o r t conditions. The launch vehicle b r i e f i n g s were updated p e r l o d e a l l y . * Apollo ouidance and Navigation system b r i e f i n g s a t the Massachusetts I n s t i t u t e of Technology I n s t e n t a t i o n Laboratory. * B r i e f i n g s and continuous t r a i n i n g on mission photographic o b j e c t i v e s and use of camera equipment. * Extensive p i l o t p a r t i c i p a t i o n i n reviews of a l l f l i g h t procedures f o r normal as well as emergency s i t u a t i o n s . * Stowage reviews and p r a c t i c e i n t r a i n i n g s e s s i o n s i n t h e s p a c e c r a f t , mockups and command module simulators allowed t h e crewmen t o evaluate s p a c e c r a f t stowage of crew-associated equipment. * More than 300 hours of t r a i n i n g p e r man i n command module and lunar module simulators a t NSC and KSC, including cloeedloop simulations with f l i g h t c o n t r o l l e r s i n t h e Mission Control Center. Other Apollo simulators a t various l o c a t i o n s were used e x t e n s i v e l y f o r s p e c i a l i z e d crew t r a i n i n g . * Entry c o r r i d o r d e c e l e r a t i o n p r o f i l e s a t lunar-return conditions i n t h e MSC F l i g h t Acceleration F a c i l i t y manned centrifuge, �* Zero-g a i r c r a f t f l i g h t s using command module and lunar module mockups f o r EVA and pressure s u i t doffing/donning p r a c t i c e and t r a i n i n g . * Underwater zero-g t r a i n i n g i n the MSC Water Immersion F a c i l i t y using spacecraft mockups t o f a m i l i a r i z e f u r t h e r crew with a l l a s p e c t s of CSM-LM docking tunnel i n t r a v e h i c u l a r t r a n s f e r and GVA i n pressurized s u i t s . * Water e g r e s s t r a i n i n g conducted i n indoor tanks a s well as i n t h e Gulf of Mexico included uprighting from the Stable I1 p a a i t i o n (apex downj t o the S t a b l e I p o s i t i o n (apex up), egress onto r a f t s and h e l i c o p t e r pickup. * Launch pad egress t r a i n i n g from mockups and from the a c t u a l s p a c e c r a f t on the launch pad f o r possible emergencies such as f i r e , contaminants and power f a i l u r e s . + The t r a i n i n g covered use of Apollo s p a c e c r a f t f i r e suppress ion equipment i n t h e cockpit. * Planetarium reviews a t Morehead Planetarium, Chapel and a t G r i f f i t h Planetarium, Los Angeles, Calif., of t h e c e l e s t i a l sphere with s p e c i a l emphasis on the 37 navigational s t a r s used by t h e Apollo guidance computer. H i l l , N.C., �Crew Biographies NAME: Thomas P. S t a f f o r d ( c o l o n e l , USAF) Apollo 10 commander NASA Astronaut BIRTHPLACE AND DATE: Born September 17, 1930, i n Weatherford, Okla., where h i s mother, Mrs. Mary E l l e n S t a f f o r d , now resides. PHYSICAL DESCRIPTION: Black h a i r , blue eyes; height: weight: 175 pounds. 6 feet; EDUCATION: Qraudated from Weatherford High School, Weatherford, Okla.; received a Bachelor of Science degree from the United S t a t e s Naval Academy i n 1952; r e c i p i e n t of an Honorary Doctorate of Science from Oklahoma C i t y U n i v e r s i t y i n 1967. MARITAL STATUS: Married t o t h e former Faye L. Shoemaker of Weatherford, Okla. H e r p a r e n t s , M r . and Mrs. E a r l e R. Shoemaker, r e s i d e i n Thomas, Okla. CHILDREN: Dionne, July 2, 1954; Karin, Aug. 28, 1957. H i s hobbies include handball, weight l i f t i n g and swimming. OTHER ACTIVITIES: ORGANIZATIONS: Pilots. Member of t h e S o c i e t y o f Experimental Test SPECIAL HONORS: Awarded two NASA Exceptional Service Medals and t h e A i r Force Astronaut Wings; t h e Distinguished Flying Cross; the A I A A A s t r o n a u t i c s Award; and co-rec i p i e n t of t h e 1966 Harmon I n t e r n a t i o n a l Aviation Trophy. EXPERIENCE: Staffo.rd, an A i r Force c o l o n e l , was colnmissioned i n i n t h e United S t a t e s A i r Force upon graduation from Annapolis. Following h i s f l i g h t t r a i n i n g , he flew f i g h t e r i n t e r c e p t o r a i r c r a f t i n t h e United S t a t e s and Germany and l a t e r a t t e n d e d t h e USAF m p e r i m e n t a l F l i g h t T e s t School a t Edwards A i r Force Base, C a l i f . H e served as Chief of t h e Performance Branch a t t h e USAP Aerospace Research P i l o t School a t Edwards and was res p o n s i b l e f o r t h e s u p e r v i s i o n and a d m i n i s t r a t i o n o f t h e f l y i n g curriculum f o r s t u d e n t test p i l o t s . H e was also an i n s t r u c t o r i n f l i g h t test t r a i n i n g and s p e c i a l i z e d academic s u b j e c t s - - e s t a b l i s h i n g b a s i c textbooks and d i r e c t i n g t h e w r l t i n g o f f l i g h t t e s t manuals f o r use by t h e s t a f f and s t u d e n t s . He i s co-author o f t h e P i l o t ' s Handbook for Performance F l i g h t T e s t i n g and t h e Asrodynamics Handbook f o r Performance F l i g h t Testing, - �H e has accumulated over 5,000 hours f l y i n g t b e , of which over 4,000 hours are i n jet a i r c r a f t . Colonel S t a f f o r d was s e l e c t e d as an a s t r o n a u t by NASA i n September 1962. H e has s i n c e served as backup p i l o t f o r the Gemini 3 f l i g h t . CURRENT ASSIGNMENT: On Dec. 15, 1965, he and command p i l o t Walter M. S c h i r r a were launched i n t o space on the history-making Qemini 6 mission and subsequently p a r t i c i p a t e d i n the f i r s t s u c c e s s f u l rendezvous of two manned maneuverable spacec r a f t by joining the a l r e a d y o r b i t i n Gemini 7 crew. Gemini 6 returned t o Earth on k c . 1 , 1965, a f t e r 25 hours 51 minutes and 24 seconds of f l i g h t . ti He made h i s second f l i g h t as command p i l o t o f t h e Gemini 9 mission. During t h i s 3-day f l i g h t which began on June 3, 1966, the s p a c e c r a f t a t t a i n e d a c i r c u l a r o r b i t of 161 s t a t u t e m i l e s ; t h e crew performed t h r e e d i f f e r e n t types of rendezvous with the previously launched Augmented Target Docking Adapter; and p i l o t Eugene Cernan logged two hours and t e n minutes o u t s i d e t h e s p a c e c r a f t i n e x t r a v e h i c u l a r a c t i v i t y . The f l i g h t ended a f t e r 72 hours and 20 minutes with a p e r f e c t r e e n t r y and recovery as Gemini 9 landed within 0.4 naukical m i l e s of t h e des i g n a t e d t a r g e t point and 13 miles from the prlme recovery s h i p , USS WASP. �NAm: John W. Young(Commander, USN) pilot NASA Astronaut Apollo 10 conrmand module BIRTHPLACE AND DATE: Born i n San Francisco, C a l i f . , on Sept. 24, 1930. H i s parents, M r . and Mrs. W i l l i a m 8 . Young, r e s i d e i n Orlando, Fla. PHYSICAL DESCRIPTION: Brown h a i r ; green eyes; height: 9 inches; weight: 165 pounds. 5 feet . Qraudated from Orlando High School, Orlando, Fla ; received a Bachelor o f Science degree i n Aeronautical Engineering from the Georgia I n s t i t u t e of Technology i n 1952* EIXJCATION: MARITAL STAWS: Married t o the former Barbara V. White of Savannah, Ga, Her parents, M r . and Mrs. Robert A . White, r e s i d e i n Jacksonville, Fla. CHILDREN: Sandy, Apr. 30, 1957; John, Jan. 17, 1959. OTHER ACTIVITIES: H i s hobbles a r e bicycle r i d i n g and handball. ORGAMIZATIONS: Member of the American I n s t i t u t e of Aeronautics and Astronautics and the Society of Experimental Test Pilots. SPECIAL HONORS: Awarded two NASA Exceptional Service Medals, t h e Navy Astronaut Wings, and three Distinguished Flying Crosses. EXPWIENCE: Upon graduation from Georgia Tech, Young entered t h e U,S, Navy i n 1952 and holds t h e rank of commander. He was a t e s t p i l o t a t t h e Naval A i r Test Center from 1959 t o 1962. Test p r o j e c t s included evaluations of t h e F8D and F4B f i g h t e r weapons systems. I n 1962, he set world time-to-climb records t o 3,000 and 25,000-meter a l t i t u d e s i n the F4B. P r i o r to h i s assignment t o NASA he was k i n t e n a n c e O f f i c e r of All-Weather -Fighter Squadron 143 a t t h e Naval A i r S t a t i o n , M i r a m a r , C a l i f . H e has logged more than 4,500 hours f l y i n g time, including more than 3,900 hours i n j e t a i r c r a f t . �CURRENT ASSIGNMENT: Commander Poumze; was s e l e c t e d as an a s t r o naut by NASA in September 1962. H e served as p i l o t on t h e first manned G e m i n i f l i g h t - - a 3 - o r b i t mission, launched on March 23, 1965, during which t h e crew accomplished t h e first manned s p a c e c r a f t o r b i t a l t r a j e c t o r y modifications and l i f t i n g r e e n t r y , and f l i g h t t e s t e d all systems i n G e m i n i 3. After t h f a assignment, he was backup p i l o t f o r Gemini 6. 18, 1966, Young occupied t h e co&d p i l o t seat f o r t h e Gemini 10 mission and, with Michael C o l l i n s as p i l o t , e f f e c t e d a successf'ul rendezvous and docking with t h e Agena target vehicle. men, they i g n i t e d t h e large Agena main engine t o propel t h e docked combination t o a record a l t i t u d e of approximately 475 miles above t h e Earth--the first manned operation o f a large r o c k e t engine i n space. They later performed a completely o p t i c a l rendezvous (without r a d a r ) on a second passive Agena. A f t e r t h e rendezvous, while Young f l e w formation on t h e passive Agena, C o l l i n s performed e x t r a v e h i c u l a r a c t i v i t y t o it and recovered a micrometeorite d e t e c t i o n experiment, accomplfahing an In-space r e t r i e v a l of t h e d e t e c t o r t h a t had been o r b i t i n g the Earth f o r t h r e e months. On July The f l i g h t was concluded a f t e r 3 days and 44 revolutions-during which Gemini 10 t r a v e l e d a t o t a l d i s t a n c e of 1,275, 091 s t a t u t e miles. Splashdown occurred in the West A t l a n t i c , 529 s t a t u t e miles e a s t of' Cape Kennedy, where Gemini 10 landed 2.6 miles from the USS GUADAUANBL w i t h i n eye and camera range of t h e prime recovery v e s s e l . �NAME: Eugene A. Cernan (Commander, USN) pilot NASA Astronaut Apollo 10 lunar module BIRTHPLACE AND DATE: Born i n Chicago, Ill,, on March 14, 1934, H i s mother, H r s . Andrew a. Cernan, r e s i d e s i n Bellwood, Ill. Brown h a i r ; blue eyes; height: 170 pounds. PHYSICAL DESCRIPTION: weight: 6 feet; EDJCATION: araduated from Proviso Township High School i n Maywood, Ill.; received a Bachelor of Science degree i n E l e c t r i c a l Engineering from Purdue University and a Master of Science degree i n Aeronautical Engineering from t h e U.S. Naval Postgraduate School. MARITAL STATUS: Married t o t h e former Barbara J . Atchley of Houston, Tex. CHILDREN: Teresa Dawn, March 4 , 1963. OTHER ACTIVITIES: H i s hobbies include gardening and a l l s p o r t s activities. ORQANIZATIONS: Member of Tau Beta P i , n a t i o n a l engineering s o c i e t y ; Sigma X i , n a t i o n a l science research s o c i e t y ; and Phi Gamma Delta, n a t i o n a l s o c i a l f r a t e r n i t y . SPECIAL HONORS: Awarded t h e NASA Exceptional Service Medal; t h e Navy Astronaut Wings; and t h e Distinguished Flying Cross. EXPERIENCE: Cernan, a United S t a t e s Navy commander, received h i s commission through t h e Navy ROTC program a t Purdue. He entered f l i g h t t r a i n i n g upon h i s graduation. P r i o r t o a t t e n d i n g the Naval Postgraduate School, he was assigned t o Attack Squadrons 126 and 113 a t t h e Miramar, C a l i f . , Naval A i r S t a t i o n , H e has logged more than 3,000 hours flying time with more than 2,810 hours i n jet a i r c r a f t . CURRENT ASSIGNMENT: Commander Cernan was one of t h e t h i r d group of a s t r o n a u t s s e l e c t e d by NASA i n October 1963. �He occupied t h e p i l o t seat alongside Command Pilo"u0m S t a f f o r d on t h e Gemini 9 mission. During t h i s 3-day f l i g h t which began on June 3, 1966, t h e s p a c e c r a f t a t t a i n e d a c i r c u l a r o r b i t o f 161 s t a t u t e miles; t h e crew used t h r e e d i f f e r e n t techniques t o e f f e c t rendezvous with t h e previous ly launched Augmented Target Docking Aaap t e r ; and Cernan logged two hours and t e n minutes o u t s i d e t h e spacec r a f t i n e x t r a v e h i c u l a r a c t i v i t y , The f l i g h t ended a f t e r 72 hours and 20 minutes with a p e r f e c t r e e n t r y and recovery as Gemini g landed within 1* miles of t h e prime recovery s h i p USS WASP and 3/8 of a mile from t h e predetermined t a r g e t p o i n t . He has s i n c e served as backup p i l o t f o r Gemini 12. �APOLLO LAUNCH OPERATIONS NASA's John F, Kennedy Space Center performs p r e f l i g h t checkout, t e s t , and launch of t h e Apollo 10 space v e h i c l e , A government-industry team of about 550 w i l l conduct t h e f i n a l countdown from F i r i n g Room 3 of t h e Munch Control Center (LCC). The f i r i n g room team i s backed up by more t h a n 5,000 persons who a r e d i r e c t l y involved i n launch o p e r a t i o n s a t KSC from t h e time t h e v e h i c l e and s p a c e c r a f t s t a g e s a r r i v e a t t h e c e n t e r u n t i l t h e launch i s completed, -- I n i t i a l checkout of t h e Apollo s p a c e c r a f t i b conducted i n work s t a n d s and i n t h e a l t i t u d e chrunbers i n t h e Manned Spacec r a f t Operations Building (MSOB) a t Kennew Space Center. A f t e r completion of checkout t h e r e , t h e a s s a b l e d s p a c e c r a f t I s taken t o t h e v e h i c l e Assembly Building (vAB) and mated with t h e launch vehicle. There t h e f i r s t i n t e g r a t e d s p a c e c r a f t and launch v e h i c l e tests a r e conducted, The assembled space v e h i c l e i s then r o l l e d o u t 60 t h e luanch pad f o r f i n a l p r e p a r a t i o n s and countdown t o launch, I n mid-October 1968, P l i g h t hardware f o r Apollo 10 began a r r i v i n g a t Kennedy Space Center, j u s t as Apollo 7 was being launched from Complex 34 on Cape Kennedy and as Apollo 8 and Apollo 9 were undergoing checkout a t lCennedy Space Center. The l u n a r module was t h e f i ~ s pt i e c e of' .&pollo 10 f l i g h t hardware t o a r r i v e a t KSC, The two s t a g e s e r e moved i n t o t h e a l t i t u d e chamber i n t h e Manned S p a c e c r a f t Operations Building (MSOB) a f t e r a n i n i t i a l m c e i v i n g i n s p e c t i o n i n October, I n t h e chamber &he I$I underwent systems tests and both unmanned and manned chamber runs, During t h e s e runs t h e chamber a i r was pumped out t o s i m u l a t e t h e vacuum of space a t a l t i t u d e s i n excesa of 200,000 f e e t , There t h e s p a c e c r a f t systems and t h e a s t r o n a u t s g l i f e support systems were t e s t e d , While t h e 1C4\11 was undergoLng p r e p a r a t i o n f o r i t s manned a l t i t u d e chamber runs, t h e Apollo 10 command/service module a r r i v e d a t KSC and a f t e r r e c e i v i n g i n s p e c t i o n , it, too, was placed i n a n a l t i t u d e chamber i n t h e MSOB f o r systems t e s t s and unmanned and manned chamber runs, The prime and back-up crews p a r t i c i p a t e d i n t h e chamber r u n s on both t h e LM and t h e CSM , I n January, t h e I24 and CSM were removed from t h e chambers. A f t e r i n s t a l l i n g t h e landing g e a r on t h e LM and t h e SPS engine nozzle on t h e CSM, t h e LM was encapsulated i n t h e s p a c e c r a f t W a d a p t e r (SLA) and t h e CSM was mated t o t h e SLA. On February 6, t h e assembled s p a c e c r a f t was moved t o t h e VAB where i t was mated t o t h e launch v e h i c l e , �The launch vehicle flight hardware began a r r i v i n g a t KSC i n late November, and by t h e end of December t h e t h r e e stages and t h e instrument unit were erected on t h e mobile launcher i n high bay 2, This was the first time high bay 2, on t h e west s i d e of t h e VAB, had been used f o r assembling a Saturn V, Tests were conducted on Individual systems on each of t h e s t a g e s and on t h e o v e r a l l launch vehicle before the spacecraft was erected a t o p t h e vehicle, After spacecraft erection, t h e spacecraft and launch vehicle were e l e c t r i c a l l y mated and t h e first o v e r a l l test (plugs-in) of t h e space vehicle was conducted, I n accordance with t h e philosophy of a c c m p l i s h i n g as much of t h e checkout as possible i n t h e VAB, t h e o v e r a l l test was conducted before t h e space vehicle was moved t o t h e launch pad. The plugs-in test v e r i f i e d the compatibility of the space vehicle systems, ground support equipment, and o f f - s i t e support f a c i l i t i e s by demonstrating t h e a b i l i t y of t h e systems t o proceed through a simulated countdown, launch, and f l i g h t . During t h e simulated f l i g h t portion of t h e test, t h e systems were required t o respond t o both emergency and normal f l i g h t conditions, The move t o Pad B from t h e VAB on March 11 occurred while t h e Apollo 9 c i r c l e d t h e Earth i n t h e first manned test of t h e lunar module. Apollo LO w i l l mark the first launch a t Pad B on complex 39. The first two unmanned Saturn V launches and t h e manned Apollo 8 and 9 launches took place at Pad A. It a l s o marked t h e f i r s t time t h a t t h e t r a n s p o r t e r maneuvered around t h e VAB carrying a f u l l load from high bay 2 on t h e 5-mile t r i p t o the launch pad, The s t a c e vehicle F l i g h t Readiness Test was conducted i n e a r l y April. Both t h e prime and backup crews p a r t i c i p a t e i n portions of t h e FFtT, which is a f i n a l o v e r a l l t e s t of t h e space vehicle systems and gmund support equipment when a l l systems are a s near as possible t o a launch configuration, After hypergolic f u e l s were loaded aboard the spsce vehicle, and t h e launch vehicle first s t a g e f u e l (RP-1) was brought aboard, t h e f i n a l major test of the space vehicle began. T h i s w a s the countdown demonstration test ( c D ~ ) , a d r e s s r-?hearsal f o r the f i n a l countdown t o launch, The CDM! f o r Apollo 10 was divided into a "wet" and a "dryf' portion. D u r i n g t h e first, o r "wet" portion, t h e e n t i r e countdown, including propellant loading, rlas c a r r i e d out down t o T-8.9 seconds, The astronaut crews did not p a r t i c i p a t e i n t h e w e t CDm. A t t h e completion of the wet CDEP, t h e cryogenic �. p r o p e l l a n t s ( l i q u i d oxygen and liquid hydrogen) were off-loaded, and t h e f i n a l p o r t i o n of t h e countdown was re-run, t h i s time s i m u l a t i n g t h e f u e l i n g and w i t h t h e prime a s t r o n a u t crew p a r t i c i p a t i n g as t h e y will on launch day. By t h e time Apollo 10 was e n t e r i n g t h e f i n a l phase of Its checkout procedure a t Complex 39B, crews had a l r e a d y s t a r t e d t h e checkout of Apollo 11 and Apollo 12. The Apollo 11 s p a c e c r a f t completed a l t i t u d e chamber t e s t i n g and was mated t o t h e launch v e h i c l e i n tne VAR i n mid-April a s t h e Apollo 12 CSM and LM begari checkout i n t h e a l t i t u d e chambers. Because of t h e complexity involved i n t h e checkout of t h e 363-foot-tall (110.6 meters) Apollo/Saturn V configuration, t h e launch teams make use of e x t e n s i v e automation in t h e i r checkout. Automation i s one of t h e major d i f f e r e n c e s i n checkout used on Apollo compared t o t h e procedures used i n t h e Mercury and Gemini programs. Computers, data d i s p l a y equipment, and d i g i t a l d a t a techniques are used throughout t h e automatic checkout f r o m t h e time t h e launch v e h i c l e i s e r e c t e d i n t h e VAB through l i f t o f f , A s i m i l a r , but s e p a r a t e computer o p e r a t i o n c a l l e d ACE ( ~ c c e p t a n c e Checkout Equipment) i s used t o v e r i f y t h e f l i g h t r e a d i n e s s of t h e s p a c e c r a f t . Spacecraft checkout i s c o n t r o l l e d from s e p a r a t e rooms i n t h e Manned Spacecraft Operations Building. ' �LAUNCH C O M P U X 39 Launch Complex 39 f a c i l i t i e s a t t h e Kennedy Space Center were planned and b u i l t s p e c i f i c a l l y f o r t h e Apollo S a t u r n V program, t h e s p a c e v e h i c l e t h a t will be u s e d t o c a r r y a s t r o n a u t s t o t h e Moon. Complex 39 i n t r o d u c e d t h e m o b i l e concept of l a u n c h operat,ions, a d e p a r t u r e from t h e f i x e d l a u n c h pad t e c h n i q u e s u s e d p r e v i o u s l y a t Cape Kennedy and o t h e r l a u n c h s i t e s . S i n c e t h e e a r l y 1950's when t h e first b a l l i s t i c misslles were launched, t h e f i x e d l a u n c h concept had been used on NASA m i s s i o n s , T h i s method c a l l e d f o r assembly, checkout and l a u n c h of a rocket a t one s i t e o m t h e l a u n c h pad. I n a d d i t i o n t o t y i n g up t h e pad, t h i s method a l s o o f t e n l e f t t h e flight equipment exposed t o t h e o u t s i d e i n f l u e n c e s of t h e weather f o r extended p e r i o d s . Using t h e mobile concept, t h e s p a c e v e h i c l e i s t h o r o u g h l y checked i n a n e n c l o s e d b u i l d i n g b e f o r e i t i s moved t o the launch pad f o r f i n a l p r e p a r a t i o n s . T h i s a f f o r d s g r e a t e r p r o t e c t i o n , a more s y s t e m a t i c checkout p r o c e s s u s i r g computer t e c h n i q u e s and a h i g h l a u n c h r a t e f o r t h e f u t u r e , s i n c e t h e pad time i s minimal. S a t u r n V s t a g e s are s h i p p e d t o t h e Kennedy Space C e n t e r b y ocean-going v e s s e l s and s p e c i a l l y d e s i g n e d a i r c r a f t , s u c h as the Guppy, Apollo s p a c e c r a f t modules a r e t r a n s p o r t e d by a i r . The s p a c e c r a f t components a r e f i r s t t a k e n t o t h e Manned Spacecraft O p e r a t i o n s B u i l d i n g f o r p r e l i m i n a r y checkout, The S a t u r n V s t a g e s are b r o u g h t immediately t o t h e V e h i c l e Assembly B u i l d i n g a f t e r a r r i v a l a t t h e nearby t u r n i n g b a s i n . Apollo 10 i s t h e f i r s t v e h i c l e t o be launched from Pad B, Complex 39. "11 p r e v i o u s S a t u r n V v e h i c l e s were launched Pad A a t Complex 39, The h i s t o r i c first l a u n c h of t h e S a t u r n V, d e s i g n a t e d Apollo 4 , took p l a c e Nov. 9, 1967 a f t e r a p e r f e c t countdown and on-time l i f t o f f a t 7 a.m. EST. The second S a t u r n V mission--Apollo 6--was conducted last A p r i l 4, The t h i r d S a t u r n V m i s s i o n , Apollo 8 , was conducted last Dec. 21-27. Apollo 9 was March 3-13, 1969. The major components of Complex 39 i n c l u d e : (1) t h e V e h i c l e Assembly B u i l d i n (VAB) where t h e A p o l l o 1 0 w a s assembled and p r e p a r e d ; 2 ) t h e Launch C o n t r o l C e n t e r , where t h e launch team c o n d u c t s t h o p r e l i m i n a r y checkout and f i n a l countdown; ( 3 ) t h e mobile l a u n c h e r , upon which t h e Apollo 10 was e r e c t e d f o r checkout and from where i t w i l l be launched; ( 4 ) t h e mobile s e r v i c e s t r u c t u r e , which p r o v i d e s e x t e r n a l access t o t h e s p a c e v e h i c l e a t t h e pad; ( 5 ) t h e t r a n s p o r t e r , which a r r r i e s t h e s p a c e v e h i c l e and mobile l a u n c h e r , as w e l l as t h e mobile s e r v i c e s t r u c t u r e t o t h e pad; ( 6 ) t h e crawlerway over which t h e s p a c e v e h i c l e t r a v e l s from t h e VAB t o t h e l a u n c h pad; and ( 7 ) t h e l a u n c h pad i t s e l f t , 'T �Vehicle Assembly build in^ The Vehicle Assembly Building i s t h e h e a r t of Launch Complex 39. Covering e i g h t a c r e s , i t i s where t h e 363-foot-tall space v e h i c l e i s assembled and t e s t e d . The VAB c o n t a i n s 129,482,000 cubic f e e t of space, It i s 716 f e e t long, and 518 f e e t wide and it covers 343,500 square f e e t of f l o o r space. The foundat i o n of t h e VAB rests on 4,225 s t e e l p i l i n g s , each 16 inches i n diameter, d r i v e n from 150 t o 170 f e e t t o bedrock. If placed end t o end, t h e s e p i l i n g s would extend a d i s t a n c e of 123 miles. The s k e l e t a l s t r u c t u r e of t h e b u i l d i n g c o n t a i n s approximately 60,000 t o n s of s t r u c t u r a l s t e e l . The e x t e r i o r i s covered by more t h a n a m i l l i o n square f e e t of i n s u l a t e d aluminum siding, The b u i l d i n g i s divided i n t o a h i g h bay a r e a 525 f e e t high and a low bay area 210 f e e t high, with both a r e a s s e r v i c e d by a t r a n s f e r a i s l e f o r movement of v e h i c l e s t a g e s . The low bay work a r e a , approximately 442 f e e t wide and 274 f e e t long, c o n t a i n s e i g h t s t a g e - p r e p a r a t i o n and checkout c e l l s . These c e l l s a r e equipped with systems t o s i m u l a t e s t a g e i n t e r f a c e and o p e r a t i o n with o t h e r s t a g e s and t h e instrument u n i t of t h e S a t u r n V launch v e h i c l e . A f t e r t h e Apollo 10 launch v e h i c l e upper s t a g e s a r r i v e d a t t h e Kennedy Space Center, t h e y were moved t o t h e low bay of t h e VAB. Here, t h e second and t h i r d s t a g e s underwent acceptance and checkout t e s t i n g p r i o r t o mating w i t h t h e S-IC f i r s t s t a g e a t o p mobile launcher 3 i n t h e high bay a r e a . The high bay provides f a c i l i t i e s f o r assembly and c h e c k o ~ t of both t h e launch v e h i c l e and s p a c e c r a f t . It c o n t a i n s f o u r s e p a r a t e bays f o r v e r t i c a l assembly and checkout. A t p r e s e n t , t h r e e bays a r e equipped, and t h e f o u r t h w i l l be r e s e r v e d f o r p o s s i b l e changes i n v e h i c l e c o n f i g u r a t i o n . -- -- Work platforms some as high a s t h r e e - s t o r y b u i l d i n g s in t h e high bays provide a c c e s s by surrounding t h e v e h i c l e a t varying l e v e l s . Each high bay has f i v e platforms, Each platform c o n s i s t s of two b i - p a r t i n g s e c t i o n s t h a t move i n from opposite s i d e s and mate, providing a 360-degree a c c e s s t o t h e s e c t i o n of t h e space v e h i c l e being checked. A 10,000-ton-capacity a i r c o n d i t i o n i n g system, s u f f i c i e n t t o cool about 3,000 homes, h e l p s t o c o n t r o l t h e environment within t h e e n t i r e o f f i c e , l a b o r a t o r y , and workshop complex l o c a t e d i n s i d e t h e low bay a r e a of t h e VAB. A i r c o n d i t i o n i n g i s a l s o fed t o i n d i v i d u a l platform l e v e l s l o c a t e d around t h e v e h i c l e . �There a r e 141. l i f t i n g devices i n t h e VAB, ranging from onet o n h o i s t s t o two 250-ton h i g h - l i f t brrdge cranes. The mobile launchers, c a r r i e d by t r a n s p o r t e r v e h i c l e s , move i n and out of t h e VAB through f o u r doors i n t h e high bay a r e a , one i n each of t h e bays, Each door i s shaped l i k e an i n v e r t e d T. They a r e 152 f e e t wide and 114 f e e t high a t t h e base, narrowing t o 76 f e e t i n w i d t h . T o t a l door h e i g h t i s 456 f e e t , The Lower s e c t i o n of each door i s of t h e a i r c r a f t hangar t y p e t h a t s l i d e s h o r i z o n t a l l y on t r a c k s . Above t h i s a r e seven t e l e s c o p i n g v e r t i c a l l i f t p a n e l s s t a c k e d one above t h e o t h e r , each 50 f e e t high and d r i v e n by a n i n d i v i d u a l motor, ]Each p a n e l s l i d e s over t h e next t o c r e a t e a n opening l a r g e enough t o p e n n i t passage of t h e mobile launcher, Munch Control Center Adjacent t o t h e VAB i s t h e h u n c h Control Center (LcC). This four-story s t r u c t u r e i s a r a d i c a l d e p a r t u r e from t h e dame-shaped blockhouses a t o t h e r launch s i t e s , The e l e c t r o n i c " b r a i n " of Launch Complex 39, t h e LCC was used f o r checkout and t e s t o p e r a t i o n s while Apollo 10 was being assembled i n s i d e t h e VAB. The LCC c o n t a i n s d i s p l a y , monitoring, and c o n t r o l equipment used f o r both checkout and launch o p e r a t i o n s . The b u i l d i n g has t e l e m e t e r checkout s ' t a t i o n s on i t s second f l o o r , and f o u r f i r i n g rooms, one f o r each high bay of t h e VAB, on i t s t h i r d f l o o r , Three f i r i n g rooms conta%n i d e n t i c a l s e t s of c o n t r o l and monitoring equipment, s o t h a t launch of a v e h i c l e and checkout of o t h e r s t a k e p l a c e simultaneously, A ground computer f a c i l i t y i s a s s o c i a t e d with each f i r i n g room, The high speed computer d a t a l i n k i s p r o ided between t h e LCC and t h e mobile launcher f o r checkout of t h e 1 unch v e h i c l e . This l i n k can be connected t o t h e mobile launcher t e i t h e r t h e VAB o r a t t h e pad, I The t h r e e equipped f i r i n g rooms have some 450 consoles which c o n t a i n c o n t r o l s and d i s p l a y s r e q u i r e d f o r the1 checkout process. The d i g i t a l d a t a l i n k s connecting taith t h e high b a y areas of t h e VAB and t h e launch pads car-ry v a s t amounts of data r e q u i r e d during checkout and launch, I I. There a r e 15 d i s p l a y systems i n each LCC i r i n g room, with each system capable of providing d i g i t a l infornlation i n s t a n t a n e ously, �S i x t y t e l e v i s i o n cameras a r e p o s i t i o n e d around t h e Apollo/ S a t u r n V t r a n s m i t t i n g p i c t u r e s on 10 modulated channels. The LCC f i r i n g room a l s o c o n t a i n s 112 o p e r a t i o n a l intercommunication channels used by t h e cpews i n t h e checkout and launch countdown. Mobile Launcher The mobile l a u n c h e r i s a t r a n s p o r t a b l e launch base and u m b i l i c a l tower f o r t h e space v e h i c l e . Three mobile launchers a r e used a t Complex 39. The launcher base i s a two-story s t e e l s t r u c t u r e , 25 f e e t h i g h , 160 f e e t long, and 135 f e e t wide. It i s p o s i t i o n e d on s i x s t e e l p e d e s t a l s 22 f e e t high when i n t h e VAB o r a t t h e launch pad, A t t h e launch pad, i n a d d i t i o n t o t h e s i x s t e e l p e d e s t a l s , f o u r extend a b l e columns a l s o are used t o s t i f f e n t h e mobile launcher a g a i n s t rebound l o a d s , i f t h e S a t u r n engines c u t o f f , The u m b i l i c a l tower, extending 398 f e e t above t h e launch p l a t form, i s mounted on one end of t h e launcher base. A hammerhead c r a n e a t t h e t o p h a s a hook h e i g h t of 376 f e e t above t h e deck with a t r a v e r s e r a d i u s of 85 f e e t from t h e c e n t e r of t h e tower. The 12-million-pound mobile launcher s t a n d s 445 f e e t high when r e s t i n g on its p e d e s t a l s , The base, covering about h a l f an a c r e , i s a compartmented s t r u c t u r e b u i l t of 25-foot s t e e l g i r d e r s , The launch v e h i c l e s i t s over a 45-foot-square opening which a l l o w s an o u t l e t f o r engine exhausts i n t o t h e launch pad t r e n c h c o n t a i n i n g a flame d e f l e c t o r . T h i s opening i s l i n e d w i t h a r e p l a c e a b l e s t e e l b l a s t s h i ~ l d ,independent of t h e s t r u c t u r e , and i s cooled by a water c u r t a i n i n i t i a t e d two seconds a f t e r l i f t o f f . There a r e n i n e h y d r a u l i c a l l y - o p e r a t e d s e r v l c e arms on t h e u m b i l i c a l tower, These s e r v i c e arms s u p p o r t l i n e s f o r t h e v e h i c l e u m b i l i c a l systems and provide a c c e s s f o r personnel t o t h e s t a g e s as well as t h e a s t r o n a u t crew t o t h e s p a c e c r a f t . On Apollo 10, one of t h e s e r v i c e arms i s r e t r a c t e d e a r l y i n t h e count. The Apollo s p a c e c r a f t a c c e s s arm i s p a r t i a l l y r e t r a c t e d a t T-43 minutes, A t h i r d s e r v i c e am i s r e l e a s e d a t T-30 seconds, and a f o u r t h a t about T-16.5 seconds, The remaining f i v e arms a r e s e t t o swing back a t v e h i c l e f i r s t motion a f t e r T-0. The s e r v i c e arms a r e equipped w i t h a backup r e t r a c t i o n system i n c a s e t h e primary mode f a i l s . �The Apollo a c c e s s arm ( s e r v i c e arm g ) , l o c a t e d a t t h e 320f o o t l e v e l above t h e l a u n c h e r base, provides a c c e s s t o t h e spacec r a f t c a b i n f o r t h e c l o s e o u t team and a s t r o n a u t crews, The f l i g h t crew w i l l board t h e s p a c e c r a f t s t a r t i n g about T-2 hours, 40 minutes i n t h e count, The a c c e s s a m w i l l be moved t o a parked position, 12 degrees from t h e s p a c e c r a f t , a t about T-43 minutes, T h i s i s a d i s t a n c e of about t h r e e f e e t , whish p e r m i t s a r a p i d r e c o n n e c t i o n of t h e arm t o t h e s p a c e c r a f t i n t h e event of a n emergency condition. The arm i s f u l l y r e t r a c t e d a t t h e T-5 mlnute mark i n t h e count, The Apollo 10 v e h i c l e i s secured t o t h e mobile l a u n c h e r by f o u r combination s u p p o r t and hold-down arms mounted on t h e launcher deck. The hold-down ams are c a s t i n one p i e c e , about 6 x 9 feet a t t h e b a s e and 10 f e e t t a l l , weighing more t h a n 20 t o n s . Damper s t r u t s s e c u r e t h e v e h i c l e n e a r i t s top. A f t e r t h e engines i g n i t e , the arms hold Apollo LO f o r about s i x seconds u n t i l t h e engines build u p t o 95 p e r c e n t t h r u s t and o t h e r monitored systems i n d i c a t e they a r e f u n c t i o n i n g p r o p e r l y . The arms r e l e a s e on r e c e i p t of a launch commit s i g n a l a t t h e z e r o mark i n t h e count. B u t t h e v e h i c l e i s prevented from a c c e l e r a t i n g t o o r a p i d l y by c o n t r o l l e d r e l e a s e mechanisms. Transporter The six-million-pound t r a n s p o r t e r s , t h e l a r g e s t t r a c k e d vehi c l e s known, move mobile l a u n c h e r s i n t o t h e VAB and mobile launchers w i t h assembled Apollo space v e h i c l e s t o t h e launch pad. They also a r e used t o t r a n s f e r t h e mobile s e r v i c e s t r u c t u r e t o and from t h e launch pads. Two t r a n s p o r t e r s are i n u s e a t Complex 39, The TYansporter i s 131 f e e t long and 114 f e e t wide. The v e h i c l e moves on f o u r double-tracked c r a w l e r s , each 10 feet high and 40 f e e t long, Each shoe on t h e c r a w l e r t r a c k i s seven f e e t six i n c h e s i n l e n g t h and weighs about a ton. S i x t e e n t r a c t i o n motors powered by f o u r 1,000-kilowatt gene r a t o r s , which i n t u r n a r e d r i v e n by two 2,750-ho~sepower d i e s e l engines, p r o v i d e t h e motive power f o r t h e t r a n s p o r t e r . Two 750k w g e n e r a t o r s , d r i v e n by two 1,065-horsepower d i e s e l engines, power t h e jacking, s t e e r i n g , l i g h t i n g , v e n t i l a t i n g and e l e c t r o n i c systems. Maximum speed of t h e t r a n s p o r t e r is about one-mile-per-hour loaded and about two-miles-per-hour unloaded, A five-mile t r i p t o Pad I3 with a mobile launcher, made a t l e s s t h a n maximum speed, t a k e s approximately 10-12 hours, �The t r a n s p o r t e r has a l e v e l i n g system designed t o keep t h e t o p of t h e space v e h i c l e v e r t i c a l within plus-or-minus 10 minutes of a r c about t h e dimensions of a basketball. -- This system a l s o provides l e v e l i n g operations required t o n e g o t i a t e t h e f i v e percent ramp which l e a d s t o t h e launch pad and keeps t h e load l e v e l when it i s r a i s e d and lowered on p e d e s t a l s both a t t h e pad and within t h e VAB. The o v e r a l l level t o the top transportation. b a l l diamond (90 height of t h e t r a n s p o r t e r i s 20 f e e t from ground deck on which t h e mobile launcher i s mated f o r The deck is f l a t and about t h e s i z e of a baseby 90 f e e t ) , Two operator c o n t r o l cabs, one a t each end of t h e c h a s s i s located diagonally opposite each other, provide t o t a l l y enclosed s t a t i o n s f r a m which a l l operating and c o n t r o l functions a r e coordinated. Crawlerway The t r a n s p o r t e r moves on a roadway 131 f e e t wide, divided by a median s t r i p . This i s almost a s broad a s an eight-lane turnpike and i s designed t o accommodate a combined weight of about 18 m i l l i o n pounds. The roadway i s b u i l t i n t h r e e l a y e r s with an average depth of seven f e e t . The roadway base l a y e r i s two-and-one-half f e e t of hydraulic f i l l compacted t o 95 percent density. The next l a y e r c o n s i s t s of t h r e e f e e t of crushed rock packed t o maximum density, followed by a l a y e r of one f o o t of s e l e c t e d hydraulic fill. The bed I s topped and s e a l e d w i t h an a s p h a l t prime coat. On top of t h e t h r e e l a y e r s i s a cover of r i v e r rock, e i g h t inches deep on t h e curves and s i x inches deep on t h e straightway, This l a y e r reduces the f r i c t i o n during s t e e r i n g and helps d i s t r i b u t e the load on the t r a n s p o r t e r bearings. Mobile Service S t r u c t u r e A 402-foot-tall, 9.8-million-pound tower i s used t o s e r v i c e t h e Apollo launch vehicle and spacecraft a t t h e pad. The 40-story s t e e l - t r u s s e d tower, c a l l e d a mobile s e r v i c e s t r u c t u r e , provides 360-degree platform access t o t h e Saturn launch vehicle and t h e Apollo s p a c e c r a f t . -- The s e r v i c e s t r u c t u r e has f i v e platforms two self-propelled Two e l e v a t o r s carry personnel and equipment between work platforms. The platforms can open and c l o s e around t h e 363-foot space vehicle, and t h r e e fixed, but movable. �A f t e r dep<:*sitingt h e mobile launcher wLth i t s space vehicle on t h e pad, the t r 8 a n s p o r t e r r e t u r n s t o a parking a r e a about 13,000 f e e t from pad B. There i t p i c k s up the mobile s e r v i c e s t r u c t u r e and moves it t o t h e launch pad. A t t h e pad, t h e huge tower i s lowered and secured t o f o u r mount mechanisms. The t o p t h r e e work platforms are l o c a t e d i n f i x e d p o s i t i o n s which s e r v e t h e Apollo s p a c e c r a f t , The two lower movable platforms s e r v e t h e S a t u r n V. The mobile s e r v i c e s t r u c t u r e remains i n p o s i t i o n u n t i l about T-11 hours when it i s removed from i t s mounts and r e turned t o t h e parkinff area. Water Deluge System 4 water deluge system w i l l provide a m i l l i o n g a l l o n s of i n d u s t r i a l water f o r c o o l i m and f i r e prevention d u r i n g launch of Apollo 10. Once t h e s e r v i c e anns a r e r e t r a c t e d a t l i f t o f f , a s p r a y system w i l l come on t o c o o l t h e s e arms from t h e h e a t of t h e f i v e S a t u r n F-1 engines d u r i n g l i f t o f f . On t h e deck of t h e mobile launcher are 29 water nozzles. This deck deluge w i l l s t a r t immediately a f t e r l i f t o f f and w i l l pour a c r o s s t h e f a c e of t h e launcher f o r 30 seconds a t t h e r a t e of 50,000 gallons-per-minute, a f t e r 30 seconds, t h e flow w i l l be reduced t o 20,000 gallons-per-minute, Positioned on both s i d e s of t h e flame t r e n c h a r e a s e r i e s of nozzles which w i l l begin pouring water at 8,000 gallons-per-minute, 10 secorcl s before l i f t o f f . This water w i l l be d i r e c t e d over t h e flame d e f l e c t o r . Other f l u s h mounted nozzles, p o s i t i o n e d around t h e pad, w i l l wash away any f l u i d s p i l l a s a p r o t e c t i o n a g a i n s t f i r e hazards. Water spray systems a l s o a r e a v a i l a b l e along t h e e g r e s s r o u t e t h a t t h e a s t r o n a u t s and c l o s e o u t crews would follow i n c a s e a n emergency evacuation w a s required. Flame Trench and D e f l e c t o r The flame t r e n c h i s 58 f e e t wide and approximately s i x f e e t above mean s e a l e v e l a t t h e base. The h e i g h t of t h e t r e n c h and d e f l e c t o r i s approximately 42 f e e t . �The Tiam-.d e f l e c t o r weighs about 1.3 m i l l i o n pounds and i s s t o r e d o u t s i d e t h e flame t r e n c h on rails. Wehn i t i s moved beneath the launcher, i t i s raised h y d r a u l i c a l l y i n t o p o s i t i o n , The d e f l e c t o r i s covered w i t h a four-and-one-half-inch t h i c k ness of r e f r a c t o r y c o n c r e t e c o n s i s t i n g of a v o l c a n i c a s h aggregate and a calcuim aluminate binder. The heat and b l a s t of t h e engines a r e expected t o wear about t h r e e - q u a r t e r s of a n i n c h from t h i s r e f r a c t o r y s u r f a c e d u r i n g t h e Apollo l o launch. pad Areas Both Pad A and Pad B of -hunch Complex 39 are roughly octagonal I n shape and cover about one f o u r t h of a square mile of t e r r a i n . The c e n t e r of t h e pad i s a hardstand c o n s t r u c t e d of heavily reinforced concrete. I n addition t o supporting t h e weight of t h e mobile launcher and t h e Apollo S a t u r n V v e h i c l e , it a l s o must support t h e 9.8-million-pound mobile s e r v i c e s t r u c t u r e and 6-million-pound t r a n s p o r t e r , a l l a t t h e same time. The t o p of t h e pad s t a n d s some 48 f e e t above s e a l e v e l , Saturn V p r o p e l l a n t s -- l i q u i d oxygen, l i q u i d hydrogen and RP-1 are s t o r e d n e a r t h e pad perimeter. -- S t a i n l e s a s t e e l , vacuum-jacketed p i p e s c a r r y t h e l i q u i d oxygen (LOX) and l i q u i d hydrogen from t h e s t o r a g e t a n k s t o t h e pad, up t h e mobile launcher, and f i n a l l y i n t o t h e launch v e h i c l e p r o p e l l a n t tanks. LOX i s supplied from a 900,000-gallon s t o r a g e t a n k . c e n t r i f u g a l pump w i t h a d i s c h a r g e p r e s s u r e of 320 poundsper-square-inchpumps LOX t o t h e v e h i c l e a t flow rates as high as 10,000-gallons-per-minute. A Liquid hydrogen, u s e d i n t h e second and t h i r d s t a g e s , i s s t o r e d i n an 850,000-gallon tank, and i s s e n t through 1,500 f e e t of 10-inch, vacuum-Jacketed i n v a r pipe. A vapori z i n g h e a t exchanger p r e s s u r i z e s t h e s t o r a g e tank t o 60 p s i f o r a 10,000 gallons-per-munute flow r a t e , The RP-1 f u e l , a high grade of kerosene i s s t o r e d i n t h r e e tanks--each with a c a p a c i t y of 86,000 g a l l o n s . It i s pumped a t a r a t e of 2,000 gallons-per-minute a t 175 p s i g , The Complex 39 pneumatic system i n c l u d e s a convertercompressor f a c i l i t y , a pad high-pressure gas s t o r a g e b a t t e t y , a high-pressure s t o r a g e b a t t e r y i n t h e VAB, low and high-press u r e , cross-country supply l i n e s , h i ~ h - p r e s s u r e hydrogen s t o r a g e and conversion equipment, and pad d i s t r i b u t i o n pipinp, t o pneumatic c o n t r o l panels, The v a r i o u s purging systems r e q u i r e 187,000 pounds of l i q u i d n i t r o g e n and 21,000 g a l l o n s of helium, �Pad B is v i r t u a l l y a twin of Pad A , The $op sf Pad B i s 5 f e e t h i g h e r i n e l e v a t i o n above mean sea l e v e l than Pad A t o provide b e t t e ~dratnage of t h e general area p tus b e t t e r drainage from h o P d i n ~and burn ponds. The e l e c t r i c a l s u b s t a t i o n f o r Pad B is l o c a t e d undern e a t h t h e w e s t s l o p e of t h e p a d whereas t h e corresponding s u b s t a t i o n f o r Pad A i s i n t h e open approximately 150 f e e t from t h e lower edge of t h e west s l o p s of t h e pad, The pad B d e s i g n change was made t o harden t h e s u b s t a t i o n a g a l n s t tfre launch environment. The only o t h e r major d i f f e r e n c e i s i n t h e l o c a t i o n of t h e i n d u s t r i a l / f i r e / p o t a b l e water valve p i t . A t Pad A, i t ' s on t h e west s i d e of t h e Pad and a t Pad B i t ' s on t h e east s i d e of t h e pad. The d i f f e r e n c e r e s t s i n t h e r o u t ing of water l i n e s a l o n g s i d e t h e crawlerway. Basic c o n s t r u c t i o n work on Pad B began on Dec, 7, 1964, and t h e f a c i l i b y was accepted by t h e government on August 22, 1966. The intemrening period h a s been s p e n t i n equipping t h e pad and b r i n g i n g it up t o launch r e a d i n e s s , Mission Control Center The Hission Control Center a t t h e Manned Spacecraft Center, Houston, i s t h e f o c a l p o i n t f o r Apollo flight c o n t r o l a c t i v i t i e s . 'Pbe c e n t e r r e c e i v e s t r a c k i n g and t e l e m e t r y d a t a from the Manned Space F l i g h t Network, p r o c e s s e s t h i s d a t a through t h e Mission Control Center Real-Time Computer Complex, and d i s p l a y s t h i s d a t a t o t h e f l i g h t c o n t r o l l e r s and e n g i n e e r s i n t h e Mission Operations Control Room and staff support rooms. The Manned Space F l i g h t Network t r a c k i n g and d a t a acqufaftfon s t a t i o n s link t h e f l i g h t controllers a t t h e center t o the spacecraft, For Apollo 10 a l l network s t a t i o n s w i l l be remote s i t e s , t h a t is, without f l i g h t c o n t r o l teams, A l l u p l i n k commands and voice c o m n i c a t i o n s w i l l o r i g i n a t e from Houston, and t e l e m e t r y d a t a w i l l be s e n t back t o Houston a t high speed r a t e s (2,400 b i t s - p e r - s e c o n d ) , on two s e p a r a t e d a t a l i n e s . They can be e % t h e r r e a l time o r playback information. S i g n a l flow f o r voice c i r c u i t s between Houston and t h e remote s i t e s i s v i a commercial c a r r i e r , u s u a l l y s a t e l l i t e , wherever p o s s i b l e u s i n g leased l i n e s which a r e part of t h e NASA n i c a t i o n s Network. Comands a r e s e n t from Houston t o NASA's Goddard Space F l i g h t Center, Greenbelt, Md., on l i n e s which l i n k computers a t t h e two p o i n t s . The Goddard communication computers prov i d e automatic switching f a c i l i t i e s and speed b u f f e r i n g f o r t h e command d a t a , Data a r e t r a n s f e r r e d from Goddard t o remote s i t e s on high speed (2,400 bits-per-second) l i n e s . Command loads a l s o can be s e n t by t e l e t y p e from Houston t o the remote sites a t 100 wor8-s-per-minute . Again, Goddard computers provide s t o r a g e and switching f u n c t i o n s . -more- �Telemetry data at the remote site are received by the RF receivers, processed by the pulse aede modulation ground stations, and transferred to the 642B remote-site telemetry computer for storage. Depending on the format selected by the telemetry controller at Houston, the 642B willsend the desired format through a 2010 data trans mission unit which provides parallel to serial conversion, and drives a 2,400 bit-per-second mode. The data mode converts the digital serial data to phase-shifted keyed tones which are fed to the high speed data lines of the comunications network. Tracking data are sent from the sites in a low speed (100 words) teletype format and a 240-bit block high speed (2,400 bits) format. Data rates are one sample-6 seconds for teletype and 10 samples (frames) per second for high speed data. All high-speed data, whether tracking or telemetry, which originate at a remote site are sent to cfoddard on highspeed lines. Goddard reformats the data when necessary and sends them to Houston in 600-bit blocks at a 40,800 bits-persecond rate. Of the 600-bit block, 480 bits are reserved for data, the other 120 bits for address, sync, intercomputer instructions, and polynominal error encoding. All wideband 40,800 bits-per-second data originating at Houston are converted to high speed (2,400 bits-per-second) data at Goddard before being transferred to the designated remote site. �MANNED SPACE FLIGHT NETWORK The Manned Space F l i g h t Network (MSFN) w i l l support the complete Apollo s p a c e c r a f t , o p e r a t i n g a t l u m r d i s t a n c e , f o r t h e first t i m e i n Apollo 10, The network had i t s i n i t i a l s e r v i c e w i t h l u n a r d i s t a n c e s i n Apollo 8 last December, b u t that flfght d i d n o t c a r r y t h e l u n a r module. For Apollo 10, the MSPN will employ a'? ground s t a t i o n s ( i n c l u d i r t ~thtSee wing, or backup, s i t e s ) , f s ~ i rinstrumented shLps, and s i x to e i g h b instrumented aiseraft, t o track spacecraft position and furnish a large volume of e o m u n i c a t i o n s , t e l e v i s i o n arad telemetry servfces, Essentially, t h e e n t i r e network I s d e s i ~ n e dt o provide r e l i a b l e and continuous c o m u n i c ~ t i o n sw i t h t h e a s t r o n a u t s , launch v e h i c l e and s p a c e c r a f t from l i f t o f f through l u n a r o r b i t t o splashdown. It w i l l keep ground c o n t r o l l e r s i n c l o s e cont a c t with t h e s p a c e c r ~ f tand a s t r o n a u t s a t a l l times, except f o r approximately 45 minutes when Apollo 1 0 w i l l be behind t h e Moon d u r i n g each l u n a r o r b i t =nd t h e time between s t a t i o n s w h i l e i n Earth o r b i t , As tke space v e h i c l e l i f t s o f f from Kennedy Space Center, t h e t r a c k i n g s t a t i o n s w i l l be watchine; it. A s t h e S a t u r n ascends, v o i c e and d a t a w i l l be i n s t a n t a n e o u s l y t r a n s m i t t e d t o Mission . Control Center (MCC) i n Houston. Data w i l l be run through computers a t MCC f o r v i s u a l d i s p l a y t o f l i g h t c o n t r o l l e r s . Depending on t h e launch azimuth, a s t r i n g of 30-footdiameter antennas around t h e Earth w i l l keep t a b s on Apollo 10 and t r a n s m i t information back t o Houston: beginning with t h e s t a t i o n a t Merritt I s l a n d , F l a , ; thence Grand Bahama I s l a n d , Bermuda; t h e t r a c k i n g s h i p Vanguard; Canary I s l a n d ; Carnarvon, Australia; Hawaii, t r a c k i n g s h i p Redstone, Guaymas, Mexico; and Corpus Christi, T e x . To i n j e c t Apollo 1 0 i n t o t r a n s l u n a r t r a j e c t o r y WCC w i l l send a s i g n a l through one of t h e land s t a t i o n s o r one of t h e Apollo s h i p s i n t h e P a c i f i c . A s t h e s p a c e c r a f t head f o r t h e Moon, t h e engine burn w i l l be monitored by t h e s h i p s and a n Apollo Range I n s t r u m e n t a t i o n A i r c r a f t ( A R I A ) , The A R I A p r o v i d e s a r e l a y f o r t h e a s t r o n a u t s 1 v o i c e s and d a t a communication w i t h Houston. As t h e s p a c e c r a f t moves away from Earth, t h e s m a l l e r 30-foot diameter antennas communicate first w i t h t h e spacec r a f t . A t a s p a c e c r a f t a l t i t u d e of 10,000 miles the t r a c k i n g f u n c t i o n goes t o t h e more powerful 85-foot antennas. These a r e l o c a t e d n e a r Madrid, Spain; Goldstone, C a l i f . ; and Canberra, Australia. �A R C T I C OCEAN 1 0 1 W C I C I f I C OCfAU I N D I A N OCEAN M A N N E D SPACE FLIGHT TRACKING NETWORK �The 85-foot a n t e n n a s are spaced a t approximately 120degree i n t e r v a l s around U r t h $0 at least one antenna has thp Moon in view a t glla times. As &he & r t h revolveg from we@C f;o east, one s t a t i o n hands over c o n t r o l t o t h e next s t a t i o n a@ i t moves i n t o view of Che s p a c e c r a f t . I n this way, cont$nuous d a t a and communication flow 1s maintained. Data are c o n s t a n t l y r e l a y a d back through t h e huge antennas and t r a n s m i t t e d v i a t h e NASA Communications Network (NASCOM) a h a l f m i l l i o n milea of land and underseas c a b l e s and r a d i o c i r c u i t s , i n c l u d i n g t h o s e t h m ugh communications s a t e l l i t e s , t o MCC, T h i s information i s f e d i n t o computers f o r v i s u a l d i s p l a y i n Missidn Control. For example, a d i s p l a y would show t h e exact p o s i t i o n of t h e s p a c e c r a f t on a l a r g e map. Returning data could i n d i c a t e a drop i n power o r some o t h e r d i f f i c u l t y which would r e s u l t i n a red l i g h t going on t o a l e r t a f l i g h t controller t o corrective action. Returning data flowing t o t h e Earth s t a t i o n s g i v e t h e necessary information f o r commanding mid-course maneuvers t o keep t h e Apollo 1 0 i n a proper t r a j e c t o r y f o r o r b i t i n g , t h e Moon, While t h e f l i g h t i s i n t h e v i c i n i t y of t h e Moon, t h e s e data i n d i c a t e t h e amount of r e t r o g r a d e burn necessary f o r t h e s e r v i c e module engine t o p l a c e t h e s p a c e c r a f t u n i t s i n l u n a r orbit. Once t h e l u n a r module s e p a r a t e s from t h e command module/ s e r v i c e module and goes i n t o a s e p a r a t e l u n a r o r b i t , t h e MSFN w i l l be r e q u i r e d t o keep t r a c k of both c r a f t and provide cont i n u o u s two-way communicatlons and t e l e m e t r y between them and t h e Earth, The prime antenna a t each of t h e t h r e e MSFN deep space t r a c k i n g s t a t i o n s w i l l handle one c r a f t while t h e wing o r back-up antenna a t each of t h e s e s t a t i o n s w i l l handle t h e o t h e r c r a f t d u r i n g each pass. Continuous t r a c k i n g and a c q u i s i t i o n of d a t a between Earth and t h e Apollo s p a c e c r a f t w i l l provide support f o r t h e Apollo rendezvous and docking maneuvers. T h i s information a l s o w i l l be used t o determine t h e time and d u r a t i o n of t h e s e r v i c e module propulsion engine burn r e q u i r e d t o place t h e command s e r v i c e module i n t o a p r e c i s e t r a j e c t o r y f o r reenterkng t h E a r t h ' s atmosphere a t t h e planned l o c a t i o n . A s t h e s p a c e c r a f t moves toward E a r t h a t about 25,000 miles-per-hour, i t must ree n t e r a t t h e proper angle. l Data coming t o t h e v a r i o u s t r a c k i n g s t a t i o n s and s N p s a r e f e d i n t o t h e computers a t MCC. From computer c a l c u l a t i o n s . , t h e P l i g h t c o n t r o l l e r s w i l l provide t h e r e t u r n i n g s p a c e c r a f t with t h e necessary information t o m k e a n a c c u r a t e r e e n t r y . Appropriate MSFN s t a t i o n s , i n c l u d i n g t r a c k i n g s h i p s and a irc r a f t p o s i t i o n e d i n t h e P a c i f i c f o r t h i s event a r e on hand t o provide support d u r i n g r e e n t r y . An A R I A a i r c r a f t w i l l r e l a y a s t r o n a u t voice communications t o MCC and Qntennas on r e e n t r y s h i p s w i l l follow the s p a c e c r a f t . �During t h e journey t o t h e Moon and back, t e l e v i s i o n w i l l be received from t h e s p a c e c r a f t a t t h e t h r e e 85-foot antennas around the world, i n Spain, C a l i f o r n i a , and A u s t r a l i a , Scan c o n v e r t e r s permit imediat e t r a n s m i s s i o n of c o m e r c i a 1 q u a l i t y t e l e v i s i o n v i a NASCOM t o Mission Control where I t w i l l be rel e a s e d t o TV networks. NASA Communications Network The NASA Communications Network (NASCOM) c o n s i s t s of s e v e r a l systems of d i v e r s e l y r o u t e d communications channels l e a s e d on communications satellites, common c a r r i e r systems and high frequency r a d i o f a c i l i t i e s where necessary t o provide the access links, The system c o n s i s t s of both narrow and wide-band channels, and some TV channels, Included a r e a v a r i e t of t e l e g r a p h , voice, and d a t a systems ( d i g i t a l and analog7 with s e v e r a l d i g i t a l data rates. Wide-band systems do not extend overseas. A l t e r n a t e r o u t e s o r redundancy provide added r e l i a bility, A primary switching c e n t e r and i n t e r m e d i a t e switching and c o n t r o l p o i n t s provide c e n t r a l i z e d f a c i l i t y and t e c h n i c a l c o n t r o l , and switching o p e r a t i o n s under d i r e c t NASA c o n t r o l . The primary switching c e n t e r i s a t t h e Goddard Space F l i g h t Center, Greenbelt, Md. I n t e r m e d i a t e switching c e n t e r s a r e l o c a t e d a t Canberra, Madrid, London, Honolulu, Guam, and Kennedy Space Center. F o r Apollo 10, t h e Kennedy Space Center i s connected d i r e c t l y t o t h e Mission Control Center, Houston v i a t h e Apollo Launch Data System and t o t h e Marshall Space F l i g h t Center, H u n t s v i l l e , Ala., by a Launch Information Exchange F a c i l i t y . Both of t h e s e systems a r e p a r t of NASCOM, They c o n s i s t of d a t a g a t h e r i n g and t r a n s m i s s i o n f a c i l i t i e s designed t o handle launch d a t a e x c l u s i v e l y , A f t e r launch, a l l network t r a c k i n g and t e l e m e t r y d a t a hubs a t QSFC f o r t r a n s m i s s i o n t o MCC Houton v i a two 50,000 b i t s - p e r second c i r c u i t s used f o r redundancy and i n c a s t of data overflow. Two I n t e l s a t communications s a t e l l i t e s w i l l be used f o r Apollo 10. The A t l a n t i c s a t e l l i t e w i l l s e r v i c e t h e Ascension I s l a n d u n i f i e d S-band (USB) s t a t i o n , t h e A t l a n t i c Ocean s h i p and t h e Canary I s l a n d s s i t e . These s t a t i o n s w i l l be able t o t r a n s m i t through t h e s a t e 1l i t e v i a t h e Comsat -operated ground s t a t i o n a t Etam W.Va. �A R C T I C OCEAN A R C T I C OCEAN I N D I A N OCEAN SOUTH P A C I F I C OCEAN NASA COMMUNICATIONS NETWORK �The second Apollo I n t e l s a t communications s a t e l l i t e over t h e mid-Pacific w i l l s e r v i c e t h e Carnarvon, A u s t r a l i a USB s i t e and t h e P a c i f i c Ocean ships. A l l t h e s e s t a t i o n s w i l l b e able t o transmit simultaneously through t h e s a t e l l i t e t o Houston v i a Brewster F l a t , Wash,, and t h e Goddard Space F l i g h t Center, Greenbelt, Md. Network Computers A t fraction-of-a-second i n t e r v a l s , t h e network's d i g i t a l data processing systems, with NASA's Manned s p a c e c r a f t . Center a s t h e f o c a l p o i n t , " t a l k " t o each o t h e r o r t o t h e spacecraft High-speed computers a t t h e remote s i t e ( t r a e k i n g ships included) i s s u e commands o r "up-link" d a t a on auch matters as c o n t r o l of cabin p r e s s u r e , o r b i t a l p i d a n c e commands, o r I t go-no-go" i n d i c a t i o n s t o perform c e r t a i n f u n c t i o n s , When information o r i g i n a t e s from Houston, t h e computers rere? t o t h e i r pre-programmed information f o r v a l i d i t y before transmitting t h e required d a t a t o t h e s p a c e c r a f t , Such "up-link" Information i s comminicated by ultrahigh-frequency r a d i o about 1,200 bits-per-second, Communication between remote ground s i t e s , v i a high-speed communications l i n k s , occurs a t about t h e same rate. Houston reads lnf'omation from t h e s e ground s t i e s aG 2,400 bits-per-second, as well a s from remote sites a t 100 words-per-minute. The computer systems perform many o t h e r functions, i n cluding: . . . Assuring t h e q u a l i t y of t h e transmission l i n e s by c o n t i n u a l l y e x e r c i s i n g d a t a paths. Verifying accuracy of t h e messages by r e p e t i t i v e operations, Constantly updating t h e f l i g h t status. For "down l i n k " data, sensors b u i l t i n t o t h e s p a c e c r a f t c o n t i n u a l l y sample cabin temperature, pressure, physical i n f o r mation on t h e a s t r o n a u t s such as h e a r t b e a t and r e s p i r a t i o n , among o t h e r items, These d a t a a r e t r a n s m i t t e d t o t h e ground s t a t i o n s a t 51,2 k i l o b i t s (12,800 binary d i g i t s pe r-second. A t MCC t h e computers: . Detect and s e l e c t changes o r d e v i a t i o n s , compare with t h e i r s t o r e d programs, and i n d i c a t e t h e problem a r e a s o r pertinent data t o t h e f l i g h t controllers. �, Provide d i s p l a y s t o mission personnel, . Assemble output d a t a i n proper formats, , Log d a t a on magnetic t a p e f o r r e p l a y f o r t h e f l i g h t control-lers. . Keep t i m e , The A ~ o l l oS h i ~ s The mission w i l l be supported by f o u r Apollo instrumentat i o n s h i p s o p e r a t i n g a s i n t e g r a l s t a t i o n s of t h e Manned Space F l i g h t Network (MSFN) t o provide coverage i n areas beyond t h e range of land s t a t i o n s , The s h i p s , Vanguard, Redstone, Mercury, and H u n t s v i l l e , . w i l l perform t r a c k i n g , t e l e m e t r y , and communication f u n c t i o n s f o r t h e launch phase, Earth o r b i t i n s e r t i o n , t r a n s l u n a r l n j e c t i o n and r e e n t r y a t t h e end of t h e mission, Vanguard w i l l be s t a t i o n e d about 1,030 m i l e s s o u t h e a s t of Bermuda (25 d e g r e e s N, 49 d e g r e e s W ) t o bridge t h e BermudaAntigua gap during E a r t h o r b i t i n s e r t i o n . Vanguard a l s o f u n c t i o n s as p a r t of t h e A t l a n t i c recovery f l e e t i n t h e event of a launch phase c o n t i w e n c y , The Redstone, a t 14 degrees S , 145.5 degrees E; Mercury, 32 degrees S, 131 d e g r e e s E; and H u n t s v i l l e , 1'7 dee ~ s b i l estations beg r e e s S, 174 degrees W, provide a % r i a n ~ ; lof tween t h e MSFN stations at Carrnarvsn and Hawaii f s eoveTage ~ of t h e burn i n t e r v a l f o r t r a n s l u n a r inJeetion. I n the event t n e launch d a t a slips from May 18, the ships w $ l L a i l move g e n e r a l l y northeastward t o cover the changing flight window patterns. Redstone and H u n t s v i l l e w i l l be r e p o s i t i o n e d along t h e r e e n t r y c o r r i d o r f o r t r a c k i n g , t e l e m e t r y , and communicatfons f u n c t i o n s during r e e n t r y and landing. They w i l l t r a c k Apollo from about 1,000 m i l e s away through comrnunicat i o n s blackout when t h e s p a c e c r a f t w i l l drop below t h e h o r i z o n and w i l l be picked up by t h e A R I A a i r c r a f t , The Apollo s h i p s were develop-d j o i n t l y by NASA and t h e Department of Defense, The DOD oy;(::rates t h e s h i p s - - i n support of Apollo and o t h e r NASA and DOD missions on a non-interference basis w i t h Apollo requirements, Management of t h e Apollo s h i p s i s t h e r e s p o n s i b i l i t y of t h e Commander, A i r Force Western T e s t Range (AFWTR), W e M i l i t a r y Sea T l a n s p o r t S e r v i c e provides t h e m a r i t i m e crews and t h e F e d e r a l E l e c t r i c Corp,, I n t e r n a t i o n a l Telephone and Telegraph, under c o n t r a c t t o AFWTR, provides t h e t e c h n i c a l i n s t r u mentation crews. �The t e c h n i c a l crews o p e r a t e i n accordance w i t h j o i n t NASA/DOD s t a n d a r d s and s p e c i f i c a t i o n s which a r e compatible w i t h MSFN o p e r a t i o n a l procedures. Apollo Range I n s t r u m e n t a t i o n Aircraft (ARIA) The Apollo Range I n s t r u m e n t s t i o n A i r c r a f t w i l l s u p p o r t t h e mission by f i l l i n g gaps i n both land and s h i p s t a t i o n coverage where important and s i g n i f i c a n t coverage requirements exist. During Apollo 10, t h e A R I A w i l l be used p r i m a r i l y t o fill coverage gaps of t h e ?and and s h i p s t a t i o n s i n t h e I n d i a n Ocean and i n t h e P a c i f i c between A u s t r a l i a and Hawaii during t h e t r a n s l u n a r i n j e c t i o n i n t e r v a l , P r i o r t o and d u r i n g t h e burn, t h e A R I A r e c o r d t e l e m e t r y data from Apollo provide a r e a l - t i m e v o i c e communication between t h e a s t r o n a u t s and t h e f l i g h t d i r e c t o r a t Houston. E i g h t a i r c r a f t w i l l p a r t l c i p a t e i n this mission, o p e r a t i n g from P a c i f i c , A u s t r a l i a n and I n d i a n Ocean a i r F i e l d s i n p o s i t i o n s under t h e orbital t r a c k of the s p a c e c r a f t and b o o s t e r . The a i r c r a f t . l i k e t h e t r a c k i n g s h i p s , w i l l be redeployed i n a northeastward d i r e c t i o n i n t h e e v e n t of launch day s l i p s . F o r r e e n t r y , t h e A R I A w i l l be redeployed t o t h e l a n d i n g area t o c o n t i n u e communications between Apollo and Mission Control and provide p o s i t i o n i n f o r m a t i o n on t h e s p a c e c r a f t a f t e r t h e blackout phase of r e e n t r y has passed. The t o t a l A R I A f l e e t f o r Apollo m i s s i o n s c o n s i s t of e i g h t EC-135A ( ~ o e i n g707) j e t s equipped s p e c i f i c a l l y t o meet mission needs, Seven-foot p a r a b o l i c a n t e n n a s have been i n s t a l l e d i n t h e nose s e c t i o n of t h e p l a n e s g i v i n g them a l a r g e , bulbous look. The a i r c r a f t , as w e l l a s f l i g h t and i n s t r u m e n t a t i o n crews, are provided by t h e A i r Force and t h e y a r e equipped through j o i n t A i r Force-NASA c o n t r a c t a c t i o n . A R I A o p e r a t e in Apollo m i s s l o n s i n accordance w i t h MSFN procedures. �Ship Positions f o r Apollo 10 -- 49 degrees W 131 degrees E 145.5 degrees E 172.5 degrees E Insertion Ship I n j e c t i o n Ship I n j e c t i o n Ship I n j e c t i o n Ship Reentry Suppore Reentry Skip (Hw) 25 degrees N 32 degrees S 14 degrees S 20 degrees S 17 degrees S - 174 degrees W I n s e r t i o n Ship I n j e c t i o n Ship I n j e c t i o n Ship Injection ship Reentry Support Reentry Ship (HTV) 25 32 14 13 N S S S I n s e r t i o n Ship (VAN I n j e c t i o n Ship I n j e c t i o n Ship I n j e c t i o n Ship Reentry Support Reentry Ship (HTV) 25 degrees W I n s e r t i o n Ship I n j e c t i o n Ship I n j e c t i o n Ship I n j e c t i o n Ship Reentry Support Reentry Ship (HTV) 25 degrees N Released 3 degrees S 9 degrees M I n s e r t i o n Ship I n j e c t i o n Ship I n j e c t i o n Ship (RED Indection Ship (RED) Reentrg Support Reentry Ship (HTV) 25 degrees N Released 0.5 degrees N 16 degrees N degrees degrees degrees degrees - - 49 degrees W 131 degrees E -- 145.5 degrees E 174 degrees E - - 8 degrees S 173 degrees W - 49 degrees W Released 7.5 degrees S 156 degrees E 1 degree I4 177.5 degrees E - - - 172 degrees W 10 degrees N - - 49 degrees W -175.5 158 degrees E d e ~ r e e sE 15.5 degrees N 22 degrees N - 173 degrees w - 49 degrees W - 161 degrees E - 174 degrees E - 173 degrees W �APOLLO PROGRAM MANAGENEW The Apollo Program, t h e United S t a t e s ' e f f o r t t o land men on t h e Moon and r e t u r n them s a f e l y t o Earth before 1970, i s t h e r e s p o n s i b i l i t y of the O f f i c e of Manned Space F l i g h t (OWSF), National Aeronautics and Space Administration, Washington, D.C. D r . George E. Mueller i s Associlate Administrator f o r Manned Space F l i g h t . NASA Manned Spacecraft Center (MSC), Houston, is r e sponsible f o r development of t h e Apollo s p a c e c r a f t , f l i g h t crew t r a i n i n g and f l i g h t c o n t r o l . Dr. Robert R . Q i l r u t h i s Center D i r e c t o r . NASA Marshall Space F l i g h t Center (MSFC), H u n t s v i l l e , A l a . , i s responsible f o r development o f the Saturn launch vehicles, D r . Wernher von Braun is Center D i r e c t o r . NASA John F. Kennedy Space Center (KSC), F l a . , i s r e sponsible f o r ~ p o l l o / ~ a t u r launch n o p e r a t i o n s . D r . Kurt H. Debus i s Center D i r e c t o r . NASA Goddard Space F l i g h t Center (GSFC), Greenbelt, Md. , manages t h e Manned Space F l i g h t Network under the d i r e c t i o n of the NASA Office of Tracking and Data Acquisition (OTDA). Gerald M. Truszynski i s Associate Administrator f o r Tracking and Data Acquisition. D r . John F. Clark i s Director of GSFC, Apollo/Saturn O f f i c i a l s NASA HEADQUARTERS L t . Gen. Sam C, P h i l l i p s , (USAF) Apollo Program D i r e c t o r , OMSF George H. Hage Apo 110 Program Deputy Director, Mission D i r e c t o r , OMSF Cnester M. Lee A s s i s t a n t Mission D i r e c t o r , OMSF :ol. A s s i s t a n t Mission Director, OMSF Thomas H. McMullen (USAF) Maj. Gen. James W. Humphreys, J r . Director o f Space Medicine, OMSF Norman Pozinsky Director, Network Support Implementation Div. , OTDA �Manned Spacecraft Center George M. Low MBnager, Apollo Spacecraft Program Kenneth S . Kleinknecht Manager, Command and Service Modules B r i g . Gen, C. H. Bolender (USAF) Manager, Lunar Module Donald K. Slayton Director of F l i g h t Crew Operations Chrf stopher C, Kraft , Jr. Director of' F l i g h t Operations Glynn S. Lunney F l i g h t Director Milton L. Windler F l i g h t Director M. P. Frank F l i g h t Director Gerald G r i f f i n F l i g h t Director Charles A. Berry Director of Medical Research and Operations Marshall Space F l i g h t Center Ma3. Gen. Ednn;md P. OtConnor Director of I n d u s t r i a l Operations D r . F. A. Speer Director o f Mission Operations Lee 33. James Manager, Saturn V . Program Off i c e William D. Brown Manager, Engine Program Office Kennedy Space Center Miles Ross Deputy Director, Center Operations Rocco A. Petrone Director, Launch Operations Raymond L. Clark Director, Technisal Support Rear Adm. Roderick 0. Middleton (USN) Manager, Apollo Program Office Walter 3, Kapryan Deputy Director, Launch Operations D r . Hans F. Gruene Director, Launch Vehicle Operations John 3 . Williams Director, Spacecraft Operations �Paul C, DDnnelly Launch Operations Manager Goddard Space Flight Center Assistant Mrector POP Manned Space Flight Tracking - Henry F. Thompson Deputy Assistant Director f o r Manned Space Flight Support H. W i l l i a m Wood Chief, Manned Flight Operations Tecwyn Roberts Chief, Manned F l i g h t Engineering Div. Div. Department of Defense Maj. Gen. Vincent Q . Huston, (USAP) DOD Manager of Planned Space Flight Support Operations Maj. Gen. David M. Jones, (US-) Deputy DOD m g e r of Manned Space Flight Support Operations, Commander of USAF Eastern Test Range Rear A m , F. E. Bakutis, (USW) Commander of Combined Task Force 130, Pacific Recovery Area Rear Adm. P. S. PLcManus, (USN) Commander of Combined Task Force 140, Atlantic Recovery Area Col, Royce G. Olson, (USAF) Director of DOD Manned Space Flight Office Brig. Gen. Allison C. Brooks, Commander Aerospace Rescue and Recovery Service (USAP) �Pllajor Apollo/Satucn V Contractors Contractor Item Bellco~pn Washington, D, C. Apollo Systems Engineering The Boeing Co. Washington, D. C, Technical I n t e g r a t i o n and Evaluation General E l e e t r i c -Apollo Support Dept,, Dagtona Beach, Bla, Apollo Checkout, and Quality and Reliability North American Rockwell Corp. Space D i v e , Downey, Callf. Command and S e w i c e Modules Grumman A i r c r a f t Engineering Corp, , Bethpage, N. I. Lunar Module Massachusetts I n s t i t u t e of Technology, Cambridge, Mass. Guidance h Navigation (Technical Management) General Motors Corp., AC Electronics Div., Milwaukee, W i s . Guidance & Navigation (~anufacturing) TRW Systems Inc. Trajectory Analysis Redondo Beach, C a l i f . Avco Corp., Space Systems D i v . , L o w e l l , Mass, H e a t Shield Ablative Material North American Rockwell Corp, Rocketdyne D i v . Canoga Park, Calif. 3-2 Engines, F-1 Engines The Boeing Co. Mew Orleans F i r s t Stage (SIC) of Saturn V Launch Vehicles, Saturn V Systems Engineering and Integration, Ground Support Equipment North American Rockwell Corp, Space Div, Seal Beach, Calif. Development and Production of S a t u r n V Second Stage (s-11) McDonnell Douglas Astronautics Co. Huntington Beach, Callf. Development and Production of Saturn V . Third Stage (s-IVB) �International Business Machines Federal Systems Div, Huntsville, Ala. Instrument Unit Bendix Corp. Navigation and Control Div. Teterboro, N . 3 . Guidance Components for Instrument Unit (Includin Stabilized Federal Electric Corp. Communications and Instrumentation Support, KSC Bendix Field Engineering Corp. Launch Operations/Complex Support, KSC Catalytic-Don Facilities Engineering and Modifications, KSC Hamilton Standard Division United Aircraft Corp. Windsor Locks, Conn. Portable Life Support System; LM ECS IiC Industries Dover, Del. Space Suits Radio Corp. of America Van Nuys, Calif. llOA Computer Sanders Associates ACashua, N . H . Uperat iona1 Display Systerns Brown Engineering Huntsville, Ala. Discrete Controls Reynolds, Smith and Hill Jacksonville, Fla. Engineering Desfgn of Moblle Launchers Ingalls Iron Works Birmingham, Ala. Mobile Launchers (ML) (structural work) Srnith/Ernst (foint Venture) Tampa, Fla. Washington, D, C. Electrical Mechanical Portion Power Shovel, Inc. Marion, Ohio Transporter Hayes International Birmingham, Ala Mobile Launcher Service Arms . - Saturn Checkout Saturn of E4Ls �APOLLO GLOSSARY Ablating Materials--Special heat-dissipating materials on the surface of a spacecraft that vaporize during veentry. Abort--The unscheduled ternination of a mission prior to its completion, Accelerometer--An instrument to sense accelerative forces and convert them into corresponding electrical quantities usually for controlling, measuring, indicating or recording purposes. Adapter Skirt--A flange or extension of a stage or section that provides a ready meaner of fitting another stage or section to It. Antipode--Point on surface of planet exactly 180 degrees opposite from reciprocal point on a line projected through center of body. In Apollo usage, antipode refers to a line from the center of the Moon through the center of the Earth and projected to the Earth surface on the opposite side. The antipode crasses the mid-Pacific recovery line along the 165th meridian of longitude once each 24 hours. Apocynthion--Point at which object In luna orbit is farthest from the lunar surface object having been launched from body other than Moon. ( , Romm goddess of Moon) -- Apogee--The point at which a Moon or artificial satellite in its orbit is farthest from -rth. Apolune--Point at which object launched from the Moon into lunar orbit is farthest from lunar surface, e,g.: ascent stage of lunar module after staging into lunar orbit fillowing lunar landing . Attitude--The position of an aerospace vehicle as detemined by the inclination of its axes to some frme of reference; for Apollo, an Inertial, space-fixed reference is used. Burnout--The point when combustion ceases in a rocket engine. Canard--A short, stubby wing-like element affixed to the launch escape tower to provide CM blunt end forward aerodpamic capture durlng an abort. Celestial Guidance--me guidance of a vehicle by reference to celestial bodies. �C e l e s t i a l Mechanics--The science t h a t d e a l s primarily with t h e e f f e c t of force as an agent i n determining the o r b i t a l p a t h s of c e l e s t i a l bodies. Cislunar--Adjective r e f e r r i n g t o space between Earth and t h e Moon, o r between Earth and Moon18 o r b i t . Closed Loop--Automatic c o n t r o l u n i t s 1l.nked t o g e t h e r w i t h a process t o form an endless chain, Deboost--A retrograde maneuver which lowers either perigee o r apogee of an o r b i t i n g s p a c e c r a f t , Not t o be confused with deorbit. &elination--Angular measurement of a body above o r below c e l e s t i a l equator, measured n o r t h o r south along t h e body's hour c i r c l e . Corresponds t o Earth surface l a t i t u d e . Delta V--Velocity change. D i g i t a l Computer--A computer i n which q u a n t i t i e s a r e represented numerically and which can be used t o solve complex problems, Down-Link--The part o f a communication system t h a t r e c e i v e s , proc e s s e s and d i s p l a y s d a t a from a s p a c e c r a f t . E n t r y Corridor--The f i n a l f l i g h t path of the s p a c e c r a f t before and during Earth r e e n t r y . Ephemeris--Orbital measurements (apogee, perigee, i n c l i n a t i o n , period, e t c . ) of one c e l e s t i a l body i n r e l a t i o n t o another a t given times. I n s p a c e f l i g h t , t h e o r b i t a l measurements of a s p a c e c r a f t r e l a t i v e t o the c e l e s t i a l body about which it orbited. Escape Velocity--The speed a body must a t t a i n t o overcome a g r a v i t a t i o n a l f i e l d , such as t h a t of Earth; t h e v e l o c i t y of escape a t the E a r t h ' s s u r f a c e i s 36,700 feet-per-second, Explosive Bolts--Bolts destroyed o r severed by a surrounding explosive charge which can be a c t i v a t e d by an e l e c t r i c a l impulse, Fairing--A piece, p a r t o r s t r u c t u r e having a smooth, streaml i n e d o u t l i n e , used t o cover a nonstreamlined o b j e c t o r t o smooth a junction. P l i g h t Control System--A system t h a t s e r v e s t o maintain a t t i t u d e s t a b i l i t y and c o n t r o l during f l i g h t , �Fuel Cell--An electrochemical generator i n which t h e chemical energy from t h e reaction of oxygen and a fuel La converted d i r e c t l y i n t o e l e c t r i c i t y . e x e r t e d upon an o b j e c t by gravity o r by r e a c t i o n t o a c c e l e r a t i o n o r d e c e l e r a t i o n , as In a change o f d i r e c t i o n : one g is t h e measure o f f o r c e required t o a c c e l e r a t e a body a t t h e rate of 32.16 feet-per-second. g o r g Force--Force on a Gimbaled Motor--A rocket motor mounted on gimbal; 1.e.: contrivance having two mutually perpendicular axes o f rot a t i o n , so as t o o b t a i n p i t c h i n g and yawing c o r r e c t i o n moments. Guidance System--A system which measures and e v a l u a t e s f l i g h t information, c o r r e l a t e s t h i s with t a r g e t d a t a , converts t h e r e s u l t i n t o t h e conditions necessary t o achieve t h e d e s i r e d f l i g h t path, and communicates t h i s d a t a i n t h e form of commands t o t h e f l i g h t c o n t r o l system. Heliocentric--Sun-centered Sun a t i t s c e n t e r . o r b i t o r o t h e r a c t i v i t y which h a s the I n e r t i a l , Guidance --Guidance by means o f t h e measurement and i n t e g r a t i o n of a c c e l e r a t i o n from on board t h e s p a c e c r a f t . A s o p h i s t i c a t e d automatic navigation system using gyroscopic devices, accelerameters e t c . , for high-speed v e h i c l e s . It absorbs and i n t e r p r e t s such d a t a a s speed, p o s i t i o n , e t c . , and automatically a d j u s t s t h e vehicle t o a pre-determined f l i g h t path. E s s e n t i a l l y , i t knows where i t ' s going and where it i s by knowing where i t came from and how i t g o t t h e r e . It does n o t give out any r a d i o frequency s i g n a l ao i t cannot be detected by r a d a r o r jammed. Injection--The process of boosting a s p a c e c r a f t i n t o a calculated trajectory. Insertion--The process o f boosting a s p a c e c r a f t i n t o an o r b i t around the Earth o r o t h e r c e l e s t i a l bodies. Multiplexing--The siaiultaneous transmission of two o r more s i g n a l s within a s i n g l e channel. The t h r e e b a s i c methods of multiplexing involve t h e s e p a r a t i o n of s i g n a l s by time d i v i s i o n , frequency d i v i s i o n and phase d i v i s i o n . O p t i c a l Navigation--hlavlgation by s i g h t , as opposed t o i n e r t i a l methods, using stars o r o t h e r v i s i b l e o b j e c t s as reference. Oxidizer--In a rocket p r o p e l l a n t , a substance such as l i q u i d oxygen o r n i t r o g e n t e t r o x i d e which supports combustion of the mel. �Penumbra--Semi-dark portion of a shadow in which light is partly cut off, e .g. : surface of Moon or Earth away from Sun where the disc of the Sun is only partly obscured, Pericynthion--Point nearest Moon of object In lunar orbit--object having been launched fron body other than Moon. Perigee--Point at which a Moon or an artificial satellite I n its orbit is closest to the Earth. Perilune--The point at which a satellite ( e , g . : a spacecraft) in its orbit is closest to the Moon. Differs from pericynthion in that the orbit is Moon-originated. Pitch--The movement of a space vehicle about an axis (Y) that is perpendfcular to its longitudinal axis. Reentry--The return of a spacecraft that reenters the atmosphere after flight above it. Retrorocket--A rocket that gives thrust in a direction opposite to the direction of the object's motion. - Right Ascension -Angu lar measurement of a body eastward alon the celestial equator Prom the vernal equinox (0 degrees RAY to the hour circle of the body. Correaponds roughly to Earth surface longitude, except as expressed in hrs:min:sec instead of 180 degrees west and east from 0 degrees (24 hours-360 degrees) . Roll--The movements of a space vehicle about its longitudinal (x) axis. S-Band--A radio-frequency band of 1,550 to 5,200 megahertz. Selenographic--Adjective relating to physical geography of Moon. Specifically, positions on lunar surface as measured in latitude from lunar equator and in longitude from a reference lunar meridian. Selenocentric--Adjective referring to orbit having Moon as center. (~elene,Or. Moon) Sidereal--Adjective relating to measurement of time, position or angle in relation to the celestial sphere and the vernal equinox. State vector--Ground-generated spacecraft position, velocity and timing information uplinked to the spacecraft computer for crew use as a navigational reference. �Telemetering-A system for taking measurements within an aerospace vehicle in flight and transmitting them by radio to a ground station. Terminator--Separation line between lighted and dark portions of celestial body which is not self luminous. Ullage--me volme in a closed tank or container that is not occupied by the stored liquid; the ratio of this volume to the total volume of the tank; also an acceleration to force propellants into the engine pump intake lines before ignition. Umbra--Darkest part of a shadow in which light is completely absent, e-g.: surface of Moon or Earth away from Sun where the disc of the Sun l a completely obscured. Update pad--Information on spacecraft attitudes, thrust values, event times, navigational data, etc., voiced up to the crew in standard formats according to the purpose, e.g,: maneuver update, navigation check, landmark tracking, entry update, etc. Up-Link Data--Information fed by radio signal from the ground to a spacecraft . Yaw--An l a r displacement of a space vehicle about its vertical ( zraxis . �APOLLO ACRONYMS AND AIEIBREVIATIONS (Note: This l i s t makes no attempt t o inelude a l l Apollo program acronyms and abbreviations, but s e v e r a l are l i s t e d t h a t w i l l be encountered frequently i n the Apsllo 10 mission. Where pronounced a s words i n a i r - t o -ground transmissions, acronyms a r e phonetically shown i n parentheses. Otherwise, abbreviations a r e sounded out by l e t t e r . ) AGCS (At3gs ) Apogee kick AK APS Abort Guidance System ( W ) (APP~) Aacent Propulsion System (LM) Awtiliaqy Propulsion System (S-IVB s t a g e ) (Be-WZ) Body mounted a t t i t u d e gyro CBSf Constant delta height CMC Cornand Module Computer COI Contingency o r b i t i n s e r t i o n CRS Concentric rendezvous sequence CSI Concentric sequence i n i t i a t e DAP (~PP) Digital autopilot DEDA ( Dee -da ) Data Entry and Display Assembly (MIAQS) DFI Development f l i g h t instrumentation DO1 Descent o r b i t i n s e r t i o n DPS ( Dips Descent propulsion system DSKY ( isk key ) Display and keyboard EPO Earth Parking O r b i t FDA1 Flight director attitude i n d i c a t o r FIllI (Fith) F i r e In the hole (LM ascent a b o r t staeing) Fixed t h r o t t l e point High-gain antenna I n e r t i a l measurement u n i t �APOLLO ACRONYMS AND ABBREYIATIONS (Note: T h i s l i s t makes no attempt t o include a l l Apollo program acronyms and abbreviations, but s e v e r a l a r e l i s t e d t h a t w i l l be encountered frequently i n the Apollo 10 mission. Where pronounced a8 words i n air-to-ground transmissions, acronyms a r e phonetically shown irP parentheses. Otherwise, abbreviations a r e sounded out by l e t t e r ) . Abort Guidance System ( W ) Apogee kick APS B31AQ A ~ c e n tPropulsion System (IN) Auxiliary Propulsion Sy~rtem(s-IVB atage) (Bee--) Body mounted a t t i t u d e gyro Constaikt d e l t a height CMC Cormnand Module Computer Contbgency o r b i t i n s e r t i o n CRS Concentric rendezvous sequence CSI Concentric sequence i n i t i a t e DAP Digital autopilot DEDA Data Entry and Display Assembly (LM AM) DFI 1)evelopment f l i g h t instrumentation Descent o r b i t i n s e r t i o n DPS Descent propulsion system DSKY Display and keyboard EPO Earth Parking O r b i t Flight director attitude indicator FITH F i r e in the hole (LM ascent abort staging PPP Fixed t h r o t t l e point High-gain antenna I n e r t i a l measurement u n i t �IRIO I n e r t i a l ra%e i n t e g r a t i n g gyro LO1 Lunar o r b i t f n s s r t i o n LPO Lunar p a r k i w o r b i t MCC Misaion Control Center MC&W Master caution and warning MSI Moon sphere of influence MTVC Manual t h r u s t vector c o n t r o l NCC Combined c o r r e c t i v e maneuver NSR C o e l l i p t i c a l maneuver PIPA ( f ippa) Pulse i n t e g r a t i ~pendulous accelerometer PLSS (~lisro) Portable l i f e support system Passive the PTC mas (Pugs) Propellant u t i l i z a t i o n and gaging systern REFSWT ( ~ esmat) f Reference t o s t a b l e member matrix RHC Rotation h m d c o n t r o l l e r R E Real-time a s SCS S t a b i l i z a t i o n m d c o n t r o l system SLA Spacecraft LM adapter SPS Service p r o ~ l s i o nsystem TEI Transearth I n j e c t i o n THC Thrust hand c o n t r o l l e r TLI Translunar InJection TPF Terminal phase f i n a l i z a t i o n TPI Terminal phase I n i t i a t e TVC Thrust vector c o n t r o l d �CONVERSION FACTORS Multiply 2 To Obtain feet 0,3048 meters Distance : feet kilometers feet kilometers statute miles statute miles kilometers nautical miles kilometers nautical miles statute miles statute miles nautical miles statute mile yards feet/sec meters/sec Velocity: feet/sec statute mph statute miles/hr nautical miles/hr statute miles/hr 1.609 km/hr nautical miles/hr (knots) 1.852 km/hr statute miles/hr Liquid measure, werkht : gallons liters liters gallons pounds kilograms kilograms pounds - more - �Multiply 8 To Obtain cubic f e e t 0.02832 cubic meters pounds/sq i n c h 70.31 grarns/sq cm Volume : Pressure : � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000071 Title A name given to the resource Apollo 10 press kit. Description An account of the resource The press kit includes documentation on the Command and Service Module, Lunar Module, Saturn V launch vehicle, astronauts, and mission descriptions. Release No. 69-68. Creator An entity primarily responsible for making the resource United States. National Aeronautics and Space Administration Date A point or period of time associated with an event in the lifecycle of the resource 1969-05-07 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Project Apollo (U.S.) Space flight to the moon Saturn launch vehicles Saturn Project (U.S.) Type The nature or genre of the resource Press kits Text Source A related resource from which the described resource is derived Saturn V Collection Box 31, Folder 30 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000051_000074 https://digitalprojects.uah.edu/files/original/20/1158/spc_stnv_000074.pdf 582f903466de2079bb829d2764795375 PDF Text Text APOLLO 6 PRE-LAUNCH PRESS CONFERENCE Cape Royal Mews Center, 'Cocoa Beach John F. Kennedy Space Center IJational Aeronautics and Space Administration Wednesday, April 3, 1968 Participants William C. Schneider, Apollo ~ i s s i b nDirector, NASA Geargo, M Low, Apol lo Spacecraft Manager ,i\IASA Clifford Charlesiyorth, Apollo 6 Flight Director, Manned Spacecraft Center, NASA Dr. Arthur Rudotpf~, Saturn V Proyrs.m Office, Mzushali Space Fli yht Center,NASA Rocco A. Pctrone, Apollo 6 Launch Director, l(cnnedy Space Center, NASA Cof. Royce Olson, USAF, Director DOD Lhnned Spacerlight Suppott Orfice, Patrick AFB Chris Kraft, Director of Fliai~tOperations, Manned Spaceciaft Center . �Mr. King: May I have your attention please? We're ready to proceed with the Apollo 6 prelaunch briefing at this time. I ' d l i k e t o cover a few logistics before we go into the actual conference here. W e ' l l be open a l l night tonight. The phone nunrber for any new arrivals who have not been with us before i s 783-7781. We'll have somebody on duty a l l night and through the morning hours leading up t o launch. You've a l l been accredited. You have your badges. You have the instructions you require to find your way out to the press site a t Launch Complex 3'9. You w i l l be able to take your own transportation out there. There w i l l be a guard who w i l l direct you to the parking lot which i s located right i n front of the press site itself. We request that you don't go up on the mound a t the press site, but bring your car into the parking lot i n front. W e ' l l start a commentary at about 2 a.m. tomorrow rnouning, rugning about every half hour until the crowd grows a l i t t l e larger. We w i l l be giving a complete commentary later i n the c o ~ l n t . The countdown commentary w i l l be handled from here until we clear thc tower a t l ifkoff a t which time it w i l l switch to the Manned Spacecraft Center i n tlouston, I n addition to your own transportation we w i l l have a bus departing here roughly on the hour, starting at r i i d n i ~ k t , with i t s last departure from the News Center at 5 : 3 0 a.m. tomorrow. You a l l might keep i n mind that i t ' s possible there could be some pretty good traffic i n the xrea as we get close to launct.1 time and it might behoove you a l l l o consider leaving early enough to notgget caught i n traffic a t the last minute. W e ' l l have a post-launch briefing at the press site at T plus 60 minutes. T h i s w i l l be followed by a second conference, a post-*mission briefing, which w i l l occur about ten hours after launch. This also will be a twoway conference, with participants from both the Kennedy Space Center and the PJlanned Spacecraft Center i n Houston. I ' d now like to introduce these gentlemen to you here, and one gentleman who i s also standing by for us at the PAanned Spacecraft Center i n I-louston. T h i s w i l l also be a two-way conference. We w i l l first take questions from here and then stvitch to your colleaqiies i n !-!ouston so that they will also have an opportunity to asl: questions. �To niy right, here at l<SC, Mr. George M. Low, viho i s Apollo Program Manager for the NASA Manned Spacecraft Center. Mext, Mr. \Nilliani Schneider, Office of Maniiecl Spaceflight, NASA Headquarters MrSchneider i s Apollo blission Director. Next Rocco Petrone, w l ~ oi s Director of Launch Operations for the Kennedy Space Center, and Launch Director for tlie Apollo 6 fligf~t. Next wc have Dr. Arthur Rudolph. Dr. Rudolph i s the Saturn V Progratn Manager from the Marsl~allSpace Fliglit Center. And Colonel Royce Olson, who i s Director of the Department of Defense F.4anned Spaceflight Support Office a t Patrick A i r Force Base. Also, standing by i n Houston, i s Mr. Cliff Charlesworth, who i s the 5 0 2 Flight Director, the Apollo 6 Flight Director for this mission at MSC. -- Mr. Kraft: I'd now like to turn it over to Mr. Schneider. Excuse me. I also understand, l'nl sorry Chris, we also have Mr. Chris Kraft, who i s Director of Fliglit Operations for the Manned Spacecraft Center, also standing by i n Houston. .Bill, would you take over please., Mr. Schneider: Good afternoon, ladies and gentlen~en. First I'd like to'apologize for the hour and a half delay. 1 assure you we were worlting and weren't just loafing. We have just completed oirr final review of the spacecrafi and tlie lairnch ve'l~icleand the entire comp!ex' as well as the netci~orkand the BOD forces, and we've conipleted our review of the weather, and everything i s at this time GO!. . The weather situation, as reported to 11sby the ESSA people, i s basically that early i n the morning the weather w i l l be much like this, as it i s out here today, that is, with clear and gentle winds, with deterio:ating conditions toward the afternoon, with ar. expected wind velocity reaching as rnuch as a peak of 25 knots sonletirnc later i n tlie day. But v ~ eare on scttediile aild moving out for an 0700 launch tomorrow morning, that's 0 7 0 0 Eastern Standard. The close of the window for tomorrow w i l l be dependent upon ille conditior?~ i n the recovery zone. VIe have set a requirerr~entthat t f con:litions ~ in thc recovery zone be such that the onsite commander can give us reasona!)ie assurance that he w i l l be able to successfully vecover the spacecraft. Vie expecl the close of that window to be, i f contlitions arc very good, on t t ~ c order of noon cr 1230 EST. �T h i s is, of course, the final qualification flight on the Saturn V launch vehicle, since we have previously qualified the command and service modules and the lunar module for manned flight i n previous missions. We are looking forward to having a goocl la~lnchvehicle flight, and as a niatter of fact, a good spacecraft flight, too, George, but as I said, the spacecraft objectives are on this tnission, secondary. It i s even conceivable that, and I stress the word conceivable, that the mission may have accomplished a l l of i t s primary mission objectives at the time of insertion into orbit, although, of course, that couldn't be determined for quite a long time. We do have one, I shall not call it a dark cloud, but one question mark, and this i s the question that kept us out at the Launch Control Center for the past couple hours. That i s the question of a temperature that we experienced during the Countdown Demonstration Test on the S-Il stage J-2 engines where some of the propellant pump discharge temperatures were a few degrees above what we call our redlinc values, that i s the values that we expect to achieve for launch. We have taken some corrective action and we have examined it. We think we've solved the problem. We have reaso~ablehope that we've solved the problem. However, there i s no way to test whether we w i l l achieve the proper redline withoui going through a cryogenic test and so the cryogenic test i s going to be i n the morning. If, for example, we do not achieve this proper temperature on the first cycle we w i l l be forced to do what we did during the CDDT, and that is, namely, cut off, stop at about 22 seconds 0: thereabouts and recycle back t o about 24 minutes, then wait and assess the problem and see whether or not we can stabilize conditions again, and try again. Wopefully that w i l l not happen, but it i s a very distinct possibility. With that, I'd like to turn it over to Rocco and ask Col. Petronit i f he would now give LIS a discussion of how things have been going out at the Cape. �Mr. Petrone: Well, we have been busy, as yo11 know. We finished our Countdown Demonstration Sunday, then we had to recycle for the count and also work our way throtrgh.sorne of the things we found i n the Countdown Demonstration, but we succeeded in picking up the count at one o'clock this morning. We have a final 24hour terminal count which we picked up at one, and at the time as of now, I understand the count is on . we left tliere schedule. We plan a hold at the eight-hour mark, T minus eight hours. We plan a hold of six hours. We have no scheduled work and at this time it does not appear that there will be any necessary within that hold; We zre on schedule with a!l of our checks, everything is going fine. So, roughly at 1700, in another hour and fifteen minutes, we w i l l complete our task on schedule, We w i l l have a six-hour hold and pick up again at 11o'clock tonight for the Final portion of the count of eight hours to a seven o'clock l iftoff. -- -- A t 10:30 p,m. we w i l l have a look at the weather to see i f the situation has changed. Right now, the forecast would indicate tfiat our niort~ingtime is the best time to go, that is Thursday morning. We w i l l take a look at the weather at lO:30, then commit at 1 1 : 0 0 p.m., that is EST, at T rnitius eight in our count for the launcli. A t T minus seven hours vie stait our cryogenic tanking and shortly theuezfter we will stati getting cryogenics into the stage. Up until T minus eight hours vJe can s i t there and . recycle on a 24-hour basis. I f we dccidc not to pick up the count a t 13.:00, and assuming we had no prob!er?i causir~g11s to go i n and change something, we could s i t there and hold,, 'vV~can do that through Saturday as tve now see it. We could wait through Thursday, Friday and Saturday on our latrnch attempts, asstlining far. some reason 'at T minus eight Iiouus we do not want to pick up the count, other than for hardware difficulties somewht?~in the program, Once we get our cryoga~icsaboard the stage we thei~are in the . positiot~of a 72-hour recycle. These are my conclusior~son wherz we have been and what we have bee!^ doing since our CDDT ended, and now we expt.ct to pick up the count at 11:GO p.m. for a launch s t 7: 0 0 a.m. Col. Olsot~: Departn:ent of Defense support for this mission is essentially the 50 1, hie have roi~yhl.y45 airsame as it was for Apollo 4 craft and 1.1 ships involved. CZ'c are taking advantage of this unmanned mission, of col!ae, to fuither t~ai!; o w crews and check S zrt? con~ir~g iilto the out the eyuipn~entOII the new Y C S D ~ ~ Y C Cti:zk -- �inventory to support Apollo, such as the Apollo ships and the ARIA aircraft, There w i l l be two aircraft in the Hawaiian area for reentry, there w i l l be three of them out here in the Atlantic, There are three Apollo ships involved. One of them, the Mercury, is sitting out here in the port, but we are getting training as the spacecraft passes over, so i f you're interested in Apollo ships, there is one right here at the port. Question: I'd like a recap on the postponements, the seriousness of them, etc,, from March 2 1. There have been five postponements, is that correct? MY, Schneider: I don't know the numbers. We did stark out for March 21, We did have a number of minor probtems, normal problems. Perhaps Rocco would like to go into them, Mr. Petrone: , Those of us working in the program, doing the job day by day, perhaps don't see much of the calendar shifts -- there are shifts throughout our scheduleo I can't think of anything -- you see, in the CDDT we did have three attempts. On one attempt we had a leak in the facility, that we had to repair. On a second attempt we had fuel difficulties. So it was those kind of problems that went on and moved us from the 2 I s t to the 4 t h -- throughout our preparation schedule, 1 can't recall a single large item that we changed out,, There was additive work, things took a l i t t l e longer at;d on some of our tasks, either we didn't hit it the First time or had to go. back i n and change a component, but there was nothing significantly large that gave us a two week s l i p by itself, There were many additive situations. Question: I'd I ike to ask George Low if a!! the objectives of thc spacecraft are regarded as secondary as f a as he is concerned, is there anything that could happen to the spacecraft, including washout or failure to recover, that might mxke you want to have another preparztory fl ight before manned flight ? Mrb Low: Wel I, I have to say yes to that question, but I can't give you a more specific answer, IF we should lose a spacecraft because of a spacecraft failure, we would hate to lool< at that failur2 t o determine whether we would need another flight or car? solve it by ground test or analysis or what have you, These questions are very difficult to answer before a flight, b[r"tome very easy after a fl iyht, �Question: For Mr. Sctllreider or Mr, Petrone, Can you explain in a little further detail the J-2 pump discharge problem? Mr. Petrone: We have a redl ine that we have to zchieve in order to assure that whe1.1your turbopump starts pumping your liquid oxygen or your l iquid hydrogen into your engine, that you do not cavitate. The term means that you don't convert the fluids into gases, because you want to deliver liquids. You want to del iver a good sol i d liquid, This has to do with ten~peratureand pressure. So we have a temperature reading that we look for at the engine inlet, The redl ine we're looking for and we're set at, is minus 286 degrees Fahrenheit, It .is now, with looking at the engines specifically and having run through our Countdown Demonstrat ion Thursday, we have, in effect, raised that two degrees to minus 284 and what you're doing here is looking for a number that ~ v j l assure l that the pumps function properly so that the liquid doesn't gasify as it goes through the pumps. These are very cold liquids and as you s i t there, you tend to pick up heat, just by virtue 6f the fact that they ar2 cryogenic. So the question of a redline on an engine, and it has to do with these particular engines and the head that you have on it, the prim2 purpose of it is to prevent cavitation or to prevent the Iiquids from being converted to a gas before you get t o the injector of that engine, �Question: May I follow up on that? M r . Petrone: Yes. Quest ion: This was on the oxygen side, rather than on the hydrogen? Mr. Petrone: We had actually, Bill, three on the oxygen side and one on the hydrogen side. We had one hydrogen feed line and three oxygen feed lines i n the second stage wherein we were, say, a few degrees hotter than the redl ine l imits . Quest ion: You don't redline hydrogen at any temperature as high as minus 286, do you? M r . Petrone: No. The number I gave was for oxygen. Hydrogen i s minus 420, i f my memory serves, minus 420. Question: Can you account for the heat sources? Dr. Rudolph: No. Really , t h i s i s not so easy to explain. We know that there must be a change i n the heat source, but what it really i s we are s t i l l struggling with. It could be. . . .. . . Question: I s this a novel situation? Has it ever happened before? Dr. Rudolph: It has not happened before. Mr. Petrone: It did not happen on 5 Q l . However, i t has beet1 seen on prior programs. Dr. Rudolph: Maybe 1 can say the following. Since this compartment where these engines are we can only test here at the Cape for the f i r s t time, not i n our captivefirirrjs on our test stands, and therefore the conditions are entirely differetit because n~!rdthe engines are enclosed and are between the oxygen tank of the second stage and the oxygen tank on the first stag?. .So we have to d2liver h2aE to protect against too much cold. Now any slight cha~gc!in the construction, an insulation change, would affect the condition in there We ti;lve taken covrcctive action by inproving insulation and as Racco already meniioned, we changed the rc;dli;le so we c-an accept a highet. tenrpeiature, but what it w i l l really turn o ~ r tomorrow t rilorniny, we don't kuov~for suye. . �Question: One part of my question may.have been answered. You changed the redline. Was that the figure you gave, Rocco ,two degrees difference; and how much different.was it; was it the CDDT when this turned up? How many degrees was it past the redline value? Mr. Petrone: It was about four or five below---or hotter---with these temperatures we're working i n the negative. We were five degrees warmer than we wanted toebe and there was some variation between the engines, but about five degrees. Dr. Rudolph: That was the worst one. The others were better. Now here we can, we have done some improved insulating and I think it w i l l contribute to a better condition and also, we changed the redline. We give two degrees, so that we think w i l l get off i n the stock box, what we call it. The engines are very sensitive to temperatures and pressures and that should do the trick. Again, we are not sure. Question: I s this only on the S-ll? Dr .. Rudolph: That's only on the S-li Question: What i s getting too hot, the cryogznics or some of the metal? Mr. Petrone: The cryogenics. Tile cryogenics ur,der the head and under the pressures in effect get superheated and that!s what this increase i n temperature is. Question: This i s for Mr. Schneider. Last week Bob Moser told us that his people are anxious to get the 503 vehicle out on the pad within ten days, i f it has to be unmanned, and he'd like to have a decision from you within seven days whether it's going to be manned or unmanned. Could you give him one i n t!mt time? Mr. Schneider: Well, I'll hasten to state that tile decision i s not mine. (Laughter). . A l l 1 car1 say i s that ttls decision w i l l be made as soon as there i s an adequate analysis of the data, so that we can determine whether or not the mission satisfied all of our requirements. As a little aside, it's difficult sometimes at the completion of 2 mission to determice whether or not it is a completely si~ccessfulmission, because you've got to await analysis of all of the data. You can have what appeals to bc a pcrfect mission 2nd i f you had a telemetry t Iiave no clata frorn thc tcchrrical link go out or a niuliiplexer yo o ~and statidpoint, it's a cornpletz failiire . �Similarly, on the other hand, you can have one where things change considerably during the mission, such as what happened on Apollo 5, but you get a i l of the data that you've been really looking for in the flight. So it w i l l take some time to make tha: decision and we a l l know how everyone wants the decision as early as possible. So that's a l l I can say now. Question: To follow that up, i f you don't say have a decision within ten or twelve days but it s t i l l looks goad, would you hold up the rollout of the 503 to the pad? Mr. Schneider: I think we'd wait, that we'd hold that decision and make that wtien we see how good the data i s or how bad the data i s . W e ' l l maice that depending on how it looks. Quest ion: Regarding the engine, again. Did this affect a l l engines and secondly, at what point w i l l you know wtiether it has been solved? Mr. Petrone: It affected three of the five of the liquid oxygen feed ducts and one of the five of the liquid hydrogen. \fire w i l l not know we have solved it to proceed w i t h the mission ufitil 22 seconds before liftoff. Q~testion: F o r B i l l Schneider. B i l l , you said i t ' s possible a l l the pritnary mission objectives w i l l be acenmplishcd by insertion into otbit. What has to be accomplished by ii~sertioninto orbit to meet a l l of your primary objectives? M r . Schneider: Well, let me hasten to add thzt a l l of the primary objectives, as listed i n your press kit, do include an S-IV-43 restart and we w i l l be mightily disappointed and w i l l not consider the rilissiorl a complete success i f we do n ~ yct t that. What 1 am saying i s that, i f for some reason or ckher we do not get a restart, we may arid D hasten to say "may", we may have sufficient information to make a ptaper decision on whether or not th? Saiirun V i s ready for man rating. We w i i l not know that until long after- ihe f l i yht , because that would be as 2 result of catefli2 analysis of t f ~ data. ~: Question: I'd like to go back to the hzating problerri, just for a moment. 1"Y'hen the.. .This pvoblt.ri1 occurs, as I LII-iderstand i t , as thc cryogenics are being pumped into the tanks? . �Mr. Petrone: No. The problem actually is seen when we go into automatic sequence at three minutes and, I believe, seven seconds. We started pressurization activity. The cryogenics heat up under the pressures. These are the flight pressures that we're building up. Now what we have to do i s read, and we do this on every flight, we read the temperature at the inlet.to the engine. We establish a band width. Vie call it a redline and wd say we must be within. that band width or below that redline in order to function properly, and on the S-ll you're reading a value on the ground and actually the engine isn't going to ignite until some two and a half minutes, so what you're doing i s extrapolating a ground condition into what it will be two and a half minutes later, but you see your temperature rise, in your automatic sequence. It's the or11y time we can see it.. That's the reason Dr. Rudolph mentioned we've got to go through our terminal sequence. We'l l be reading these values and our tinies are down to minus.22 seconds. If we are within the redline, we would then proceed. I f we're not, we plan to cut off. Question: A t the time the fuel i s injected into the engine, i n which state is it? is it liquid and then it gasifies in the engine? Mr. Petrone: You gc through the injector as a liquid with your liquid oxygen. The difficulty comes at your pump i f you start to cavitate .or build up an air bubble there. The pump w i l l not work efficiently and therefore your mixing ratios are entirefy different than what you've planfied and you can get any mixi~igratio, which can lead, of 'course, to many consequences, whether it would go in the engine properly, or whether you would get too much fuel ancl not enough oxygen, but basically, what you do, is you're upsetting your ratio of fuel to oxidizer going into the engine. Dr. Rudolph: And you want to start fircl rich, not oxygen rich. Both are liquid. Question: For George Low. George, what's the status of the spacecraft for the 503 mission? Where is it and how soon can you bring it out to the VAB to stack it, assuming that the flight tomorrow i s a success? . hlr Low: Are you tal king about a spacecraft for an unmanned or a manned flight? Wel I, George, that would be comrnand modulc 103, whic11 i s about to go into clieckont i r l Dowt~eyanrl LM-3 which has bcer~in ctleckout at Bztilpagc f3r S O ~ ! Itirria. C~ tdeitl~evoite of tliese vehicles arz schsduled for dslivery t~eveuntil surnrr;crtin;e. �Question: I'm a little confused, then, on the basis of Howard Benedict's question and then the answer to this last one,, what i s the sweat about moving the next Saturn V out to the pad i f you don't have the command module and the lunar module for the manned flight here? Answer: Well, because of some of.thz interactions i n getting some of our work done out on our remote sites, some of the programs that must be put in. We have a situation where our missions are pressing one on the other. . . Answer: I believe we've got a boilerplate on 503 now, and i f tihe decision was made to f l y unmanned, and what we have planned and brought up to this point, we have on board a boilerplate spacecraft with a l l the weights and the simulations i n there and that's what v~ould fly. Question: And you'd want to gct that out i n a hurry i n order to make way f o i 504, which would then be ycur first manned flight? But.. Answer: That's our planning as o f today. We've broughl the 5 03 to tlie point of checkout, where it's near rollout within these ten days that Howard mention~d. Now v ~ e ' l llook at tlie results of 5 0 2 . before we make further decisioiis. We have brought it to the point where the boilerplate that would f l y for the eventuality that we have to launch it, we would not wait on another delivery of a spacecraft. I believe that was the question that was raised. Question: I n other words, i f you decided that you were going to have another.. i f you decided that your next flight was going to be the manned one, then you would not be in a hurry to get the Saturn V out of the ..... VAB? Answer: That's correct. Question: Two more brief qirestions on the temperature problem. Ro'cco, I'm s t i l l not sure whether one of tlie J-2 ellgines or two of then1 were not affected i n any way by this problem, and secondly, do you have any indication of villy they were not affected and the others were? Mr. 'Petrone: It turns out that the t h r w that were affected by l i q ~ i i doxygen,and two were not. The otie that was affected by liquid h'yduo5cn was, not affected by liquid oxygen. So vie !lad the cr?nter engine that VJC ran fickter on tile liquid hycluogzn that did not, t f ~ was t within . �the redline, on the liquid oxygen. So what you have i s a case of three engines where they're out of spec. on liquid oxygen and one engine out of spec. on liquid hydrogen, not the same engines. Question: Can you explain in anyway why the first engine did not have this problem on either side? Mr. Petrbnz: No Dr. Rudolph: No, the fifth engine had the problem on the hydrogen side, the center engine, the hydrogen side, and it has a longer feed duct. You see, the feed duct comcs down the side of the stage and then goes to the engines, and they are not all down on one side, but are distributed. Now theti, the lines are equally long for the four outer engines, but the center engine, being farther away, needs a longer f ~ e dline, so it i s therefore more sensitive to any temperature changes which might occur in that stretch of the line t o the center engine. Mr. Petrone: It's a frrtiction of geometry and heat distribution, as Dr. Rudolph mentioned. The flow in that interstage, the only time you see it is here at the launch site. The only time you have a first stage to sit on topof and therefore the fuel conditioi~syoit get. We have electror~lcsin there and actually v:t? nitlst pump warrn air in there. Now you get a series of factors so that you end up with a result: and therz's going to be same movemet;t of values, the inlet temperatures, and literally, one can only experiment with it here to see what the end result i s going to be. It cannot be done on a test site. Mr. Klng: We had two patient hands i n the front row and there's a third hand up now. Vde'll take these two questions 11t;vrt ,then we'll go to Houston for questions, therl we'il ccltrle back here far anybody who has questions. Go ahead. Question: Another question on this heat probier;!. If you go to F mint!s 22 seconds and havc to hold, w i i l that be a prolonged hof d or.. Mu. Petronz: We wiff not hold at T minus 22. At I"r n i n ~ ~22 s secofids, anybyhere after three minutes seven seconds, we w i l l revert back, we'i t go back to T minus 24 minutes. .*.. .... �Question: Is there some quick fix or do you have something in'mind that you can make a change .to get the temperature down again? Mr. Petrone:. By observing the particular trace of the temperature, we'll be watching the temperature on. the recorder and have it plotted. There are adjustments, such as inlet, temperatures of that interstage. That i s one adjustment we can make ., Dr. Rudolph: We also expect that we had during the CDDT, that on the second round as we call it, the situation had improved. It did. on the first attempt, or rather on the second attempt, during the CDDT, improve, Only one LOX side was out of the specs. or the .redline. Que.stion: I believe this i s for Dr. Rudolph. A t an earlier briefing, Bob Moser told us that i f vie go manned on 503., the S-11 stage w i l l go back. to Michoud for man rating and certain modifications. 1-le specifically nlentioned possible relocation or strenthening of the baffles, the LOX baffles which hzve given some troubleon 5 0 1 . Could you pinpoint this and explain a little b i t about it. Dr. Rudolph: Yes, you talk two different i s s ~ e sat the same time, so that we talk fir'st about a one where you mention the second stage, th3 S-11 would go back to the test site. That's correct. We would indicate that 503 would be manned, take the second stage, ship it'back to the Mississippi Test Facility znd make a cryogenic proof test, so that answers one question, I believe. The other one .is that during the 5 0 1 LOX loading in the .S-I!, we had damage of baffles and i n order to save time during the countdown and avoid crew fatigue we want to go to a fast f i l l on 503 manned. Now since we had this problem with the. baffle damage of 501, we have to do something to the baffles. Strengthen them for instance. Question: What? Specifically, how? Dr. Rudolph: Well, we, for instance, changed the baffles, which are shaped like a rhomboid and s i t down at the bottom of the LOX sun,p. We took the lower half off, so i n a way, LV.,~ took them out of ti12 stream of the incoming liquid oxygen. That helps, but we also have to stirdy the flow dynamics inside. It isn't all that simple. As I say it here, and again, you can only find that out by testing, not by anaf.ysis, by sitting down at your desk ancl trying in your mind to figure o.ut what the f ~ r c e sare. 'Any~lay,tvt? tilink we, by also niaking certain changes to the facility, Kocccr, understand the probler~i well eno:!gh that on 503, manned, we c2n fast load zgaln. �Mr. King: Thank you. We'll now switch to Houston. I understand both M r . Kraft and M r . Chaviescvorth have a statement. \lo ice : T h i s i s I-lauston. We have one logistical announcement to make f i r s t . The Houston News Center w i l l be open until ten p .me, Central time, this evening and reopen at fowr a.m., Central time, tomorrow morning. Next w e ' l l hear from M r . Kraft and M r . Charlesworth. �Mr. Kraft: I ivot~ldlike to point out that this is another ~~nmanned flight of a manned vehicle and therefore another complex job for the flight control and ground crew to accomplistl. There are a large number of things that we can and may have to do and it may be a difficult m i s s i o ~from l that p o i ~ of t view. The other point I would like to make i s that we have been making a large number of modifications to the whole network over the last two years and this flight i n itself i s sort of a dress rehearsal for our upcoming .first manned flight of the 101 Spacecraft. We have made a lot of changes, we've added a lot of equipment and we feel now that this flight w i l l he proof that all of that equipment i s ready to support our manned space flight program. About all 1 would like to add that we have completed our tralning to date with what I thirlk is good results a i d i t seems prepared to do whatever i s required to he done. I n terns of the facilities, our ground support facilities, computers, network, etc. ,are proceeding along normally with our part of the count to meet the pad's. We have no problems at this time, and based on past testing support and the CDDT we don't really expect any and we expect to be ready to Meet the pad launch in the morning and have a good flight. Okay, we are open now here in klouston for questiorrs, Assuming a lar~nchtomorrow morning, has anyone recalculated the apogee and perigee of the S-IVB, and how mzny degrees it wifi' miss the moon, and whether it wil! come hack to earth ? Mr. Kraft: Mr. Chaulesworth has. l t v e got a few nirrnbeus, 1 knew someone would ask. Assuming we launch on time, the best ififormation I have i s to expect the apogee of the S-IVS to be some 279 thousand 13autica.l miles. With a perigee, that i s wker; it comes back to the earth, of around 1700 m i l e s , with a period of some 16 clays. Now we don't expect it tc enter essentially the area of the moon's sphere of infiuence, i f we go on time. Nov~, i f you try to pin me down v1itl.1 launch delays or different days I can't t~onestfyanswer it becairse it i s a variable depending .on the time of the day you launch, location , day of the month, eir:. Question: What about i n reentering the atmosphere? LViII i t corrle back and dn that under ihe present plans. Mr. Kraft: The first time out i t d;oesnlt look like it will ,but the next time around i f we get into the spherz of the ~ O D ~ I ' Sit-rfiuence becatlse of the trajectory, i t could, It's probably a good probability that it w i l i come in. Any further questions Fiom I-louston here ? �Mr. King: Thank you. We'll continue the questions here as has been the practice and is the practice once again. Mr. Schneider passed oil a note t o me to remind me that he does have an airplane to catch. We w i l l continue this for a short while. Question: If we had t o put a dollar value on that beast out there from the top of the L E S down to the base of the model what would that figure be? Mr. Lodge:. We don't judge our program that way. It's kind of meaning!ess There are so, many things that you don't see that you pay for that there is no real way of coming up with what the dollar value i s of that. The do1lar value i s immense when you con sider the value to the United States. The value to the United States is incalculable. What it costs, I don't have any way of figurir~gout. Question: Rocco, how many times is it feasible to recycle back t o 24 minutes, Would you do it just one time or.. Mr. Petrorie: No. We have a multiple opportunity. We are looking for a rnaximum .of four.. That is going to depend upon many things. As far as gaseous hydrogen that we use to charge our bottles for the J-2 engine, we feel vde have 4 recycles that the time duration goes back t o T -24 does not mean'we w i l l go back and pick up and then yo in again. You have to loolc at data, look at the va,lues, lool<'at the occurenccs, the trends, temperatures and all, and wait for certain things to stabilize and then go i n again.. Right now we are hoping we have worked these values so that the First time tfirough, of course, is our best'gilkss. We will, based on what we see ar~dwhat we know happened Sunday be able to plot two points on the curve and make another extrapolation forward at the second attempt. Question: I am sure this w i l l be an easy one. How much damage from a monetary standpoint did this first Saturn V cost to the piid and how long did it take to fix it, and have you taken any steps to perhaps I~aveless damage this ti'me? Mr. Petrone: Yes. We have taken steps to hatie !ess damage. The items of the pad and launcher are sornewhai. sepamie. The launcher g2ts a l i t t l e more damage than the pad itself. \rVe would anticipate tl.~at,say for an average launch and what we found in 501, that we could have the pad in shape within 10 days to receive another launcher. The launcher itself is going to take longer in the neighborhood of thrcc weeks, and maybe Four. The monetary value we have not - - . . - ' - �collected as part of our refurbishment and maintenance, if you go into maintenafice items and refurbishment. However I must say that I was most pleased with the very limited damage on the 501 and I only hope it i s an indication of what we wil I continue to see i n the future. It was very, very minor in the larger picture. Question: Well, from a money standpoint, can you give us the ballpark. Was it under one hundred m i l lion? - It was more than $10. Somewhere along there must be faily close. Answeu: That's a pretty big broad spectrum you put out. Why don't we just use that? Question: You must be able to do better than that. No - let's say yes. It's between those two numbers. Question: Aviation Week i n the current issue says that if tomoru~w'sflight goes v~ell, there i s a good chance that tbe manned flight to the moon could go in the first half of 1969. Would you comment please? Mr. Low: There can be a lot of problems t o take yet between tomorrow's flight and the first fiight t:, the moon. Vde /lave to get manned flight i n Apallo in earth orbit and we have to do a number of earth orbital rendezvous flights on the Sziurn V, and then with the LM and the CSNI, f think it w i l l be a most difficuit'job to get the lunar landing by the end of 1969. 1 think we've got a very good chance of doing that. Question: Isense a certain ~'eiuctai~cc to talk about money. However, I have to press this question a little b i t to Mr. Schneider. In testimony before the sub-committee last fdair'ch 16, 1967, I believe it was, von Braun put a price tag, a fairly precise one of $205 million for a laut~chedSaturn V. Peopie at NASA tell me that that figure i s still kind of hanging and that's alright. Nr~wif von Braun can be as precise in 1967 when zsked by Congress about the price of a vehicle, why can't we be equally precise in 3-968 when aslced by the puess. I don't agree that this is just an editorial comment is pqssing it i s kind of meaningless to talk about the price of anything. Mr. Schneider: I am ;he mission clirectou - not the Senate director. As mission director I couldn't 'even tell rot! what u!lu bt~dgctis. I am not in that business. That's why i cannot answer that qtiestiot~. - �Question: Wel I , can anyone ? Answer: Nobody here at the table has the answer for you and we w i l l do our best to get it for you. We'll check. Question: For B i l l Schneider. Bill, just so I fairly accurately understand this point. If yoLi don't get a second stage burn of the S-IVB,have you met your primary mission objective? Can you man rate for 503 and start manned flights with 503? Mr. Schneider: The answer to the first one is no. We would not have met the primary mission objectives as stated in the document because they do include anS-IVB restart. The answer to the second question is it is perfectly coi~ceivablethat after analysis of the data we could 'find that the reason for restart failure had no implications on whether or not the vehicle was man-ratable. The first planned Saturn V mission does not currently include the manned restart of the S-IVB. - Question: For George Low. Why is the new hatch being flown aboard this spacecraft other than the fact i t was ready. Mr. Lovr: I guess you have almost answered your own question, Joe. We did at the time we made the decision on the nevi hatch know that we could not get it oil Spacecraft 017. LVe knew we c o ~ ~get l d it on Spacecraft 0 2 0 so we nloved it outand pit it on 0 20 t o get the best possible test of the hatch at the speeds, heat transfer rates, etc., but we have completed some very satisfactory ground tests. We have more to go and also we have seen the very low heating rate i n that area on Spacecraft 017 so that since that decision was made we have convinced ourselves that we don't need a flight test of this hatch for man rating pi.!rposes, Question: I have two short questions. The first one is what is the official lifting capacity of the Saturn V. Dr. Rudolph: Question: 2 0 0 , 0 0 0 pounds? Then this is an increase of 10,000 pounds i n about the last three or f o i i ~years is i t ? Dr. Rudolph: No. For the last 2 years, i f my nlernory serves pounds. rile right., 98,000 �Question: Second question. The S-IVB trajectory, and I siippose this might go to Mr. Charlesworth in Houston. I believe this is one of the few and possibly the only circ~imlunartrajectory that we have flown. Possibly there has been one, or maybe a scientific experiment has flown this way. As I understand it, this is an orbit that goes around both the Earth and the Moon - is it not - am I wrong about that? I see Mr. Schneider shaking his head. Weii, I can just add this. Is this the kind of trajectory that one would f l y i f one were flying men around the moon? Answer: In terms of energy imparted to the trajectory, yes. In terms of the actual taigeting , no. LVe are essentially shooting for a fictitioirs moon, so to,speal<. lye do not expect tcmorrovi for this trajectory to go around both the Earth and the Moon. We do not expect it to enter into the sphere of influence of the PJoon. Question: I'm a i i t t l e b i t confused about this S-IVB. We were told by Mr. Charleswouth that we had a 279,000 nautical mile apogee and a 1,700 nautical mile perigee. That is frain the Moon, is that right, or frorn the Earth? You just told Diet< Le\.vis it did not go aroilt?d both of them. W i l l somebody please maybe use a blackhoard and tell us what it is going to do. Mr. Charlesworth: i t goes out t o lunar distances, but it does not go around the Moon itself. Mr. Schneider: It is a high!y elliptical orbit that at its closest point ccmes within I! ,700 rriiles of the Eatth and at its furthest ciistance goes t o 279,060 miles f(om the Earth. Quest 'Ion: Wl~atis the lifetime? Answer: The period i s 26 days. Mr. Charlesworth: The period for this orbit, this I?igltly elliptical orbit, i s 16 days. When i t comes bzck through 2nd starts up, depending on where the Moon is, we will prciiabfy get some pertirrbatioix, it is difficult to predict-- 1 can't predict--wf~at ~ j i fl i,appen on the next pzss. It niay very li!ceiy rc"c1r.n is Earih. Let me p ~ i n out t that fcr the f i g ~ ~ r eused s fcr the S--IVB that i f you a:c o f f only a few feet per second or several ierlths af a cie<jr.cc it is going to have a Irernzncloils effect on the apctgee and perigee relative to the Earth. So yo\i shouldn't take t i i ~ f i nt l l i i i ~ k ? ! ' ~2 s gospel. �Question: i just want t o reiterate this point since it was raised again. As I understood, the ascent part, the orbit of the S-IVB would go around the Moon and then on its return would go around the Earth and then go back up to the Moon. Answer: Why don't t draw you a picture after we're done here. Question: One more time on the J-2's. Bid you detect this problem i n the CDDT? And also in some way you detected it today. I'm confused on that. Answer: Just on the C D D I ; Sort of been living with it ever since. Dr. Rudolph: Yes. Discussing it, analyzing it, looking at what shifts we should make. But in order to detect it, you have to have cryogenic support and go through your terminal sequence. Question: The fuel flow has to stail before you detect i t ? Dr. Rudolph: You don't have to start fuel flow. No, you've got static conditions of the fuel i n the pump. You've got a valve downstream of that pump. When you are measuring your temgeuature and pressure, geometry-wise just above the entrance to the engine itself. You do not measure the flow. We get the flow at ignitior~on the first stage. On the second stage there would not be flow until you start, actualiy 2-1/2 minutes into the mission. - Question: Mr. Schneider, if for some reason you are unable to mail rate this vehicle tomorrow, how firm are your plans to go t o a dua! laurrch concept using the Saturn IB after the 205 flight? Mr. Schneider: We have that i n our plans and we w i l l retain it in our plans. However, i f we do not have a satisfactcry Flight on t.l~isone, the 502 flight, our current plans are to go out with 503 boiler plates. Mow i f we do that. and that is a successful flight then it is conceiveable that we would go to the Saturn V matlned launch on the 504 and not clo a dual launch, but we w i l l retain that capability until some later date. Question: Jack., any pilots i n training and i f so how maily and w i l l they be watching it tomorrow. , Mr. King: We are supposed to be getting a list, George, of which astronauts w i l l be here for the launch. 1111 check on that as soon as this i s over and wllatevcr information we have we w i l l be glad to pass i t on. 1 certainly expect ve; wilt habe it by tonio;:roa rnorillng. �Question: i would like to ask one question. What are the reasons, a l l the reasons for the S-IVB shooting for this fictitious moon target? Dr. Rudolph: You would exeiScisethe antennas on the stage and find out whether you can communicate. That is, whether you can receive signals or can send signals up and have them bounce back, There i s certainly one very significant advantage and y.ou would also find out whether you achieved your velocities you are looking for. I would like to add something so that there is no misconception. The S-IVB has a guaranteed l i f e of about six hours, but we hope that w i l l go on ,to about 1 0 or I 1 hours. As you hcard earlier, this has a 15-day period, so we would only be able to get actual signals back from the S-lVB for those first 1 0 hours - not out at lunar distances. Question: I woilld like to pursue Mr. Lewis' questiori further. You said that the Saturn V is now rated to lift 1 0 0 , 0 0 0 pounds. The present weight, the payload for tornorrow, comes to just under 94,000 pounds, according to the press information. However, this is only a 6 , 0 0 0 pound lunar test a r t i ~ l e . The real load, as I understand it, w i l l be about 3 2 , 0 0 0 , maybe Inore, If we add this 6 , 0 0 0 we w i l l just barely make it w i t h 1 0 0 , 0 0 0 pounds of payload in a vehicle capable of l i f t i n g 9 0 0 , 0 0 0 pounds. Very marginal. Maybe Mr. LOW would l i k e to answer. Mr. Low: True. We do have a weiglit problem in Apollo. Comrnand Service modules and the lunar moduie are esscniialfy at the limit of w c i g i ~ t that we can fly. Vlle have the s i l ~ ~ a t i under o i ~ control, the cornmand/service modules ren~ainec!steady ellough though a t t h e i r current weight for the last 4 or 5 m o t 2 t i ~ . I am talking about the comrnand/scrvice module from the Block 2 vellicle that w i l l be on the lur;ar rrrissioii. P,nd we s t i l l hzve som? margirl left. Thc situation on the lunar module is sotneavhat tighter since we made the post-accident changes s o ~ ~ ~ e wlater h a l and we did riot get tila weights on the control as q ~ i i c k l y , b u t they loo are leveling off now aud with very tight weight coi~ivoiand sorrle possible weight recfuction I am confident we are going to niako it, but v,e esscrltialiy arc at the lirnit. Mr. King: I am afraid we are going to have to terinlnatc the conference now. Thai~!<yorl very inuch. � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000074 Title A name given to the resource "Apollo 6 Pre-Launch Press Conference." Description An account of the resource The press conference was given at Cape Royal News Center in Cocoa Beach, Florida, on Wednesday, April 3, 1968, at 3:30 PM. Participants: William C. Schneider, Apollo Mission Director, NASA; George M. Low, Apollo Spacecraft Manager, NASA; Clifford Charlesworth, Apollo 6 Flight Director, Manned Spacecraft Center, NASA; Dr. Arthur Rudolph, Saturn V Program Office, Marshall Space Flight Center, NASA; Rocco A. Petrone, Apollo 6 Launch Director, Kennedy Space Center, NASA; Col. Royce Olson, USAF, Director DOD Manned Spaceflight Support Office, Patrick AFB; Chris Kraft, Director of Flight Operations, Manned Spacecraft Center. Creator An entity primarily responsible for making the resource United States. National Aeronautics and Space Administration Date A point or period of time associated with an event in the lifecycle of the resource 1968-04-03 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Apollo 6 flight Apollo spacecraft John F. Kennedy Space Center Project Apollo (U.S.) Saturn launch vehicles Saturn Project (U.S.) Type The nature or genre of the resource Press releases Text Source A related resource from which the described resource is derived Saturn V Collection Box 26, Folder 19 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000051_000074 https://digitalprojects.uah.edu/files/original/20/1453/spc_stnv_000005_01.mp3 d2e527e05bdcc5b076bdf11d50eb3b0f https://digitalprojects.uah.edu/files/original/20/1453/spc_stnv_000005_02.mp3 c1fe25de46d7b4732ac8d15c34188d27 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Oral History A resource containing historical information obtained in interviews with persons having firsthand knowledge. Duration Length of time involved (seconds, minutes, hours, days, class periods, etc.) 1:29:06 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000005_01 spc_stnv_000005_02 MC_2_001 Title A name given to the resource Interviews with Wernher von Braun conducted by Dr. Emme and T. Ray. Description An account of the resource Interview with Dr. von Braun by Dr. Emme. Beginning of side 1 to 19:50. Interview of Dr. von Braun by T. Ray. Side 1 19:50 thru end of side 2. Creator An entity primarily responsible for making the resource United States. National Aeronautics and Space Administration University of Alabama in Huntsville Date A point or period of time associated with an event in the lifecycle of the resource 1970-08 Temporal Coverage Temporal characteristics of the resource. 1970-1979 Subject The topic of the resource Von Braun, Wernher, 1912-1977 United States. National Advisory Committee for Aeronautics United States. National Aeronautics and Space Administration German Americans Canaveral, Cape (Fla. : Cape) Format The file format, physical medium, or dimensions of the resource Open reel audiotapes Type The nature or genre of the resource Interviews Audio Source A related resource from which the described resource is derived Saturn V Collection University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource clir_grant_audio_metadata https://digitalprojects.uah.edu/files/original/20/1466/spc_stnv_000006_01.mp3 d7935a85a9f2271b3888053c14ab10b7 https://digitalprojects.uah.edu/files/original/20/1466/spc_stnv_000006_02.mp3 9eb3ba99a56f4370f61af114f7cd778a Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Oral History A resource containing historical information obtained in interviews with persons having firsthand knowledge. Duration Length of time involved (seconds, minutes, hours, days, class periods, etc.) 1:00:57 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000006_01 spc_stnv_000006_02 MC_2_002 Title A name given to the resource Interview with Dieter Grau. Description An account of the resource Dieter Grau interviewed on failure analysis and management of Saturn program. Both sides of tape. Creator An entity primarily responsible for making the resource United States. National Aeronautics and Space Administration University of Alabama in Huntsville Subject The topic of the resource United States. National Aeronautics and Space Administration German Americans Project Apollo (U.S.) George C. Marshall Space Flight Center Format The file format, physical medium, or dimensions of the resource Audiocassettes Type The nature or genre of the resource Interviews Audio Source A related resource from which the described resource is derived Saturn V Collection University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource clir_grant_audio_metadata Oral History https://digitalprojects.uah.edu/files/original/20/1467/spc_stnv_000007_01.mp3 e741df60c652b72b552375ce2813e43b https://digitalprojects.uah.edu/files/original/20/1467/spc_stnv_000007_02.mp3 b8a2834a2cdf36b57f548884cd7f75ce Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Oral History A resource containing historical information obtained in interviews with persons having firsthand knowledge. Duration Length of time involved (seconds, minutes, hours, days, class periods, etc.) 1:03:07 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000007_01 spc_stnv_000007_02 MC_2_003 Title A name given to the resource Interviews with Shields and Davenport (Rocketdyne?). Description An account of the resource Interview with Davenport (0-23:44 S1) and Shields (23:44 S1 - end S2). Topics covered include the reliability of the F1 engine, Skylab, and electronic manufacturing. Creator An entity primarily responsible for making the resource United States. National Aeronautics and Space Administration University of Alabama in Huntsville Subject The topic of the resource United States. National Aeronautics and Space Administration Project Apollo (U.S.) George C. Marshall Space Flight Center Format The file format, physical medium, or dimensions of the resource Audiocassettes Type The nature or genre of the resource Interviews Audio Source A related resource from which the described resource is derived Saturn V Collection University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource clir_grant_audio_metadata Oral History https://digitalprojects.uah.edu/files/original/20/1468/spc_stnv_000008_01.mp3 3e3a8b4ec34667c0511020dc822a2caa https://digitalprojects.uah.edu/files/original/20/1468/spc_stnv_000008_02.mp3 1e5abc650ab554d9d8bc6fa0a505285c Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Oral History A resource containing historical information obtained in interviews with persons having firsthand knowledge. Duration Length of time involved (seconds, minutes, hours, days, class periods, etc.) 0:58:24 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000008_01 spc_stnv_000008_02 MC_2_004 Title A name given to the resource Interviews with Sawyer and Kudebeh (Rocketdyne?). Description An account of the resource Interviews with Sawyer (0 - 16:58 S1) and Kudebeh (16:58 S1 - end S2) on weight penalties, schedule/performance bonuses, and project management. Creator An entity primarily responsible for making the resource United States. National Aeronautics and Space Administration University of Alabama in Huntsville Subject The topic of the resource United States. National Aeronautics and Space Administration Project Apollo (U.S.) Skylab Program George C. Marshall Space Flight Center Format The file format, physical medium, or dimensions of the resource Audiocassettes Type The nature or genre of the resource Interviews Audio Source A related resource from which the described resource is derived Saturn V Collection University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource clir_grant_audio_metadata Oral History https://digitalprojects.uah.edu/files/original/20/1469/spc_stnv_000009_01.mp3 a6af54b9e66df9aa8bd44733ac5ba136 https://digitalprojects.uah.edu/files/original/20/1469/spc_stnv_000009_02.mp3 f87ceb767ac88b2833b7c77c929f2f8f Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Oral History A resource containing historical information obtained in interviews with persons having firsthand knowledge. Duration Length of time involved (seconds, minutes, hours, days, class periods, etc.) 0:29:51 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000009_01 spc_stnv_000009_02 MC_2_005 Title A name given to the resource Interviews with Weidner and Neubert. Description An account of the resource Side 1 is an interview with Weidner and Neubert on the testing of Saturn and the different design philosophies of various NASA groups. Side 2 is an interview with Dave Aiken and John Beltz on Saturn development and the different philosophies of NASA groups. Creator An entity primarily responsible for making the resource United States. National Aeronautics and Space Administration University of Alabama in Huntsville Subject The topic of the resource United States. National Aeronautics and Space Administration Project Apollo (U.S.) German Americans Canaveral, Cape (Fla. : Cape) George C. Marshall Space Flight Center Format The file format, physical medium, or dimensions of the resource Audiocassettes Type The nature or genre of the resource Interviews Audio Source A related resource from which the described resource is derived Saturn V Collection University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource clir_grant_audio_metadata Oral History https://digitalprojects.uah.edu/files/original/20/1470/spc_stnv_000010_01.mp3 563d4df4c1f5d1d895da1e37c5f7d3e3 https://digitalprojects.uah.edu/files/original/20/1470/spc_stnv_000010_02.mp3 681e3d83794d10345349a878ec380bb1 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Oral History A resource containing historical information obtained in interviews with persons having firsthand knowledge. Duration Length of time involved (seconds, minutes, hours, days, class periods, etc.) 1:02:15 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000010_01 spc_stnv_000010_02 MC_2_006 Title A name given to the resource Interview with Bauer. Description An account of the resource Interview on the developments on Thor applied to the Saturn Program, structures, Welding, Machining of Part, and Insulation of the rocket. Both sides of tape. Creator An entity primarily responsible for making the resource United States. National Aeronautics and Space Administration University of Alabama in Huntsville Subject The topic of the resource United States. National Aeronautics and Space Administration Project Apollo (U.S.) Canaveral, Cape (Fla. : Cape) George C. Marshall Space Flight Center Format The file format, physical medium, or dimensions of the resource Audiocassettes Type The nature or genre of the resource Interviews Audio Source A related resource from which the described resource is derived Saturn V Collection University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource clir_grant_audio_metadata Oral History https://digitalprojects.uah.edu/files/original/20/1471/spc_stnv_000011_01.mp3 a95762589f1adab3d774ae1b1826dfe2 https://digitalprojects.uah.edu/files/original/20/1471/spc_stnv_000011_02.mp3 d8a9b13022cbb02b7ee9894ea2a4d4bb Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Oral History A resource containing historical information obtained in interviews with persons having firsthand knowledge. Duration Length of time involved (seconds, minutes, hours, days, class periods, etc.) 0:47:42 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000011_01 spc_stnv_000011_02 MC_2_007 Title A name given to the resource Interview with Ed Mims. Description An account of the resource Interview on the fuels involved in the Saturn as well as the transport and management of these fuels. Both sides of tape. Creator An entity primarily responsible for making the resource United States. National Aeronautics and Space Administration University of Alabama in Huntsville Subject The topic of the resource United States. National Aeronautics and Space Administration Project Apollo (U.S.) Canaveral, Cape (Fla. : Cape) George C. Marshall Space Flight Center Format The file format, physical medium, or dimensions of the resource Audiocassettes Type The nature or genre of the resource Interviews Audio Source A related resource from which the described resource is derived Saturn V Collection University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource clir_grant_audio_metadata Oral History https://digitalprojects.uah.edu/files/original/20/1472/spc_stnv_000012_01.mp3 2101fdbff1282cb6c926ee775633c004 https://digitalprojects.uah.edu/files/original/20/1472/spc_stnv_000012_02.mp3 5e9ba765ca4c0340b57a92ef45da0f4c Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Oral History A resource containing historical information obtained in interviews with persons having firsthand knowledge. Duration Length of time involved (seconds, minutes, hours, days, class periods, etc.) 0:56:20 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000012_01 spc_stnv_000012_02 MC_2_008 Title A name given to the resource Interview with Schwartz (chief engineer?). Description An account of the resource Interview on the development of Saturn engine design and control, as well as life at the Mississippi engine test site. Both sides of the tape. Creator An entity primarily responsible for making the resource United States. National Aeronautics and Space Administration University of Alabama in Huntsville Subject The topic of the resource United States. National Aeronautics and Space Administration Project Apollo (U.S.) George C. Marshall Space Flight Center Format The file format, physical medium, or dimensions of the resource Audiocassettes Type The nature or genre of the resource Interviews Audio Source A related resource from which the described resource is derived Saturn V Collection University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource clir_grant_audio_metadata Oral History https://digitalprojects.uah.edu/files/original/20/1473/spc_stnv_000013_01.mp3 77c70fe3a767b4eab34b151ec3795120 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Oral History A resource containing historical information obtained in interviews with persons having firsthand knowledge. Duration Length of time involved (seconds, minutes, hours, days, class periods, etc.) 0:25:01 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000013_01 spc_stnv_000013_02 MC_2_009 Title A name given to the resource Interview with Newell. Description An account of the resource Interview on the Development of Saturn and the general design and management philospohy of NASA. One side of tape only. Creator An entity primarily responsible for making the resource United States. National Aeronautics and Space Administration University of Alabama in Huntsville Subject The topic of the resource United States. National Aeronautics and Space Administration Project Apollo (U.S.) George C. Marshall Space Flight Center Format The file format, physical medium, or dimensions of the resource Audiocassettes Type The nature or genre of the resource Interviews Audio Source A related resource from which the described resource is derived Saturn V Collection University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource clir_grant_audio_metadata Oral History