10 20 8242 https://digitalprojects.uah.edu/files/original/20/2305/spc_stnv_000077.pdf d4d3d32be8310c51bd73e2ff97183ab6 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 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 <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <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. 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. 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. 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_000077 Title A name given to the resource "Apollo Documentation Administration Instruction." Alternative Title An alternative name for the resource. The distinction between titles and alternative titles is application-specific. X67-81658 TM X-59409 Description An account of the resource According to the foreword found on page i, this document includes instructions on "procedures, methods and practices...necessary for the effective management of a program documentation system." Creator An entity primarily responsible for making the resource National Aeronautics and Space Administration Date A point or period of time associated with an event in the lifecycle of the resource 1964-08-01 Subject The topic of the resource Project Apollo (U.S.) Project management Saturn Project (U.S.) United States. Apollo Program Office--Management 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 spc_stnv_000075_000118 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Type The nature or genre of the resource Documents Text https://digitalprojects.uah.edu/files/original/20/2335/spc_stnv_000107.pdf 50483bf8f7b7d36fad698700ae78f4fb 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 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 <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <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. 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. 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. 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_000107 Title A name given to the resource "Apollo Logistic Support Systems." Description An account of the resource According to an abstract found on the page following the title page, this paper includes "one possible conceptual definition of an early Apollo Logistics Support Systems (ALSS) is presented and various payloads for the system are briefly discussed. " It also discusses the Lunar Mobile Laboratory (MOLAB) and other considerations for a lunar scientific mission. Creator An entity primarily responsible for making the resource Schaefer, Herbert, 1911-1999 Yarbrough, Leonard Date A point or period of time associated with an event in the lifecycle of the resource 1964-05 Subject The topic of the resource Lunar roving vehicles Lunar surface vehicles Project Apollo (U.S.) Saturn Project (U.S.) Source A related resource from which the described resource is derived Saturn V Collection Box 11, Folder 23 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_000075_000118 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. <a href="%E2%80%9Dhttp%3A//libarchstor.uah.edu:8081/repositories/2/archival_objects/16944%E2%80%9D">View this item in ArchivesSpace</a> Temporal Coverage Temporal characteristics of the resource. 1960-1969 Type The nature or genre of the resource Reports Still image Text https://digitalprojects.uah.edu/files/original/20/2314/spc_stnv_000086.pdf 6bfe13801d9be8751b327811821e78a5 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 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 <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <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. 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. 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. 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_000086 Title A name given to the resource "Apollo Logistics Support System (ALSS) Payloads Summary Report." Description An account of the resource This report includes a summary of the major tasks performed by the Apollo Logistics Support System Payloads with an emphasis on the Lunar Mobile Laboratory (MOLAB). Creator An entity primarily responsible for making the resource Boeing Company. Aero-Space Division. Date A point or period of time associated with an event in the lifecycle of the resource 1965-06 Subject The topic of the resource Lunar mobile laboratories Lunar surface vehicles Payloads Project Apollo (U.S.) Saturn Project (U.S.) Source A related resource from which the described resource is derived Saturn V Collection Box 14, Folder 5 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_000075_000118 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17152 Alternative Title An alternative name for the resource. The distinction between titles and alternative titles is application-specific. D2-83001-1 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Type The nature or genre of the resource Reports Still Image Text https://digitalprojects.uah.edu/files/original/20/2311/spc_stnv_000083.pdf 1555552d85d440effe03fb912861fa83 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 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 <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <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. 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. 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. 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_000083 Title A name given to the resource "Apollo Program Management Volume 3." Description An account of the resource According to the introduction found on page ii, this document was created to detail the "MSFC segment of the total Apollo Management process and to describe the methodologies and techniques currently being implemented." Creator An entity primarily responsible for making the resource George C. Marshall Space Flight Center. Date A point or period of time associated with an event in the lifecycle of the resource 1967-12-01 Subject The topic of the resource Project Apollo (U.S.) Project management Saturn Project (U.S.) Source A related resource from which the described resource is derived Saturn V Collection Box 24, Folder 12 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_000075_000118 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17775 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Type The nature or genre of the resource Documents Still Image Text https://digitalprojects.uah.edu/files/original/20/2319/spc_stnv_000091.pdf c4a535ae60895986978a98847bc6aec1 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 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 <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <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. 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. 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. 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_000091 Title A name given to the resource "Apollo Program: Glossary of Acronyms and Abbreviations." Creator An entity primarily responsible for making the resource Ertel, Ivan D. Date A point or period of time associated with an event in the lifecycle of the resource 1969-07-01 Source A related resource from which the described resource is derived Saturn V Collection Box 32, Folder 13 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_000075_000118 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. http://libarchstor.uah.edu:8081/repositories/2/archival_objects/18196 Description An account of the resource This glossary contains acronyms and abbreviations commonly found in documentation from the Apollo Program. This glossary is meant to be a tool for historians and other researchers. Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Aeronautics--United States Communication of technical information Information management Project Apollo (U.S.) Saturn Project (U.S.) Type The nature or genre of the resource Glossaries Text https://digitalprojects.uah.edu/files/original/20/2321/spc_stnv_000093.pdf 0c92e7467ee711450ea159b310ea3298 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 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 <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <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. 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. 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. 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_000093 Title A name given to the resource "Apollo Saturn LIEF Operations Plan." Description An account of the resource This paper identifies the support functions performed by MSFC through the Launch Information Exchange Facility (LIEF) during the Apollo Saturn Mission Operations and other facilities required to carry out these functions. It also identifies mission specific documents required for operation. Note that page 20 is missing. Creator An entity primarily responsible for making the resource Naumcheff, M. Date A point or period of time associated with an event in the lifecycle of the resource 1968-09 Subject The topic of the resource George C. Marshall Space Flight Center Launch Information Exchange Facility (LIEF) Project Apollo (U.S.) Project management Saturn Project (U.S.) Support systems Source A related resource from which the described resource is derived Saturn V Collection Box 27, Folder 53 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_000075_000118 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17940 Alternative Title An alternative name for the resource. The distinction between titles and alternative titles is application-specific. Report # I-MO-23-68 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Type The nature or genre of the resource Reports Still Image Text https://digitalprojects.uah.edu/files/original/20/10427/scan0009rev_080107115937.jpg a8dc91c7c2361c8f4d4c757e674d2723 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 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 <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <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. 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. 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. 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 scan0009rev_080107115937.jpg spc_stnv_000783 Title A name given to the resource "Apollo spacecraft Diagram." Description An account of the resource 8 x 10 inch black and white diagram of an Apollo spacecraft, each section labled for easy identification. Creator An entity primarily responsible for making the resource George C. Marshall Space Flight Center. Propulsion & Vehicle Engineering Laboratory.Metallurgical Analysis Section. Materials Division, Metallic Materials Branch Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Apollo project Apollo spacecraft Type The nature or genre of the resource Still Image Diagrams 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 Is Part Of A related resource in which the described resource is physically or logically included. Is referenced by: Materials in space exploration.; Is part of: Envelope - Photos Accompanied C. E. Cataldo paper "Materials in space exploration". 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_000775_000799 https://digitalprojects.uah.edu/files/original/20/2326/spc_stnv_000098.pdf 11429fa7166ae47eb73fb9c488840cfd 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 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 <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <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. 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. 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. 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_000098 Title A name given to the resource "Apollo Telescope Mount Fact Sheet." Creator An entity primarily responsible for making the resource George C. Marshall Space Flight Center. Public Affairs Office. Date A point or period of time associated with an event in the lifecycle of the resource 1968-03-01 Subject The topic of the resource Apollo telescope mount Manned orbital telescopes Orbiting solar observatories Project Apollo (U.S.) Source A related resource from which the described resource is derived Saturn V Collection Box 26, Folder 3 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_000075_000118 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17850 Description An account of the resource This fact sheet contains information related to the Apollo Telescope Mount, or ATM, which allows scientists to look at the activity of the sun through the fogging effects of the earth's atmosphere. Temporal Coverage Temporal characteristics of the resource. 1960-1969 Type The nature or genre of the resource Documents Still Image Text https://digitalprojects.uah.edu/files/original/200/14399/sdsp_skyl_000064_001.pdf 2c1987d169a5152b241ab7b61b46fa1c PDF Text Text 50M02416 SEPTEMBER 2 3 . APOLLO TELESCOPE MOUNT SEQUENTIAL FLOW PLAN PREPARED BY ASTR1 ON ICS LABORATORY ��r Hire FORM ui (VERTICAL) (AUSUST IHOl MOTICf — When Government drawing®, apoclf kotiona, or ether data ere weed for any parpeeo other then In connection with • definitely related Govsrs«a*l •roc«r*m«M oeeratlon. the United Statee Covarnmtni thereby Inovre no roe oonelbllltv noT obligation whatsoever: and the 'act thai the Government may have 'emulated. 'wrnlahed. or In any way supplied the aald drawings apoclflcatkno or other data la not to bo regarded by Im plication ar ©therwlee aa In any nannar licensing the hnldor or any otbor paraon or corporation, or oonvoylng any righto or pormiaelon to menufaetora. vao. or aoll any potantod Invention that may In any way bo related thereto. NEXT ASSY MF PART NO. APPLICATION REVISIONS 8YM USED ON [ DESCRIPTION | DATE | APPROVAL I > l EUGENE H . CAGLE E n g i n e e r i n g M a n a g e r f o r ATM R-ASTR-0IR UNLESS OTHERWISE SPECIFIED DIMENSIONS ARC IN INCHES TOLERANCES OHi rtACTIORt OICIRAL1 ORIGINAL DATE OF DRAWING 1 LLI'STR ATO" ANCLII . H.S .i-rrtnMu on CEORCE 9-23-68 CHICHI ATM CHECKCN TMCIR NATIONAL AERONAUTICS SEQUENTIAL MATERIAL AND SPACE ADMINISTRATION nO'M FLOW P L A N submitted HEAT TREATMENT v .. M • ( • Tsii'Vca FINAL PROTECTIVE FINISH C. MARSHALL SPACE FLICHT CENTER 2 -jC —Sa- ft) EV f.-T7 Dwa SCALE UNIT WT SIZE 50M02416 SHEET | o» 125 ��2 50M02416 ��CD sz 4-» xi 4-» o c: 13 ZD •— CO CD a zz o 4-» k_ — o oo CD X3 O E CD 3EE oo I— oo CO CD rsi •— v_ E o k— **— TO =F I— < EE CO CD **— XI 4—' o 4—' **— O 00 •— o 4-' — c M— — z CD CD LU co GO CD Q_ CC CD E 3 CO o •— o 4-» -a zz CD oo 3 CT sz CD 4—' 00 o !•_ o CD 4—' CI o c o o 00 a. o CD =3 o. CD XI h- 4-» c CD 00 CD i— CL 50M02AI 6 �»— o 4—' o TO CO c o •— 4-' TO rvi co i— •— 4-» xz — 1— o o 4—' CD •— c 4-» •— CI =3 4-» TO TO TO XI CxO i— "O o c O i— O- TO «x CO «a: z CO 4-' CI o E DO • —, 4—' c ZD o 2E TO — — U_ XI c TO 4—' i— TO C TO TO a. ZD CI o X CD TO TO TO CO CL TO CD 4—' O TO 4-» O V*_ — X3 CS4 •— z CD •— CD U_J CSi CD CO CL CL •— Y— •— •— TO4-» O c CO TO 4-» C o CO o 4-» a. XI DO TO TO TO E =3 o o •o CO xz 4-» XI 4—' •4— o C — — — u_ 2E h— TO XI 4-* CO l_ o 4—' 4— o •— •— 4-^ CO — •— o uQ_ DO C XI 4-» 4-» o DO CL 4-» •— TO TO U CO TO TO4—* TO 4-» c TO a. CL CL c o TO o TO TO 4—' TO CI CI c TO sz C 4-» c: >• *— •— — — — >— CD C •— \— Q- o CO i— TO CL E 3 CD o X3 50M02416 �L. o 1 CD) CD CD TO EE 3: O — H- -ID 4-' CD CD 1— CD LU OO —1 -a: cn 111 *• i z LU CD SZ CO CD o 4—' TO k__ CD CDCD o CD CD >• TO sz CD. CD "CD CO ID o CD o »— ID EC o c CO TO => -ID 4-' CO c — — — TO CD __ CD 4— TO CD 3: S <o v— <x CD -ID H— TO CO 4-» O CD CDCO . TO 4—* CO CD 4—' i CD OA i— o CD CD >— -CD 4—' CD SZ h- CNJ o CD) r— E o o H— o ID TO CO CD o V— o • — 4-' ID o o CD k— D3 4-» E LO CD 4—' o O M —— CD -CD 4-» O 4—» «*— O —— -CD E CD CO CO CD CO TO -CD o o CD 4-» k_ V— TO O- TO >« E CD **— +-> LO TO 4— O CDCD CO CD 4—' CD a) TO CO CD O CD •c£ CD <— 4-» TO TD CD 4-J CO CD 4—* CO 4—' TO CD '— 4-J CD •— 3= ~D) CD O 4—' O o t*— CO — a. CD -O CD CD -ID ID O TO t— CO 4-» •— CO E o o k__ CD CD E TO 4—* CD o o — O CD CD I— .d 4-» SZ CO CD CD 4—» CDCD CD CD - CD to XD CD TO XD CD CO O JD 4—» CD i O E o CD -c: 4-* •— * — EC TD ID TO •— 3: CD ID) <o 4—> —— SZ OA CD d TO — CD. 14- 1— TO o — CDL CO •— TD CD CD. k— CD 4—* CO TD CD 4-» o 4—* O k— Q_ CD O k_ 4—* CD o o 4—' f OA •— — u_ CD -CD 1— CD 4—' CD TO TO o CD =e o — — o *•— 4—' TD CD OA i_ k_ D) CD Q_ CD. TO h— -ID 4-' CD o •— -a ID O TO 4-» TO TO CD »— OA CD CD TO TD CD OA k_ 3 C"L CO -ID 4-» l_ CD o 4—* k— • — k— o E o CD- OA LO CO CD .a CD TO TO -CD 4-* •— "0 CD TO »— o i— 4-» CD E ' 4—' CO CD CD O CO CD CD O TO CD *— CD 4~> CO CD TO > > 4-J TO i CD OA i CD E CD O k_ •— TO 4—' k_ TO O TO CD — —— • CD "3" CD 4—' _ CO CD E +1 - CD OA k ID CD- TO TO E o u— CD. O 4—' TO u_ CD o CD — Li_ o O CD -O TO r—ID O -CD 4-» i— 4—* TO CO CD . CD CD k— D3 4—' CD k— CD. 3: O TO k__ CD CDE CD 4-» •— > sz i— o CD DJ TO CD CD. 4—' ID CD CD CD CD *o CD TO CD +1 TO CD CO E o o u. 4—' 4—' O ID •— — •— -CD Li— O LO sz CD CD. X CD c: •— TO 4-* —— CD l— CD TO o 4-' CD CD E TO i— TD ID •— -CD "O CD — TO 4J i— CD > o TO — CD l— O E TO CD — 4-* "a CD 4-» o "a CD •— 3: CD CDCD \ • — *— OA CD c > TO c: 4-J TO CD E TO TO CD >— CO I CD > o o CO CO CD o -d •— 4—* 4-' a. 4— o O E o o CD k_ - CD CD t— 4-' 4-» CD CD E D3 O o •CD E= D3 -CD 4—' CD CD E •— k_ CD CDL X CD CD -CD 4—» TO • TO k— CD. O k— CDCD- TO CD o CD CD D3 CDCD CO 5 50M02416 ��50M02A16 �o o ce <1 UJ _J o in in =r CD >—I to 2 — UJ CO >ct: O l— <£ en o CO <t CD cc UJ O <1 Q UJ 21 or 0 u_ a: uj a. CO CO 2: UJ CO _l LU O X I— CO — o x z »- <t CH UJ x 1— cc a; <1 o a. u. to UJ UJ z x O I— —I —I — to 12 o z — l— 1— «t <c 1— UJ CO X I— X ce: u- o o 3 CL. 3 3 - CD =3 CO CO UJ _J --J —J <t — — 3 H— UJ Z QC — UJ X z C£ CD <t <t 1— to Z V- CD z o — H-d —I _j O O z o t— Z o UJ 2: — cc Ul Ox UJ a: o • ce z: UJ o x o Hcr o 1 8 50M02416 ��2 o o en z <c UJ -J o - in LO r=r CD t- z UJ 2: zz CD z o —1 — =3 CO — — _J <1 1— zz. UJ 2 a: UJ Q_ — X UJ >- en O »— -=c cc o m c _i CD Z — CC UJ UJ z CD z — UJ CD z cc z 1— o < u_ ZD z <t 2 — z o 1— cc o 1— co Q — UJ M — 2 — z 2 O H- l— z CD UJ o z 3 UJ cc CC UJ UJ u_ 1— UJ z en ZD o UJ CJ z — UJ UJ z hhUJ 2 z • CD UJ o _J z •« <t —I »— <t z CQ UJ CC 2 UJ — 1— cc z UJ z CC o X o UJ — UJ _J CD _J <£ — »— 3= z — — — CO 1— z UJ 2 — cc UJ 0_ CO z o — h- c o t- u_ Q en Z UJ <c > h- fz z UJ UJ 2 2 z z CD CD — — —- _J _J •« _J en <r I— — z — o u_ Q UJ Q en UJ O z O 1— UJ cc CD z UJ CD 3: _J O _l _J _J o 3 . u_ CO Q UJ CO z UJ z o > —J — CD z cc z o O cc 2 — y— <c UJ — > y— o X Q_ en f— o UJ CO z _J UJ UJ UJ UJ CD 2 <£ z cc re z t- 1— _J CD UJ z o — I <t o 1— 3 10 50MCJ2416 ��. 2: 0 0 cc z LU _J O in LO r=r CD z 0 — 3D CO Q_ >- =3 o 0 t— <t en a: O CO _l CD —I «5 CD z C£ LU LU Z — CD z LU CD Z oc z t— O <1 U_ 33 Z <1 3 >- 1— z LU 3 Z CD — _] < _l < — H— z — CO —I —1 <1 O — • CO LU < O CO z LU LU a CO LU Li_ _J UJ _J QC — 3= O — CO CO LU <1 1— CO Z CO LU 1— 3: Z 1— (— O — I/O h- <t a <r uj a >• CO — J— ZD Ll_ — — > LU CO < CO LU QC > CD O »— t- CD z z *- LU — z 2: t-J LU Z — 21 CD —1 Q_ — — — —I »— Z <1 Z O LU CC UJ 2: h ILJ z 1— t— UJ C3 C/3 2 >Z _J CO CD _J — «t —I —1 <r <t Q O Z — UJ < tz a. t- LU O t— — Z CO <t 12 z 33 CO CD LU z — Ll_ 2 I— <t LU Z »— LU Z O tQ 1 1I UJ z CD — _i O LU < _1 Q- UJ CO _J —1 — CO t— z LU 2 — LU en <c C/J —i cr. UJ QX UJ <C I— LU Q _1 —1 <* LU «£>s 2 C\J ~ z =r >- CD CO 1 _J — O _J 31 -I o in 0 CO <1 CO CO Q_ 50M02416 ��15 50M02416 �2: 0 0 ce >- CO Q UJ 2! ce 0 u_ ce 1UJ i1 a_ z <1 UJ _J 0 _ z o — h— <1 Z — 2! CC UJ (— LU Q in in Is=r UJ CO _J _J — S — Q _J z 0 — ZD CO — 1— z - >- 1— — > <r ce CD U_ 0 A: UJ J— z 1UJ 11 O —J ac UJ t— >- — O I— 2: or UJ QC HUJ *X CH O CO • _J 1— CD z > <1 <T >- ce ce CD UJ z u_ 0 — III UJ Q oc 0 UJ z — CD z UJ 1— 1— Z UJ UJ 2: 0 z _J 0 <t — ce co UJ z 1— UJ <t h- CD z — CC z H0 <T LAZD —I z <£ 21 UJ z 1— 16 50M024I 6 ��UJ CO 2: o o cc UJ CO z <r UJ o - in in rrr z <r Z CO CO z — Q —1 — CD 03 - >- 1C o <t cc o CC o I— <t cc o CO 1 >- I CO CO CO < CO z cc LU LlJ — CO z UJ CO z — cc CD 1— o UZ z <r 2 _J —1 — 3 Z Ul CO 1— 1— => Z O Ul z z o <t z 2 z o — o o —I UJ < CO o o — 1 1— o z z O UJ _J —J — 3: —i 1 — CO 3: CO z — O 3 <t cc cc <t UJ —I z o h- CO z O — H<t Z — 2 cc uj I— UJ Q o z cc UJ lCO — z <x o Q UJ 1— Z ZD O 2: >_J UJ 1— UJ -J z 2 o o o <t Z CO z o — Z UJ <1 CO CC UJ >- 3: 1- o — _J > <t cc CO u_ o CC UJ 1— Z UJ O UJ z 1— CO co z — 3 z <1 Q_ CO Ul z h- U1 O z t— tQ Z UJ UJ _J I— CO z :£ < UJ CO CO <t 18 2 h< UJ Z I— - Q UJ _J _J <s: I— CO z — z UJ 1— CO — z •C O CO <1 CO z 1— — 3 Q UJ cc CO UJ CO Z z < t— CO o co UJ CO 50M02416 �19 50M02416 �<t CO z o — 1— <r z 2 cc UJ 1— UJ o >- z CD — Z in in r=r CD z — o — > <t cc CD u_ o cc UJ 1— UJ o 21 t— <c Q UJ _J CO 2 UJ CO to <1 z CO - >- cc o 1— <x cc o 00 <r CD Z — cc UJ UJ Z — CD z UJ CD — CC zo I— c_> Uz Z UJ <t cc 2 -a: 2 cc UJ t— UJ Q 11 1 III CO cc UJ z — <t 1— 2z t— o < c_> —J _J — 3 Q CD UJ Z _J — CO Q_ 2 o_ UJ — CO z CO CO «a 2 UJ fZ <1 I— UJ Ll— Z O h>1— — > <c cc CD o 1— z — 1— — U_ CD oz — CC Q UJ •< 1— o Z _J UJ o o 1— UJ z cc 1— o — cc cc 20 5CM02416 ��CO o r=r CD Z Q —I =3 CD O 1— ID LO r^z CD z a _i cc o Z to z <c cc Z CO Q LU 1 to z _J o z l— z o O cc 1— • Z 3: >- O _i Q _J < Q 1— Z Z LU LU 2 z Z =3 O CO z — LU > z Z 1— LU z 11 Li-I1 |I— CO — 3: CD z -J >— _J 3: _l z O Q O LU 1— CD Z z O — z a_ to z z LU CO z z CO h- CO 2 to 1— — <t 2 LU hz <t 1— LU z I— 2 o z Z Q Z hZ O Z CO z •< z I— X 1— •< LU Z 1— — <x 2 1— <t z z 1— z — Q z z o z LU CO z <r o z o — 1— <t t— z o z to z <t z t— • -—• O C\J CaCCl o 2: o _J in —I •—• <t z z o _J z to —I z — o — h— 1— Z -c Q 1— z o z 22 50M02416 ��_1 Q LU o > • CO o hZD O o LU z o CD z — cx z I— o - Cd O 1— <t Cd O CO «t _l UJ o z <r CX =5 CO CO <t >- > 1— — 1 — — (X cr <t Z — CO — 2: i— <t _J LU (X oO >- J— — 1 Z o o LU 2 z 1— LU CO o t— _J —1 1— — z 3: LU o - cx LU o z — c >- 1- _J z LU o Ho — CD Q z LU — 2 0_ 2 Q_ — — z <r CO LU Cd LU <X z t— LU z -a: O o i— CO z CO — o • r- CD LU =r z — — CD CD z Z CD 3: — <t Q CO z « 2 J— <1 — ZD CO z cx o LU LU u_ Z Q 1— — 2 CO o z — 2U o cx 50M02416 ��z <t LXJ _J o - CO o r=r CD z — o i — CO >-~ QC z: t— LU z Hcd z Q -X O —I z ZD O t— <c qc o CO <t —1 LU O z <1 QC ZD CO to <1 >- t— — _J — CO <t — —J LU OC °0 >»— -J 21 <t O O LU O <1 —I Q_ LU CO -J —I — 3 Q Z CO <1 CD <x QC CO LU Z 0 — — •< I— H- to z <C 0 —1 0 Q_ CD LU CD z z z — Q_ Q_ (- • — 1— to — ze: LU Z 0 t— to 0 Q: 5: LU LU z z Hhto LU >2: _J CO 0 O CO QC ZD Ll_ LU to Z O 1— QC LU O > LU U_ O Q SI — z LU tO 0 QC Z — — 1— LU <t CO O QC z <1 —1 <x Q_ —1 1— LU — to QC O3: I— CO Z t— LU <£ J— Q LU LU LU Zz > »- J- O 2: z UJ 0 QC ZD O O QC 26 50MC24 1 6 ��< UJ _J o 00 o r=f CD CO CD to UJ t- CO >CO CO zd CO >ex o I— <t cx o CO <1 o z <t cx ZD CO CO <£ (X <1 _J o CO 21 U_ I— — <x Q UJ UJ Z > UJ H- o z 2 • I— o UJ UJ 1— ex 2 Q UJ t— O UJ z u_ z o I— o CO UJ UJ 1— CO UJ t— CO CO —1 — —J z —— H5 »— (X -a: UJ I— Q CO UJ 1— UJ z O I -1 0 1— — 0 Q is z z 0 O O —1 z 0 UJ UJ CD Z UJ uj -a z en _i ex zd _J to —1 -I Q _J 1— - UJ — CO 1? z 0 v— CD UJ • z z zc CO — UJ 1— UJ 1— UJ -J CO CD • CO UJ CD <X \— CO UJ 0 <t z> 2; UJ ex ZD I— X ZZ O Z UJ 2: 1- H- CO 2; UJ CD CO UJ H- ex z <1 UJ UJ _J UJ CO z h»- -1 z ZD ex UJ 1— U. <£ Q UJ ex — ZD O <t cx oO _1 CD >CO CO CO < o — — 3 -I u_ CO CD DZ Z t— O ex 3: * ex >- ZD O CD z ex ZD 1— o <1 u_ Z3 Z *1 2 • —o — zr CM o 2: 0 10 •—• z 1— <r 1 CO o ex Qt— t— CO ZD UJ O 1CO «t UJ Z 0 — 1— *-*• 2 ex 0 u_ z • <a I— CX UJ o o <s <1 CD z Q — UJ z _J z CO -a _J ex CO — 0 UJ _J — <1 t— UJ Q UJ z 1— CO to ex o 0 X u_ o _ _ III — UJ 28 50M02416 ��cc . CO o =r CD z — Q — Z CO - >1— cc to o 1— UJ T— 1— z UJ S: >- <£ CC o CO o UJ (J z o z <t cc z CO CO _J QUJ Q — 3: <T >- 1— z CO — z UJ cc oB >3— — z z o UJ z 3— X to — o u_ z o z z UJ 3— z 3— o 1— z — Q Z Q Z UJ o 1— <t z 3— z 1— o <C s z UJ CO CO z z z z — — 3 3 CD UJ z cc — z 3 3— X z — o u_ <t z 3— z UJ s: 3— >o z z Q- z UJ 3— Q z CD o z UJ >>1 z z z •c O o z cc <r z 3o o z z z s: z Q z Z CO CO to <c UJ 3— z <t • cc 1 CO 0 z z 3— — z -I 3 CD Z Z CD o 21 — z — cc CO z 3 Q- z z 21 <r z z 0 — 3z • z <t z CD z s: z 0 — 0 z 3- cc 2: z <1 3— 2: 3— 1— 2 <r <c 3— <x z <t z z z o z z 3— l— •» — Q O 3 z 3>O >- o Q z — 3; 1— z Z 0 Q- 3— <x — UJ 2: Z O z — O Z cc z 3— X z z o Q z 3— cc z 0 z o_ 0 — Q z <t to UJ Q O cc <t —I o to CD UJ z o UJ >o _J Q_ UJ Q Z Q UJ UJ z 3= ^ O UJ z o $ .» I 30 5CK2A16 ��CO <t CO l— _J • — UJ Z 3: z < < 2 UJ o a. 2 O Q O Z °° 0 2 O Z — _J Z r- ZT co CO - >- CO hCO LlJ CC CD z o 0 Z - Z — r-j O 2: X 1— — CC ZD 0 t— —1 — 0 u_ 0 s-c O UJ - CO 0 UJ z O <x CC 1— ZD 0 CO <1 0 z <t CC DZ UJ 1— t— _l CO <t _J UJ DC 1— z <1 UJ —I — CC ZD 1— O — <t U. • UJ 0 z <t 1— CO UJ -J -J — > 2 1— — 3 UJ 1— Q CO z 0 CO —1 0 O- VCO 0 CC UJ — UJ 1— 1— z z 1— 2 CO 2 UJ 1— CO >co 2: 0 0 oc CO z 3: UJ CO >- _i UJ O- CO CO >- ZD UJ 2: U- CC ZD oO CD CC CD 0 <x Ul CO H- <t CC CO CO >- z • 0 0 32 ZD — CO CO 0 0 Q CO z z — 0 «X — 2 H 0 UJ z z z 1— U_ t— <1 UJ _J z 2 — CO <r 50M02416 ��cc 0 Q Ul U°a 2 <r 2 0 CO —I . LlJ —1 IT) Q O 2 Z O K<1 CC CO _l z —CO —1 Z z < Z Q oO O Z O Z O H<C —1 -I »— CO z CD O r^z CD z — 0 _1 — z CD >- z 0 I— <t cc 0 CD <t 1 UJ O Z -a; a: => CO CO «=c >- »— _J — CO <1 1 UJ z oO >- f— —I •d ZD 0 z 0 — »— <1 z CO 2 — _J > UJ UJ UJ z z z UJ Z H- 1— t— z z 1— 1— - 1— z <t 0 - 0 2 z I— 0 • 0 0 0 cc UJ Ul — z —I _J 1- 0 z ZD _J <t — 0 <r Z hUl 0 l— z —I 2 00 z I— z O z 0 0 z — Ul 0 CO z — co z — UJ 1— H- CO z z 1- <t -a: z 0 CC —I »— CD —1 Z 1— — — 0 z 1— > 3: z 0 z Ul 2 Z O Z O —I 0 — <1 — 1— a —5 LLl t— z z Q z <t —I CO »— H- Z CO z 2 <C >- Z Ul O CO — 2 0 z Ul ZD I— Q CC Z CO <£ UJ h- 0 — -J CO Z _J Q —I z =) —1 — UJ <t — • 3C 21 1— 2! CO Ul CO — Z H- z z — _J — <£ — 1— =5 <r Ul Ul z CO Q cc CO Z z 0 <c O 1- 2 —I z Ul _J z z z z — z 0 0 t— 3c < — — 1— h<X «=£ z _l — Ul z cc cc z 2 CO CO <r — — — z 1— > > 34 50M02A16 ��en z •d LU _J o - CO o rcr — ZD CO >- O t— <t en z — o CO •d 1 CD z — en o CO 3= 2 1— •d LU Z >V- h— - —J z — o o — -d 1— Ll_ •d z z LU O O- — O h•d CO Z — CO z — t— > CD z —1 — — LU 3c CO z CO o — — 1— •d _i Vz LU LU Z (— z cc 1— 1— •d CO z z l— — 2 LU O z <c 2 en cd CO CO <1 >- t— LU — 2 — CO •d Li_ O z o — 1— J<t LU z CO < — > CO 2 1 LU en LU o z z I— >d 03 >- »— — —• -d =3 o 1 _J — z LU CO — en CO LU CO o LU CO - 1 J •d t— o LU CD CD •d CO —I •d 1— CO en z (— — — Q <£ en o u_ - O LU 1— Z LU 21 CD CD Z z o — t— 2 •d 1— _i «t O CO LU Z LU 1— DC (— Z o 2: o O cr t— CO •d CD z — LU Z 1— z o o — H- y- LU Z -1 o o_ — 2 1— O <t o »— en z o o o_ Q- CO C3 Z <X en i— 36 50M02.16 ��o o bC o LLJ or o CXJ en CJ <x. en UJ en o a. to z -a: ce CO o o_ o q: to z <t CC >I— — _J o CO z — o f— <t <t cc CO 38 50M024 16 �"39 50M02416 �o CO o zt o Q en CO DC O Q_ 00 o oc •d ce CO UJ <a: QC O O CO <x cn CO Q O >O — I— <s cc — O <r U- CO zz. — o S <£ _J cc CO uo % 50K)24 16 ��• - cr> — to =r to z — hco LU 1— z o — I— cr CD — > en o U_ to z — h- •< 2 2 t— <t oa 2; CO z — Q —I — Z CO UJ en z i— X — u_ z o t— «a: en CO — - >- en o H<r en. o CO c —1 co z — en UJ UJ z — to z UJ UJ _l o — z UJ > °B z o — CO _J Z QO CC Q- > UJ z 1— z o Q UJ _J —I <C 1— CO z — UJ CO o z o <1 UJ —1 UJ _J —I <t O hCO CO z z o — o UJ 1— CO CO UJ 1 I— —1 UJ 3C z t- o _J O UJ 1— — z Q CO UJ h- CC o <r UJ _l z o Z CO o O UJ z UJ I— CO • _J z • t— CO UJ (— z o — 1— cc CO — > UJ z _J Z »— _J — CO _J 3: UJ u_ — CO o UJ 1— to en en <t z hQ. co cc UJ UJ z t— HCO — o z H<t c_> cn o UJ — z cc 1— CL 3: z O 2: — t— i— < •« hQ z Z UJ <T 2 z 2 CC _J 1— CO UJ Z z — t— UJ z 1— U2 5 CM)2116 ��O Z <1 O) TD =3" CD C3 X J CO T— CO O_ — -A: ^ • I— CO <O UJ IN CX CO Q I— UJ UJ 1— Z — DC CO — O Z — _J U_ <R CO >- Z Z -J •< <1 - Q_ O LU T— _J CO T— DX O LU TO CO CO o T— S < (O o Q U J I U UJ X CD < C_> UJ Z DC — CD o CD CO <t CO CO <£ to CO CO UJ CO z — z to C x o z UJ _l o Z LU > CO <1 o O- 2: O I— *X DC CO CD I— LU CO UJ > O O _J -a _J LU UJ to co z o CO Q_ O tx Q_ — H- TO to < >>- DC CO to UJ CD LU CO A- O CO > U_ O I— 3E CO S O LU LU I— «T —I I— Z UJ o SL z CO — UJ O CN OC CO UJ CO >- o to u_ UM 50M02416 ��Q UJ I— <C z cc O UJ — Q_ OL (— CO cc UJ =r o <T CO CO CD O -a: Z _J — —I Q — CO CO UJ >cc o I— <R cc o — CD Z O —I CO 2! UJ I— CO >UJ CO CO <r cc CO «x O I— CD z z cc UJ UJ z Q CD CD z O O Z UJ ID > CD O UJ 2E CO UJ T— CO CO — UJ O J— CD J— < Z CO UJ Q T— Z UJ < CC CO O CO —1X1— UJ u_ CD a. O cc Q_ CO cc UJ ZD J— O U6 50M»16 �2CD ujq: CD Z CDO >17 50M02416 �CD Z Q —I O) CO =r ZD CO o CD CO >CC O F— <r <* 2: UJ Q CE O CO «A CC O Q- co z <1 cc. cn O O 21 F— CD Q CC UJ -A 2; UJ O CD CO -a: z z O ^ O UJ Z UJ O UJ UJ —J O °a z O CO Q_ O cc CL 3: <X cc 2; CO I— — < > Q F— z CO •*t O Q_ 2; —J CR O OD O R=F M3 50M02A16 ��CO o Q_ CC O CC o r=r CD CO O hIco z CO O r=r CD CO o Q LU z CC CC CC UJ CO *3 Q Z -X I— < Q z < o c o UJ z o 2: z —I o z I— <t CC CO 50 50M02416 ��<1 LU _J o CO o r- =T Q CD CO Q <X y— CO >o CO on CD —l <1 O z <r t— CO I— <r cc o CO LU O z •< o <t o Q — cc I LU CC -j 2: LU CC >- —1 < I— CO Z — o o _l on O O 52 50M02416 �53 50M02416 �CO o =T CD O UJ CO co >CC z LU Q z <t o h- <x cc CD o «x CO UJ _l o z o z <t cc CO CO CO Q UJ <r t— Q CO UJ Z Q — CC O UJ O CO UJ CC CO <c cc 2: oO o >- o CC 3 UJ 2 2 Z _J CD UJ _1 z <1 _J -a <1 UJ o o 54 50C2416 ��O LU O O =5 Z Q z 00 o LU O cc o R^=T ZD CD CO LU Z CO CO LU CO Q LU CO CO >ce o CO >CO cc o 2Z CC — O HLL_ CO A LU <T CO CO O CC LU co az CO CO •<£ CO »— CO CC ZD CO CO <T zn LU Q CO LU CO ZD — Q CO I— CO CO I— >- O CO LU Q_ o Q- CO <1 O Ll_ — <X O LU CC CO CO <1 Z LU Z — CC U Z H LU Q < _J OO LU CC OQ O O >- CC —I <1 ZD _J <a: LU 2I I— O LU CC Q LL. o c_> 56 50M02A16 ��1 X — u_ CO O rzr CD z — 1— CO LU 1— 1— Z UJ >- o Q. UJ Cu CD Z — 3 Z O — (~ <t cc CO — > t— CO o Q_ Q 1 — ZD CO - >- cc o 1— <c CC O CO <£ —I UJ CD Z cc ZD co CO <r >- — i — CO <t — LU CC oS >- 1— — 1 < CD o O 1— 1 ZD LU CD 1 UJ ZD CC Q O >z cc UJ Z Ho 1— <r <t UJ CO CD z — O h- 3 LU z 1— LU LU <X > Z — >- (— 1— — o _l o Z Q_ 1— — LU Q T CD 1— z UJ <c — z LU t— LU CO z z 1— co o o 2: z Q o «c LU cc z t— LL. z Z o z O o o UJ y I— z o t— CD LL. z z 3: <t z o Q o o UJ LU >Z LU O o CO _J <r QI— _J LU LU —1 o Q — 3: UJ LU CD CO CO LU —I _J _l _l CO — — <1 3 3: o CO CO cc CD CD UJ ~Z z Q. — s 3 s ZD LU LU Z z • 1— (— LU CC CD ZD zz (— -=r LU cc t— LU <x CD CC — <X z z CD c_> _J 1 Q — z <t 1 CO CD 3 z — __ CO 3 Q_ y UJ <t z _i Hu_ O . CO _J UJ T<c Q_ CD °3 CD UJ Z h- y O CC u. 58 UJ LU DC 3 z 1— UJ cc CO - Q LU >- o _J Q_ UJ O .—. O CC —J CO LL. CJ t— Z UJ CC cc =3 o CO LU _J rz> O o 2: z UJ >z u_ cc 3 — o CC 1— LU > —I 50M024 1 6 ��o z <1 ex CO ex o o r- Q_ CO zt z < CD cc Q CO >• cc o H- >: i— •c LU I— z ex I— o 0- z ex <1 CD z Q <r o CC o CO *r <£ Q LU _J O <t <r z _J LU LU o z o_ CO QC O <t •ct QC ZD CO CO <t >- Q O LU I— CD CO CD Q <t LU CO CX CO CO <t CX Q <t CX >- o I— LU Q_ _j <t ro H- Z < CC o z CO 60 50M02416 ��OT <T UJ CD d cr CL CO CD or d O UJ d or co Q z ro O UJ O QT UJ ORO CO OR I— U_ CO O T- OR CJ UJ O X CD C\J O CO 2: 2; O O 10 or o or D O O UJ Z cc o O- CO T— CD CO CR CD UJ UJ CO cr or o GCO Q d d Z-UJ CO CR <1 or UJ L— >OR CL. O C. 0- =3 CO CD ZR D OR 1— 2 I— D Q DC I— O OR O_ UJ CO OR UJ O. N> CO UJ OR O CO CO D CD O OR CO O 2: — hd or UJ -I. UJ O UJ co cc o rr CO > D O SL or zr d <S) UJ — UJ F— OR CO — CO D U_ o o >CO O >Q_ CLCO CD CD <T O H- zr or i— hco d *2 CD CD UJ O G. O CO ZR O d or on D — CO — cc CD O 1— UJ zr _) UJ — 2! d zr I— O UJ or O — 50M02416 ��o CE O CE CE O to 2: to Q to <T CE — >- A. QCD CD CE UJ CE RO CO CE O DC 3: TO O 1 —IX U_ LU (— LU CO LU —I CO _J <1 — CO 3 LU >- O cc CE a- o Z3 LE CD CE CE — UJ < CE E3 Z CO O I— LU CD LU 6U 50M02416 ��HLI_ 1• O CD CC <x o cc 1Li1—11 31 1— O z <1 O i— z o o LU o <t o cc LU 1— cc o QCO z <x rv* t— S t— <C CD Z co <r X LU 1— — Q <r o _J z z) » LU CO <t CO LU o o: O Li ce — Z o t— CD z — _) LU :TJ LU CO —I —1 — 3 CC LU o CO 2: o t— Q LU t— a: O Qco zr <r QC 1— Q z <r z o 1— CD z — 1— 1 cc _J o LU Q_ CO <r ~T CC .—- 1— I— —i •y o P -d — cc LU LU z 1 — <t CC •— 66 50M02416 ��UJ UJ a: or t— t— <C o CC O O UJ O CD Q <t I CD O o cc CD CD Z o CO UJ UJ UJ S < I— UJ —; X) CO 2 O o cc <t <1 CD Q <1 o R UJ CO DC I— CC UJ O u_ 1— CO z o <c UJ cc ^R o <C LU 2 CQ X — I- -a UJ lCO Q o: Z — -I < CJ I — Q CJ 3= UJ — > R Q CD CC Q. UJ R Q cd z O -a: UJ —J o cc I— CD <x cc o UJ CD <t Q_ CO Q CC O CO cc cc a. O QCO Z <t CC I— CC UJ > o CD CC UJ X R Lu O < CC - O V UJ X re co q I— z u. -a: 3 cc h 68 50M024 16 ��o UJ o z: iuj z: Q Q UJ z: > <C o 21 o z o <t z h- o o tx CO I— cc cr: UJ <C U_ O CO <t UJ z cc <* UJ CX UI— CO o o z CO UJ «I z: ix o O cu • O UJ —1 o CD —J z o <t • IX I— 21 UJ CO o O CO CX cc CO CO CD _j _1 — 3: UJ u_ CO Z <£ CX 2: t- z < UJ _J o 1O <t UJ o CO UJ X CO 2; CO o o CO CX —I u_ o 70 5>C CM M' 0 2 4 L 6 ��o 0 z <c 0 Q z LU LU LU _J CD CO <r 1 Q. LU _J —1 1— LU Q CC 3: LU <1 CO — Z <1 2: 0 0 hCC <t 1— Dr LU 2 1— <t O CO lu zz z: 1— <x LU — Li_ 1 CO z 2 H- t— cd 2: O Q: <r z z — O O ce I— — z CO <1 0 Q- LU —1 O - l£> ro CD z — Q —I — ZD CO - CD CO 2: CO LU 0_ O z Z <c LU 3 co 1— CO _J 1— <t CD Z LU 2 co a_ • t— CO H3 z LU — 2; 1— <r CO — O 2: 2 z CD LU 1 DC <1 1— LU :c t— CO <t CD Z. LU zo <t I— CO LU I— Li_ z CO ZD zz O CO t— LU T CO LU LU CO O LU > O O LU CO <1 Q_ LU O LU CO z <£ LL- CO LU Q LU CO 0 CD 2! LU a: LU 2 2: CD — _l <r O LU > LI_ — O LU — U_ — f— O 2 <c oc l— LU q: 0 u. 0 LU —I O co Z CD 2 CD LU _J CD — H- 1— CO <z Q_ O z: 0 — CO >Z < —I —I —i CD <t ZD CO LU — LU > zxz tQ Z LU LU CD Z CD 3 <r CO z ZD 72 50M02416 �t^msr. '*r. OF ;v i^^Miiiac«*a.'^r^5a«\,*rwjr»'»*F*-J i 73 50M02416 �cc UJ Q Q UJ Q UJ 2: cc cc UJ CO O u_ cc UJ Q_ UJ CO •D O CO z CD O CD cc UJ > O z F— — O I— z UJ 2: 2 CD I <r < z o o cc <T UJ _1 O TO CO CD z • _J ID CO O O — <x CC |— UJ 01 > O Q_ I— CO z z UJ <T 2: CC Z F— 3: <R I— cr cr <r o _J o_ O CO CO z •d UJ ct: 01 -O UJ O 2: UJ z or CD <t — O_ —I UJ CD <1 CC 2 J- CD z o — z 3: -d CL. CO < UJ O —I O _J UJ <1 UJ U. CD I— CJ> O O CD CO UJ CO cc 7U 50M02416 ��>- cc o t- o •— <r h- Z cc o CD <T _J Z O — LU O CM CO ""5 Q <£ — z O o _J 1 cc o _J — ID CD <1 >- <r X o I— <t c t— — — CO Z LU 2 z o cc cc o CD <r — > z _l CD t— <C _J _J <1 1— LU CD z — z z — • DC LU > o o DC LU 1— DC O D_ CO z «I QC t— LU _J _J LU o Z UJ o cc b- UJ O <r 0co I— LU CD i 21 _l —J m CC LU CO 2 <1 — — o L— CO s z o LU t— <r cc LU Kcc o Qco 2 ID ID C_> <r CC o Oco T~ <c cc 1— c_> >— z LU 2 z o cc — > z LU 21 t— <t LU o <t Q_ CO z <t cc >• 0 LU z 0 — 1— — CO c D_ O z <C h- 00 DC LU Lc CO cr <r DC 1— s O •< z 2: DC LU LU DI DC 1— 1— > LU in I— O 2 LU DC t— Q LU 76 50M02416 ��<r QZ LU CO 2: •< zc o o 1— oz LU 1— oz o CL CO Z <t oz t— 2: o oz Li_ CD LU QZ QZ LU Li_ CO z • CM CO CD z — o —I — zd CO - >- qz O I— -=r oz C CO •et 1 Z o — 1— <r i z 2! — CO _J t— <E oz h- LU 2 2: t— <r o QZ — z z > z LU UJ O <t Q_ CO LU zc O 1— LU z ZC o — 1— (— CD O Q LU 1— z —I < —1 1— 1— o QZ CO QZ <t O QZ LU LU CO LU ZC ll_ CO 1— ZZL _l <1 — 2 QZ 3= o QZ t— - LiLU CO CD o: t— — LU <t h2: QZ CO — O QZ z O Li. o zc Q o LU LU LU CO I— \— CO Z —1 — zz> —1 o o — QZ 2: 3: LU - 2: CO i— I— QZ <t _J <1 _J O LU — ZC 3: LU (— QZ 2: 1— • i— QZ -a • LU Q t— CO QZ 2: LU CD <1 <r CD O QZ <t o CO QZ LU Z> LU U_ \ QZ CO t— I— Z <t LU QZ oz 1— t— 78 CO LU _J o • Z O — t— — CO O CL. z 3 O o O 2= LU zo CO LU ZC hz — o LU o <1 _J Q. CD Z <£ CD Z <t i— CO 1— ZD O S»Z o LU zc o o — 1— 1— OZ I— <t QZ o_ CD ZD o o o QZ o CO o QZ — LU CO cd 21 z -=t ZC o >1— LU — ZC CD h- — 2 CD Q5 z ZC <r LU - > Q — LU 1— CO o —I —I LU o OZ LU ti5 CO O =r _1 —I — li_ 3: o in QZ O CO O ZD CD Z QZ LU CO 2: <z QZ O LU QZ 1— — 21 QZ o CO ZD _J Q- • QZ LU CD QZ <r _i CD z <r CO z o QZ O — 21 Ll— o in o r- o 50M02416 ��CO 1l_l_J 11 f— t— CO =3 CO s 1U_J 11 I— CO • CO co CO CO LU CO Z — Q —I — ZD CO CO >CO >- <t s ce i UJ ce Q_ CO CO U_ -=c o z z CD «=t - CO CO s Z LU ZD Q 1— CD LU CO S 1— ><1 CO CO — _l > —I LU LU Z ce <t •c en O o CO <c _l z o — t— <1 _J ZD LU or I— z 3= O — CO _J <r l— z LU S Z o or — > z LU LU O <r Q_ CO CD CD 1 <r ' ce Ce 1r— <1 t— CO LU CD <t LU re 1— >- CO CD Q III °3 U-i ce CD o i— i1 1• 1i re z I— CD LU DL Q_ S o o CO ce z LU Ll. CD _— re h- o \— UJ CD >- _i Z Ll_ _i ZD — o U— ce ce CO > z z — LU t— Q CD CO o O z t— — LU Q_ Q CO UJ 21 33 S a_ ce —J CD o u_ i— ce UJ ce Qo — UJ ce CO CL. z CD —I 1 — 3s ce z o —I — UJ ZD 00 03 S <x CO or — — CD or 3 t— LU CO or z l— — o — UJ o 1— CD UJ <t — f— ce CO <1 LU 1— CD Q- ZD CD o CD _l 80 50M02416 ��CO cc <x 1 _J 1 LU o z CO 1— Q 2: z z <x t— <x CO Q LU LU _J z 1 LU 1— o z z 1— cn CO cc z o cc Q_ LU o LU —I CO cc DC 21 z 1— <x LU 1— 1— t— CO . z cn Q >- LU Tcn CC o III U_J LU u_ 3= 1— CO o o _J CO —J z o —1 CO o_ o — LU 5 cc 1— LU -a: CO 1 CC cc O. o Q o z 1— 2: CD Q LU <r c_> «=r 1 _j LU z ZD LU z CD 2: Z cc cn t— LU CO > <t co o 1 z o <r >- H- 2: CO cc - LU o —I Q CC DC 1 LU LU t— o t— CO U_ <r 2: CO (— z o DC 3= cc O — CL ZD Q LU I CO O C\J ro co ZT — Q —i — ZD CO >- cc o 1— <1 cc o CD <£ _J Z o o o cc o — 1— •< 1 ZD 2! — cn —j <t I— z LU 2 Z o cc — > z LU LU O <1 Q_ CO — — - — • — — — — 82 50M02416 �83 50M02416 �LU O -J cc <r cc l— CC z Li_ S Q UJ LU CC Q I— Q Z ZD Z OJ ro CD CO CO o <t >cc o V*1 cc o CO <C cc LU LU Q CC CO <r =5 CO z 3 O CD Q <1 O O LU Q Q_ LU o LU CO <1 o CO CC <t CC LU Lu CO o <t <1 3= >- CC CO LU CO O S LU <C Q CC =3 c 2: cc UJ CC CO H- CO (— O LU zc. z I— <x _J U_ Q_ O I— O CC UJ or cc CO I I— CO T— LU CD CO CO Z CO — Z LU o cc _J LU — O • 3= Q CC LU S LU T- h- CO CC <r S -a: <r o <1 o_ co i— LU zx: co Z CJ I— (— LU CO 8U UJ =3 O ZD O CC <C LU > CC <t =3 S Lu CC 50M02416 ��1 CD z Z LU 3 — — Z o 3: 3: I— CD (M 00 z 3: O O Q Z LU 1 Z ZD 00 o hS t— <1 u_ o z o — t— <t t— o cc CD z — o _J — ZD CD - >- a: o i— z UJ UJ O <r CC to LU CC a Q CD <r 2 z <1 <t LU O o •S) O z CC LU z — UJ D» CO z O UJ 1— ~*T UJ z LU z • 1— CC t— - o LU o 1— <r CD HCO CD LU _J Q 1 LU f- O LU — 1— s Q 3 < ZD _J 1— ZD o CO o o u_ Q cc <c 1 > o UJ UJ z — CD •c z CO _J —J s LU cc z cc — LU < <E 3 z _J _J 1— CC o 2 CO t— <r Lc CC O <c o z z UJ z z <£ z o _J h— to LU cc 1— LU z o Q _l 1— I— UJ <r f— cc 2c o _J CJ O t— z LU z O Q — z LU LU CO o Z CC o h- LU —I to 3 •< — 1— O S Q <t _l cc UJ UJ UJ z CO CD t— CD 86 • a LU i— o LU T z o o LU CC LU CO CD Q Z z o — 1— — CO o cc 50M02416 ��CO CCJ I— CO UJ 1— CO _ UJ (— CO >_ co — 2: CC UJ >— UJ CO >CO LxJ or 00 Q h- O O U_ ZD Q uj S CC O U_ CC UJ 3: — o _i — CO >- CC o o — 1— <C CC UJ O- Q_ o S O I— O <1 > O co <t -J —1 az — o 2: CC UJ nr I— O — I— <c —1 CO UJ UJ 2 I— ZT o co cc co o Q_ — co H- z co UJ >- _l < CO t— 3: uj Q <r uj a. 1— co O > UJ CC CO co <r ro ZD <t CO CO — > z uj UJ O <x OCO UJ UJ CO 31 h- UJ C_) zr. I— U_ o t— z o <t UJ u_ UUJ 88 50M02416 ��Q UJ CD CD d CO UJ 2: o o oz Q Z d z d UJ —I o QZ UJ CO UJ 21 CO d z —I o 1 — UJ 3: z 1 r~ cc CM ro CD z o —J — ZD CO 1— z UJ 2: Q_ — Z to oz o UCD z — Q <r o - >- CC o hd cc o CO d i z o CM CO CD z Q 1 2T (— Ud O — z CO UJ t— Z z 1— o UJ z 1— t— o CO UJ UJ —J 1— _J o to oz 2 » UJ t— 1— CO cc >- d CO o o 1— ilZ o d CO — • f— UJ QZ oz z UJ UJ 1— U- 1— co QZ u_ z o o d a_ oz co z 1— z d o — UJ cc J— z t— UJ t— _J UJ Q_ o z 2: t— t— o o Q o UJ UJ I— z DZ CO — ir o o >— z UJ <t o o d z —I d Q- < ZD 21 — CO 1 <t t— z UJ 2: z o QZ — > z 1 1J1 U UJ o d o_ CO 90 o UJ i— QZ o QCO z d oz 1— O ~ " — U- QZ UJ UJ CO > UJ _l QZ _J — \- 3 Z UJ 2; s 1— z d CD UJ _J Z d 1— oz o u_ 50M02416 ��z o — I— < CO — U— cn LLI > t— z UJ 2 Z CO — _l <£ 2 zd ZD O c > \ _i <s 2; cc UJ Z t— 1— CO 0 Q_ • 21 O O cn z «i UJ _J CO - CD CO CO z 0 1 — ZD CO CO co 2: z 0 2: cn UJ 1— UJ Q t— <t cn O hQ UJ 2 C£ O • U_ 1— cn z UJ UJ o- 2 z UJ 0 m cr — —1 > _J z — UJ 3: 2 Z Z3 O ZO — CO t— <1 < > O — —I u_ <s — 2 OC CC UJ UJ > z i— 1— Z UJ UJ z 2 Hz CO u_ 0 —I < CO t— 2 CO 1— UJ < U_ u Z Ul «a: UJ Z V— 92 <t QUJ QC o_ Z — O UJ CO CO < CO UJ cn UJ CO _j — 3 2 1— UJ z y« 1— z UJ 2 z z CO 0 — — 1— <1 1— CO 0; T" 0 CD3 CO O z _J <r _l DC O tu_ CE O U_ 50M02416 ��l— U1 >- o CD cc <r o CC UJ m 1— Q_ QZD CD UJ CU ZD CO 2: o cc o t— u_ zz Q UJ — cc UJ I— cc > • z CO <t X UJ 1— cr h- UJ o Q_ CO CD ~2Z — Q <£ O 1 - CO < CO UJ o cc o u_ cc — <t zzz o 1— CD zz. _J i UJ o 2 UJ CO >- _1 Q—1 Q. — ZD 3: CD cc UJ 1— CC O QCO z <r cc h- cc UJ Q_ ZD CO UJ in h- o i— 2 z: f— — <r cc UJ UJ m _i 1I c cc h- 94 50M02416 ��z 0 1 r~ <t 1— UJ 0 1 Ll- Q- CO 2; zc 2 O 0 O z UJ <1 ZD O I— O <1 CO - DC UJ h- CD <1 cc _J LU cc <X H- li ce: 0 Q 1— O O —1 UJ CO CO u_ ZD 1— O O LU Q cc cc O O 0 2 O- Ll- z 1— — CU 00 t— z O H<t ZD cc z LU cc — L— t— CC <t f— UD O UJ «I CD CL. cl. —1 1— Lt- — UJ UJ to CO H- to CC 21 z <t z cc — Q Z z <t _] <t cc —1 H— — LU 0- Z >- — t— UJ ZD ZD 1— O <1 LU > CO z — 1— J to J LU — — ZD 1 t— • <C O 2 cc Q. 2 cc 2 Q_ UJ UJ 1— <1 CD _J O O cc JZ h- >t— Ll_ t— 2 LU ZD ZD O O O CC a. 1 3 2 ZD J O O O > 2 J z t— C m 2 (— CD CC UJ — UJ 0 1— _1 1 <1 Q_ u_ ZD (— UJ UJ ZD O 2: UJ zc 1— • 1— zc O UJ 1 z: l— 11 1 O DC t_J 11 1 LLJ zz LL- ZC — CI CD 96 30M02416 ��cc 111 LU —I <t cc 1— 1— Ll. 1 o CC CC 1— CO Q CD <t o cc — o o co CO iC 1UJ 1 1 cc (— S z o — it: co it: o cc 11 LL. Q ILU II o <x Q I1 11 1 (— CC O CC CO z <1 cc (— T 1— c 1 Q. —i CO LU O CO CO • <t Q — cc o _l Li_ •» Q_ — CC 1— CO o — iC CO o CO iC _J 2: _l LU — 31 3 hcc o LU I— 1— cc o O LU cc CO z <r t— cc o cc CC CO 1- z <r LU CC 3= I— I1 Q z <t 98 50M02416 ��CD O LU CO z 2: I 1— UJ 0 z 1r~ I CD O CO . en O UJ en en UJ u_ en z <t en > UJ —J CO CO 1L—I1 —1i z en Li_ — UJ 0 _J 1— z en 0 -a 0 z UJ o_ UJ _J en 0 z t— -a: CO UJ oc UJ z h- X bo O h- 1 UJ - CD Z — O _l — ZD CO en z 0 — b<1 en UJ Q_ 0 I— u_ <t en 0 UJ O c Q_ en CD UJ z z «t 2: 21 UJ 0 1— z 1— <t 1— CO UJ 1— <x <1 z I— CD 21 UJ "5T O — O O u_ en QC — u_ 1— z en CD <t UJ UJ UJ 0 en _J en 0 UJ o_ u_ 2: ZD en 1— z <x. CD <t UJ en UJ _J b- z <1 (— UJ UJ CO CD z — UJ CD —J 0 — z _J 3= <t —1 CD UJ CD CD <r CD -y z b- — 2; "5" en 3: H1— -a: <t l— 2; ZD 0 UJ UJ O 0 z z zn Q: 1— 1— 0 UJ UJ 0 z z z 0 b- <1 100 50M02416 ��O UJ UJ ZD ZD 2 o o O: Z <t UJ CO LU —I o s 1— <t - CD z — >- o —I Q_ UJ Q CD Q _J — ZD CO CO Z O 1— <r — CD U1 1— UJ _1 zz DC — UJ CD 3D 3= 2: >- CD oZ Q —J <x UJ Q_ CD UJ CD ZD Q UJ CO 1— <z CD CD UJ ZZ UJ 2; Q— 3= CO UJ z CO UJ — ZD 1— z — Q UJ CD —I _J 1 _J 3= <r >- ZD CD CO UJ — 3= O o. <r UJ Q_ CO <r z O _J z UJ —i ZZ «=t f— 3z Q <r UJ CO UJ —I > o —I 3D s UJ 1— > — UJ CD • -z- O 1— — — CO o 0_ o LU CD CD O. O UJ <C t— o CO 3D _J o CD Q_J CO — UJ Q 1 — UJ 'S- DC u_ UJ h- O 3D HCD UJ h- u_ <r CD CD UJ CD <t Q_ CO • UJ z zz <t ZZ — Z: CD • CO >- Q ZD Z cz Z <t — CO CO DC UJ CD CD <r — <r zz> UJ \— 3D CD X h— Ll_ 3 3: — 102 50M02416 ��<t 2: LU 03 CD LU CC a. O —J LU CO I— —1 33 <t — I— CD 3 • — o o cc Z O — I— <1 CD — cc z I— O O CO U- — LU I— > O <t Z LU CD — —J — —1 Lu _J lu <r — <t LU o < CD z CD • ZD CO CO z o <t CC LU Q. O CC o LU o <r Qco Q — h- CC CL CC CO LU — LU Z > (J LU Z CC CD LU Q. CD CD CD — — <t — 3; -J LU <c s < >- _l CO . (— — <t (— Z Lu Z Q Z LU QC UJ LU 2: h- LU N S — CO I Z CC UJ Z D CD LU (— o. X LU CD < LU CC LU — LU _l D CD < O Z LU J K CC CC —I LU LU CO I— — x :x C — LU (— Z I— H- Z CO LU — <T <1 CO ^ z Z 1— a_ — o z — CD Lu LU 21 2: o — LU CC ZD LU >Z O CC Lu f— Lu H- I CC CO CO CC LU Z LU LU a_ I 04 50M02416 ��UJ a: (— o z <c I ) UJ t er CO z UJ 1— CO >- CO z o o en 2: <t UJ _i o 1— ZD o o UJ re o CO 2 UJ 1— CO >CO 21 1— z (— <r - Q UJ t— o UJ z z o o UJ CD — CD z — o _J — J UJ z <r Q. CO Q U— o z o — 1— UJ _J Qz o o UJ re H1— <r • z ZD en °S o O I— =3 UJ Q_ o — (— c a: UJ Q_ o I— u_ <t en o UJ o <r Q_ CO Q UJ z z <x z >1— O 1— o en Cn Q z <£ UJ rC 1— • or UJ o UJ 1— <t z hu_ O CO z (— «s. o_ co z <r Q z <t Q UJ CD CD <1 CQ UJ CO Z _J en o u_ z o t<1 or <c o_ UJ en en z — o UJ re o CO z UJ 1— CO >- CO UJ O c en UJ 1— Q_ <r <t CO Z ZD o z z i— <r _J 1 z — (— 3= <£ z i— UJ re H- UJ re t— u_ o < en - o t— 1— ro o UJ _j it: re <t o t— z UJ — re o Li o 1— 06 50M02416 ��Q zz. <r Q LU t— o 2 O o LU o o ac z ZSZ o CD <r LU >- zzz 1 _l _J <r LU 1 o s: h- <X o s: i— <c LU cc t— - cd ZZL o I— —1 —I — zz cc <r LU CD o — cc — 1 2 1— <t zz *2o (— LU CC <x. 1— CO LU o <s t— Q z <t Q o LU LU LU _J zxz > LU H- o • — zz zz. O — «=r — ZD CD (— cc _J o <r Q_ . LU to CC _l 00 LU CD CD cc LU <t < CD I— o CD ZD Q_ o <1 cc s cc CD LU L— CO <r Q_ <r . s: LU cc ZD LU 1— CD LU ~Z> CC ZD CO ZZZ O — 1— <1 a: LU D_ —I HQ LU C o to LU CD _J itC s L±o 1 LU LU CC CC CC LU CD 1— o to o 3: 1— Ll_ <t cc o UJ o I— CD <t — cc cu CO cc Ho ZD o cc (— cc \— o ZE 1— Ll_ o o LU >1 1 o LU LU (— o DC CC 1— <x LU 1— Q LU ZZZ h- Z3Z <t z ZD o s. z 108 LU CC t— z z: o o o LU _J LU 50M02416 ��en LU o <t QCO en Z <r LU o 2 tC - CD z — o — ZD CO CO z o (— <r DC LU Qo LL- <£ QZ CJ LU CJ C 0_ CO i 11 i• _J 1— LU •Z 1— - 1— I— zr. z z nz • T O O LU CO Z <c CO LU ZD > LU o 2 Q_ O z ZZ) 1— CD 1 1— CO 1 zn LU <£ CD 1— o CI LU LU O 3: ry CO z 2! 2 CD LU _i CD CO o o >- z LLZ 2 ZD 1 CO o LU LU en. •=1 ZJZ CD z o LU — o 00 en — LU t— _i 1— CD — <£ LU 00 21 — _J — 3= LU zo t— o U- CO Q CD o LU Z <t 00 _J <z CO LU LU «a CO zc ziz CJ LU h1I 1r— en <x O Li_ LU 2 (— o o_ ~5" >- QZ z ZD LU _I zn o — <T 1— O CD LU LU — 1 CO z Q_ ZD 2 Ll_ O o Q z LU <x zc <c 0= UJ zn i— Lu O t— CD LU Ll_ LI_ LU LU Z1Z t— z CD 1UJ 11 oz CJ o 1— CD CO <r QC LU 1— Li_ — — en en CD <c LU LU I— 2 CO - LU > LU en z z H- en o ziz LU or LU LU (— CO 1— <1 1— I— en <r Q_ LU • -=T 2 _J LU z <x _u -a 3 f- Q LU <c O O h- — zc 50M02416 ��3 2: 0 0 3 z <t LU 3 O 2 h<c 1 CO =D UJ OO 3 1— 3 O X 0 OO 3 UJ 3 — 3 Q UJ UJ CO 1— <c <c 3 LU 3 3 O O CD 3 Q 3 3 CO 00 3 0 h<1 3 LU 3 O 1— 3 <t 3 O LU O <1 QCO BE 3 CO CD 3 3 f— z - 1— CO UJ f— 0 0 00 3 O _J — CO 3 CO — 1— X co UJ 0 1— UJ 1— UJ I— _J <x 3 2 X Q CO 3 «=t O 3: 3 -a: 2: 1— <t 0 X 2 LU _l X —i UJ 3 1— Z — 3 h— — 3 Q UJ t— Z 3 O X 1 LU Z <1 3 O °o O - Q LU Z z <x 2 UJ X 3 LU y- f— CO >- co 0 X 3 3 t— 3 CD — 3 3 1— 00 3 t— 3 1— <C "^7 Q 3 <1 3 3 3 1— 3 O Z O 1— 3 3 3 X O C-3 3 3 h1— -=r 1— CO — 3 <t 0 1— O CO 3 3 <r 1— 0 3 CD 3 t— 3 3 3 — i— <1 2 H3 3 3 00 0 3 3 3 2 — 3 > 3 3 3s I— 0 CO < 1 CO 3 0 3 3 O 3 3 3 CD 3 0 — <1 JC 3 — i— > O 3 3 3 3 3 3 O 3 CD — 3 CO 3 = > CD <1 CD 0 2 1— <t 3 3 — CO CO 3 0 (- 3 <r 3 — 0 3 — 1— 3 — 3 3 3 1— CO CO CO — <t 3 3 3 3 3 3 3 <1 t— 3 3 3 O CO 3 — O 3: O <C 3 3 3 • CO •< CO 0 3 3 3 O CO 0 3 1— — X — 3 CO > CO t— 3 3 H3 O O 0 <r 3 0 O 3 <t — O O 3 3 3 0 3 3 X 3 3 l— O (— 3 CD O • f— 3 3 0 3 3 O — <r 3 0 3 3 3 — >- O 0 t- 3 3 CO — CD 0 — 00 CO 3 O 3 — 0 3 3 — 0 3 1— O 3= 3 sc 3 0 — O 3 3 3 3 - 1— CO CO UJ Hc X o 3 <£ 3 0 3 > • 3 h<t 3 CD 3 1— 3 1— CO <r 3 3 3 t— 0 l— 0 3 t— 3 0 3 CO 3 <t 3 h- • 3 3 <t 3 0 Q Q 3 <r 3 3 Q 3 3 3 H- > 3 0 — 3 3 3 X i— h<r >-. • ^ CO X 3 0 3 3 -=r 3 1— 1— co <t I 12 50M02416 ��<z —1 I— CO LU t— LU z h- o LU — (- Q LU z <c or CD LU t— z — CO or Ui 3= O _J 1— CO <r LU z h— z 2: t— <r 2: i LU or ZD 1— X — U— — ZD CO CO V CD o — L— <C or LLJ Q_ O z — c zz. <r DZ Q 1— Li_ <t or O LU CD <r OCO Q LiJ z z <r 21 DZ CO 3S — Q —I 3 Q LU t— <t 21 — — Z ZD o or CD s: V— <t Q z <r hCO LU z 1— CO • Q Z c or <£ LU _1 or O ZD CO 1— X 2 — 1— LL. <T CD LU z DZ — 1— _J Q Z O <r z DZ <c f— Q CO Z ZD 1— o CO or LU CD hLU Q DZ LU 1— T— <T o or 1— CD z LU — h— Z o — LU or »— LU CO 3= <t O LU _J i m CD z — • LU DZ t— — LI_ o 2: or or o ZD LU h3= I— O o O —1 CO LU CD LU LU or ZC ZC ZD 1— 1— O- or LU 3 — o s —I Q —J LU _l —I CD LU z L— LU CO <r hCO z LU CO - <t <1 _J CO LU or ZD 1— X — Ll. CD 2 — _J Q Z <r zc o z ZD o or CD LU DZ t— Ll. O Q_ O 1— Z o Q LU O <1 1 CL. 0 0 >1r~ 1 1I —i o <r LU ZD Q z Z LU o — Z <r 1— CD I— z — t— o _1 o <t LU LU Q CO CO z <r z LU o DZ — LU 1— 3: _i 1 or <r 1 LU iI— Ir— CO 3= CO — z — Q —I <r LU LU CD CO — ZC 2 _J CO L— C — or <r 3r LU _J Z 2 o HI— CO <r • 21 2 LU 1— T— DZ <T <T t— LU LU Z Z i— i— — z o — 1— <t or LU OO CO — z i— 50M02416 �I I5 50M02416 �o I— <r _i <t i— co o o Q Z <T (— CO 1— CO UJ 1— Q UJ I— -a: cn. CO CD UJ 1— z Q z <r 1— CO <r UJ o cc UJ I— Q_ <t O <£ Q O cc <t -=I cc c_> UJ o <t Q_ CO cc UJ Q_ O- CD z — Q —I — ZD 03 CO z o — t— cc UJ Q_ O hU_ -=t CC o UJ o >=t Q_ CO Q UJ ZZL Z <r s o_ o o 1— UJ cc —I UJ z _l t— o <1 cc 1— o UJ CO a. o z CO <x z —J <t o_ UJ cc CO ho (- _J o Z _J —I — —I 3: o Q Q_ UJ cc <1 CC UJ UJ > UJ s o z o o t— -J X o o UJ UJ 1— _j CO 1— Q_ CO Q s —J <1 UJ o —I —I cc o — Q_ cc 3 UJ z u_ CD UJ _J CO z z CO z o <r <1 o cc cc UJ 1— UJ 3 UJ CO o UJ z o 1 cc Hz z UJ 1— o o z o f— z t- z cc z . 1— o <t CO — 1 —I hCO CO UJ <t cc 1— cc cc — cc UJ UJ 1— o Q. s Q_ Q_ o UJ CO z 1 -c UJ <r UJ UJ z cc z z 1— f— 1— 1— Q cc u_ z o o <£ u_ 50M024L6 ��j j I Z o 33 — t— X 33 CO — —1 «I 33 3 1— —1 <t y CC 03 <1 _l hr- t— — n CO 1— 33 z CO r^n X LU 1 CO s o o X UJ —i CO 2! O o m o z z> <=c —1 o 1— o 1— t— o LU 1— CC o QCO z <t cc 1— LU CO — CO z <t cc f— Z — t— <t T _l —I _J — 3 s H<r s: i LU z t— Z. — o 33 o LU y —I LU O — 03 o 3C cc S _J 1 z o — <t LU LU z _J o cc o LU 1— 1— y CO 1— o <1 z — z o <c LU o o 2! h- X —I s: 1— co _l <1 LU <t > s LU <1 OC Z LU LU 1— Z I— • t— CC — LU LU 03 1— LU cc —1 o — _J CO 1— — CO 3 2 LU < **7~ <r CC 1— _i 1— CO s; o o LU cc CC _J Lo — o 1— Q_ Q z <c LU LU CD LU CC LU 3C 33 z I— Q- I— |— 50M02416 ��CE 1UJ •1 hQZ O 0_ CO ZZ <t ce I— O —i i O a. <t UJ DC t— 2 O CE u_ Q IUJ II 1— U— CD iE O <1 f— CO CO ro LU o — _i CO l— — Z =D 1> s: UJ S ZD cc hCO z IUJ II DC 1— —1 1— <£ 1I I11I CO Q UJ —1 1— —1 <£ — 2 S Q 2 1— <X o o o zz ZD <t <1 CO CO X UJ —1 Q_ 2 o o zc o z: ZD •a: —i I 20 X UJ 2 _J —1 c_> O ZSZ UJ UJ Q > ZD O CE zc CO z UJ UJ zc t— DC O z: ZD <r _J UJ zz t— o 1— 50M024 16 ��LU 03 CC t- d 1 rr o — CO CO 33 LU 1— CO X CO LU _J o LU or LU CD — LU > CC n: iC o ro 3= CJ s Q_ <r UJ h- cc cc CC Z 1— LU o LU hit; CC CO co — o <c LU I— —1 z: or CO d <_> — o - 3= CO cc LU s: o CO or LU CO CD I— 1— z: d CO LU CO >- CO u_ CO o Ll_ z — O o oo i— 1 LU CO CO t<r Ll. 1— — d LU — CO CL _J > cc LU ro cc LU CC o LU CC CO o 1— O CO CO LL_ d s — LU 1— Z CO z d d d o CO LU CC LU or I— ro > rr o d LU re OT • 33 re — CM o ic o LU or o Q d Q_ CO rn o o o CO —1 O CC — 1 — LU — 1— CL. >3= — X _J . u_ u_ O 1 1— Ll_ — _J — 1— Z —: Z o — Hd CC LU Q_ o ro u. CO LU LU S o 1— sc Q_ o d — \— <x z s O d LU LU LU X CO iC or o I— o CD cc _J d z Q_ _J 1— — Q. — CO 3E d 3: 22 50M02416 ��z 1 — ZD QZ CO 1— CO 2: LU z t— — QZ UJ t— u_ <1 I1 _i ID <t 1— • z Q <C UJ 2 QZ QZ — O ZD O O UJ UJ UJ zr oz CO t— u_ >- — _i — _J z CO S O 1— — CO zn ZD 1— 1— O z — oz UJ 3= — 21 0 QZ LL LL QZ UJ O UJ Q_ 1 f— X f— <Z UJ U- UJ — ZC CO <r -J CO <1 _l — zc UJ 3= 0 3£ ZZ3 21 CO CO H•c <t CO 2 z z 1 O O >- ctz <r CO CO UJ 0 UJ z • (— z UJ 2: >- 0 -J CO LLI Q CO z — 3= O z — — CD UJ 1— I— z zc c <c — 1— QZ 1— ZxZ UJ O Q- UJ O O 2 • 124 50M02416 �� 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 Tony O'Neil Apollo Telescope Mount 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 sdsp_skyl_000064 Title A name given to the resource "APOLLO TELESCOPE MOUNT SEQUENTIAL FLOW PLAN." Description An account of the resource This is a manual that describes the handling and use of the Apollo Telescope Mount prior to launch. 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 1968-09-23 Temporal Coverage Temporal characteristics of the resource. 1965-1970 Subject The topic of the resource George C. Marshall Space Flight Center Skylab Program Apollo applications program Apollo Telescope Mount Type The nature or genre of the resource Technical Manuals Text Source A related resource from which the described resource is derived Tony O'Neil Apollo Telescope Mount Collection Box 1, Folder 1 University of Alabama in Huntsville Archives and Special Collections, 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 Skylab Document Scanning Project Metadata Skylab 50th Anniversary https://digitalprojects.uah.edu/files/original/20/2328/spc_stnv_000100.pdf 0bb3df04da742c1b6310fc584bdc94e9 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 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 <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <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. 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. 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. 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_000100 Title A name given to the resource "Apollo Vehicle Propulsion Systems." Description An account of the resource This paper discusses the propulsion requirements for various stages of the Apollo vehicles and the development of these engines. Creator An entity primarily responsible for making the resource Belew, Leland F. Patterson, Wayne H. Thomas Jr., James W. Date A point or period of time associated with an event in the lifecycle of the resource 1965-07 Subject The topic of the resource Apollo project Liquid propellant rocket engines Liquid propellant rockets Project Apollo (U.S.) Saturn Project (U.S.) Space vehicles--Propulsion systems Spacecraft propulsion Source A related resource from which the described resource is derived Saturn V Collection Box 14, Folder 35 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_000075_000118 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17182 Alternative Title An alternative name for the resource. The distinction between titles and alternative titles is application-specific. AIAA Paper No. 65-303. Temporal Coverage Temporal characteristics of the resource. 1960-1969 Type The nature or genre of the resource Reports Still Image Text https://digitalprojects.uah.edu/files/original/20/2310/spc_stnv_000082.pdf eea852e0a0000be8cb2085e8bc07a9ab 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 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 <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <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. 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. 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. 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_000082 Title A name given to the resource "Apollo-LEM Docking Combined Probe and Drogue Assemblies Static Structural Test." Description An account of the resource This document contains the test technical report and results for the LEM docking probe and drogue assemblies to demonstrate that the assemblies would sustain enough load to capture latch. The document contains various graphs, diagrams, and images from testing. The final page contains a note that page no. A-139 is missing from the report. Creator An entity primarily responsible for making the resource North American Aviation, Incorporated. Structures Test Group of Laboratories and Test. Subject The topic of the resource Apollo lunar experiment module Loads (Mechanics) Measuring instruments Project Apollo (U.S.) Towed bodies Saturn Project (U.S.) Spacecraft docking Static tests Source A related resource from which the described resource is derived Saturn V Collection Box 20, Folder 43 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_000075_000118 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17626 Alternative Title An alternative name for the resource. The distinction between titles and alternative titles is application-specific. SID 67-317 TR 332077 CTR 02332077 Date A point or period of time associated with an event in the lifecycle of the resource 1967-03 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Type The nature or genre of the resource Reports Still Image Text https://digitalprojects.uah.edu/files/original/20/10719/pdf_040108104245.pdf efc376bc6d0edf5f4d0a8c258d5df120 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 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 <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <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. 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. 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. 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 pdf_040108104245.pdf spc_stnv_000594 Title A name given to the resource "Apollo/Saturn consolidated instrumentation plan for AS-204/LM-1." Description An account of the resource This report represents the consolidated instrumentation plan for employing optical and electronic data acquisition systems to monitor the performance and trajectory of the Apollo/Saturn 1B vehicle, AS-2 04/LM-1, during powered flight. Telemetry and electronic tracking equipment on board the vehicle, and data acquisition systems monitoring the flight are discussed. Flight safety instrumentation and vehicle data transmission are described, and geophysical information is provided. This plan reflects the general instrumentation coverage requirements set forth in the NASA Program Support Requirements Document (PSRD) for Apollo/Saturn 16, and the commitments of Eastern Test Range (ETR) Operations Directive (OD) No. 4206,dated 15 August 1967. This plan is not intended to conflict with or to supersede either document. The information presented in this document reflects planning concepts developed prior to October 1, 1967. Creator An entity primarily responsible for making the resource John F. Kennedy Space Center Date A point or period of time associated with an event in the lifecycle of the resource 1967-10-16 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Apollo project Astronautical instruments Optical instruments Saturn launch vehicles Lunar Module Saturn launch vehicles Type The nature or genre of the resource Instrumentation Plans Source A related resource from which the described resource is derived Saturn V Collection Box 23, Folder 54 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_000575_000599 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17744 https://digitalprojects.uah.edu/files/original/20/2312/spc_stnv_000084.pdf aa00eca1d9f698747a21f693d4d7b09b 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 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 <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <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. 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. 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. 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_000084 Title A name given to the resource "Apollo/Saturn Guide for the Preparation of Specifications: Volume I of II Volumes." Description An account of the resource According to the purpose found in section 1.1, "Volume I provides a guide for the preparation of specifications for existing equipment in the Apollo/Saturn Program." Creator An entity primarily responsible for making the resource National Aeronautics and Space Administration. Date A point or period of time associated with an event in the lifecycle of the resource 1967-05-01 Subject The topic of the resource Apollo spacecraft Project Apollo (U.S.) Project management Saturn launch vehicles--Specifications Saturn Project (U.S.) Specifications Source A related resource from which the described resource is derived Saturn V Collection Box 22, Folder 15 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_000075_000118 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17675 Alternative Title An alternative name for the resource. The distinction between titles and alternative titles is application-specific. K-AM-030/4 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Type The nature or genre of the resource Documents Text https://digitalprojects.uah.edu/files/original/20/2330/spc_stnv_000102.pdf 0d4cd607592865cd5a58335d929470c0 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 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 <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <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. 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. 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. 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_000102 Title A name given to the resource "Appendix to Chapter II of a Survey of Various Vehicle Systems for the Manned Lunar Landing Mission." Description An account of the resource This appendix includes various diagrams of orbital launch vehicles, graphs of propellant and tankweight, returnpayload, and lift-off requirements, velocity requirements for a manned lunar mission, multiple drawings for the Saturn C-3 vehicles, lunar mission payloads, information of vehicle size, and a summary of the Saturn C-3 lunar mission. Creator An entity primarily responsible for making the resource Ruppe, Harry O. Date A point or period of time associated with an event in the lifecycle of the resource 1961-06-10 Subject The topic of the resource Lunar landing Manned space flight Manned spacecraft Saturn Project (U.S.) Space vehicles--Design and construction 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 spc_stnv_000075_000118 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Type The nature or genre of the resource Documents Still Image Text https://digitalprojects.uah.edu/files/original/199/14390/sdsp_skyl_000055_001.pdf 696ad6a094f47e3b934bf3d9e5fa7221 PDF Text Text GEORGE C. HUNTSVILLE, ALABAMA APPENDIX TO SPENT STAGE EXPERIMENT SUPPORT MODULE PROPOSAL JUNE 1966 FOR NASA INTERNAL USE ONLY National Aeronautics and Space Administration MSFC - Form 454 (Revised September 1961) ��TABLE OF CONTENTS Page SECTION 1.0 INTRODUCTION 1-1 SECTION 2.0 DESIGN GROUND RULES 2-1 SECTION 3.0 MISSION SEQUENCE 3-1 SECTION 4.0 VIBRATION AND ACOUSTIC TESTING 4-1 SECTION 5.0 ELECTRICAL SYSTEM SCHEMATICS 5-1 SECTION 6.0 INSTRUMENTATION PROGRAM AND COMPONENTS 6-1 SECTION 7.0 HANDLING SEQUENCE (SSESM) 7-1 SECTION 8.0 MAINTENANCE CONCEPT 8-1 SECTION 9.0 TEST AND SIMULATION FACILITIES 9-1 SECTION 10.0 CREW FAMILIARIZATION PLAN 10-1 ��SECTION 1.0 INTRODUCTION This Appendix contains supplementary material on selected subjects which complements the MSFC Spent Stage Experiment Support Module (SSESM) Proposal. Presented are the design ground rules upon which the SSESM design is based, mission and mission task sequences, structural testing criteria, electrical system schematics, instrumentation equipment list and measurements, maintenance con cepts, handling procedures, and crew familiarization requirements. 1-1 ��SECTION Z. 0 Z. 1 DESIGN GROUND RULES MISSION DESIGN GROUND RULES Z. 1.1 General The Saturn IB Design Ground Rules, revision Z, R-P&VE-VAD-65-10 1, will apply except where specifically stated otherwise. a . Mission. - Mission objective of the S-IVB Spent Stage Experiment is to activate the AS-Z09 S-IVB LH2 tank into a large pressurized workshop in which astronauts can operate in a shirt-sleeve e n v i r o n m e n t f o r 4 h o u r s p e r 1 6 - h o u r p e r i o d f o r ZO d a y s . M i n i m u m change to the Saturn IB launch vehicle and Block II Command Service Module (CSM) and maximum use of developed and qualified subsystems, operational procedures and techniques should be employed whenever possible. A design objective is to retain a readiness and capability on the S-IVB stage and CSM for use on a standard Apollo mission. (1) Orbit Conditions. - It will be determined if CSM propulsion must be used for orbit circularization to meet the minimum mission duration. (Z) Experiment Definition. - The p r i m a r y experiment is the passivation and activation of the S-IVB spent stage into a workshop capable of supporting manned activity and the activation of the Spent Stage Experiment Support Module (SSESM) and associated support systems. A limited number of corollary experiments will be incorporated in the S-IVB Spent Stage Experiment. Experiment equipment will be stowed or installed inside and/or outside the SSESM during launch into orbit. (3) Orbital Operation (a) The transposition and docking maneuver will be accomplished after orbital confirmation and systems checkout. (b) The planned Apollo docking procedure will be followed which includes fold-out of the spacecraft Lunar Excursion Module (LEM) adapter panels to their normal 45-degree deployment position. It will be determined what the subsequent deployment will be. Z-l �(c) The S-IVB stage will stabilize and control its own attitude during the CSM transposing and docking maneuver. (d) The CSM will provide all stabilization and control required for the spacecraft after the transposing and docking maneuver is completed. (e) Attitude control of the spacecraft will be pro vided when required for experiment operation and thermal control of t h e w o r k s h o p . I t w i l l b e d e t e r m i n e d if o p e r a t i o n a l r e q u i r e m e n t s o t h e r than those stated dictate attitude control for the spacecraft for specified periods of operation. (f) Propulsion capabilities for the CSM for orbital abort will be maintained throughout the entire mission. (g) After transposing and docking, the CSM will provide all orbital guidance and earth communication. (h) Service Module (SM) propellant loading will be in accordance with mission requirements. (i) Preparation for activation of the workshop will be made after the transposing and docking maneuver and normal inflight checkout have been accomplished. (j) All equipment required for S-IVB LH2 tank habitation and experiment utilization will be carried external to the S-IVB LH2 tank at launch and assembled manually in orbit. (k) LH2 tank will be vented prior to astronaut egress from the air lock. (1) T h e S - I V B L H 2 t a n k w i l l b e m a d e r e a d y f o r occupancy by astronaut removal and storage of the LH2 tank dome hatch, followed by attachment of a stowed flexible pressure sealing boot between the aft end of the air lock and the LH2 tank dome hatch mounting surface. (m) LH2 tank passivation functions will be tele metered via the Instrument Unit (IU) for ground monitoring. 2 - 2 �(n) The LH2 interior tank wall will have a p r o tective coating to inhibit burning of insulation if the tank wall is penetrated by a micrometeoroid. (o) Titanium spheres located within the LH2 tank will either be removed or protective covers will be installed. b. Configuration. - The Saturn IB spent stage experiment launch vehicle will consist of an operational Saturn IB launch vehicle and air lock unit. The Saturn IB launch vehicle is composed of the S-IB stage, S-IVB stage, and IU. The first Saturn IB launch vehicle utilized will be AS-209. Modifications to the Saturn and Apollo hardware will be held to a minimum. Modification to AS-209 which could prevent the accomplishment of its primary mission a s an Apollo backup will not be permitted. Existing or off-the-shelf hardware will be used to mini mize cost, schedule, and development problems. S-IVB/IU subsystems which represent a potential hazard to the astronaut will be modified to provide a method(s) of passivation. Add-on type S-IVB subsystem passivation modifications will be installed at Kennedy Space Center (KSC). Subsystems to be investigated for passivation should include, but not be restricted to, the following: Electrical System, Hydraulic System, Stored Gases, Ordnance System, and Propellant. c. Interface Requirements. - MSFC will control the following interfaces in addition to the Saturn IB launch vehicle interfaces: Air lock to CSM, Air lock to S-IVB Stage, Air lock to IU, Air lock to SLA, Air lock to the Launch Complex, and Air lock to the Government Furnished Support Equipment. All interfaces will be controlled in accordance with the Interface Control Documents (ICD's) in the Apollo Intercenter Interface Control Document Log (1A01) and the Saturn Interface Control Document Log (1S0 1). 2-3 �2 . 1 . 2 Expe riments a. Experiment Integration. - MSFC will integrate experi ments and develop interface specifications. b. Weight. - The maximum weight of corollary experi ments and associated equipment will not exceed 1, 000 pounds. 2 . 1 . 3 Launch Facilities The Saturn IB Spent Stage Experiment launch vehicle will be capable of being launched from Launch Complexes (LC) 34 and 37B. 2 . 2 S-IB STAGE DESIGN GROUND RULES Configuration of the S-IB stage for the Saturn IB Orbital Workshop launch vehicle will be identical to the S-IB stage for the operational Saturn IB launch vehicle. 2. 3 S-IVB STAGE DESIGN GROUND RULES 2-3.1 General a. Configuration. - The S-IVB Orbital Workshop is an operational S-IVB/IB stage, with minor modifications to support the spent stage experiment. b. Interface Requirements (1) Interface Tooling. - The a i r lock flexible bellows adapter interface tooling (master mating gauge) will be manufactured by the S-IVB stage contractor. 2 . 3 . 2 Structure (Propellant Containers) a. The LH2 tank forward dome access opening will be enlarged to a 43-inch diameter. 4 2-4 �b. Provisions will be made for the storage of the LH2 tank forward access dome hatch. c. A hand valve will be provided in the LH2 tank forward dome hatch, or in the near vicinity, for manually venting hydrogen gas which is liberated from the LH2 tank insulation. d. The LH2 tank forward dome will have provisions to mate and make a pressure tight connection with the flexible bellows adapter. e. One hundred holes will be drilled and tapped at the intersections of the waffle pattern grids in the LH2 tank for the pur pose of mounting equipment and experiments. Work will be accomplished in accordance with MSFC SK10-8270. f. An atmosphere circulation blower system will be required within the LH2 tank. 2 . 3 . 3 Propulsion System (Propellant Evacuation) a. Venting of the LH2 tank will be accomplished by the nonpropulsive vent system. b. Method (s) to be employed to evacuate residual and flight performance reserve LOX will be determined. c. Existing controls will be modified to accomplish evacuating and/or venting of propellants. 2.3.4 Environmental Control System The environmental control system which is located on the air lock support structure will provide atmosphere supply to the workshop. 2 . 4 SSESM DESIGN GROUND RULES 2. 4. 1 General The SSESM is defined as an independent air lock unit which interconnects the CSM and the S-IVB LH2 tank and is mounted at the 2-5 �LEM attach points in the LEM adapter. The SSESM will include docking capability with the CSM and will provide environmental control system, electrical power, and life support to the S-IVB spent stage for the entire mission. The air lock and docking structure will not be connected to or transmit loads to the S-IVB stage hydrogen tank forward dome during powered flight of the launch vehicle. a. Configuration. - The SSESM will include an air lock, docking structure, environmental control system, electrical power system, and support equipment, as defined below. It will also include the support structure for these systems, expendables, and experiment stowage. The air lock will have the capability for independent and integrated operation with the CSM and S-IVB Workshop. b. Interface Requirements (1) Interface Tooling. - Manned Spacecraft Center (MSC) and/or the spacecraft contractor will provide the air lock/ space craft interface tooling. The S-IVB stage contractor will provide the air lock/S-IVB adapter interface tooling. (2) Field Splice Connecting Hardware. - MSFC will supply the connecting hardware for all air lock unit field splices. The interface hardware will be specified and documented in vehicle assembly documentation by the S-IB stage contractor. The hardware will be delivered to Cape Kennedy in compliance with the vehicle assembly schedule for AS-209. c. Alignment. - Air lock unit to S-IVB forward bulkhead alignment is not critical as the design of the flexible adapter will allow for minor misalignment. Internal alignment of the air lock unit compo nents will be controlled by an MSFC drawing "to be released. " This drawing will govern pertinent design documentation but will not be used for manufacturing, procurement of hardware, inspection of manufactured items or assembly. d. Reliability. - The reliability goal for the SSESM has not been established. 2-6 �e . Weights. - The maximum weight of the SSESM and corollary experiments is 10, 996 pounds. The control weight is presently established as 9, 000 pounds without the carry-on experiments. These weights are preliminary and will be revised. 2.4.2 Test Requirements The complete SSESM test item and subsystem will be functionally tested to verify the capability to meet the structural loads, natural and induced environments expected during mission lifetime. Human factor task tests will be performed to assure man/machine compatibility. Electrical power requirements during ground test operations will be provided from an external source. 2.4.3 Flight Mechanics a . Natural Environments. - Design of the SSESM will be based on applicable natural (space) environmental conditions, as given in NASA reports TMX-53273 and NASA TMX-53023. b. Induced Environments. - Design of the SSESM will be based on applicable induced environmental conditions, as given in MSFC Report IN-P&VE-S-63-1. 2.4.4 Structure a. General. - The operational air lock will provide minimum environment perturbation on the CSM, micrometeorite pro tection as great as CSM, even lighting distribution, local voice communi cations, and operational sensing equipment to all systems required for the operations of the workshop. The docking structure will make maxi mum use of existing CSM/LEM design and components. The a i r lock will be capable of accommodating two suited astronauts, and a locking through cycle will normally be done for two astronauts. The air lock will allow for astronaut suit donning and doffing. b. Emergency Facilities. - The air lock will provide for emergency occupancy by two astronauts independent of the CSM. c . Factors of Safety. - The following factors of safety are the minimum values to be applied. They are to be used in addition �to consideration of vibration magnification and shock given to surge phenomena, coupling between stages and propulsion system vibrations. Analytical investigations and test results will be used to validate the actual factors of safety of hydraulic and pneumatic systems. Safety factors different from those specified in the guide will require approval by the procuring agency. (1) General Structure Manned Vehicle Yield factor of safety Ultimate factor of safety s 1.10 = 1.40 (2) Hydraulic o r Pneumatic Systems Flexible hose, tubing, ducts, and fittings less than 11/2 inches in diameter. Proof pressure Burst pressure = 2.00 X limit pressure = 4.00 X limit pressure Flexible hose, tubing, ducts, and fittings 1 1/2 inches in diameter and greater. Proof pressure Burst pressure = 1. 50 X limit pressure = 2. 50 X limit pressure Actuating cylinders, valves, filters, switches. Proof pressure Burst pressure = 1. 50 X limit pressure = 2. 50 X limit pressure Reservoirs Proof pressure Yield pressure Burst pressure = 1. 50 X limit pressure = 1. 10 X limit pressure: 2. 00 X limit pressure d. Pimensions. - The cylindrical air lock will be nominally 65 inches in diameter and a minimum of 110 inches long (gross length). T h e l e n g t h m a y b e g r e a t e r t h a n 1 1 0 i n c h e s if n e c e s s a r y . 2-8 �e. Access. - The air lock will contain three hatches: Top hatch (Apollo command module exit) identical to LEM docking hatch. Side hatch (exit to LEM adapter area). Bottom hatch (entrance to S-IVB stage hydrogen tank) will be 48 inches in diameter. All equipment for the workshop will pass through the air lock. f. Docking Structure. - The top of the a i r lock and support structure will include a docking structure compatible with the Block II Apollo spacecraft and similar to the LEM docking adapter. The docking structure will be capable of carrying all loads induced by the SM propulsion system a s a result of orbit change maneuvers in addition to docking loads. g . Adapter (air lock/S-IVB). - Provisions will be made for a pres sure-tight connection to the S-IVB LH2 forward dome mounting surface after removal of the dome cover which provides a pressure environment for passage from the air lock to the hydrogen tank. h. Equipment Support and Storage. - The air lock support structure will be capable of supporting all experiment and support equipment as well as the air lock. Equipment to be used inside the S-IVB hydrogen tank during operation in orbit will be stowed on the air lock unit during launch. i. Umbilicals. - Two pressure suit loop umbilicals will be provided in the air lock. Umbilical length will be sufficient to allow the astronaut to move to the S-IVB common bulkhead. j. Lightning Protection. - The air lock unit will have the capability to receive and discharge lightning without damage to the vehicle. For additional information see Kennedy Space Center policy memorandum dated November 30, 1964. k. Electrostatic Compatibility. - It will be determined if a positive shorting system is required to make the air lock/docking mechanism and CSM compatible during docking maneuver. 2-9 �2 . 4 . 5 Propulsion System There is no propulsion system associated with the air lock unit. 2.4.6 Astrionic Systems a. Electrical System (1) Battery power will provide a maximum of ele c t rical power with an average of 750 watts for 4 hours/16-hour cycle for Environmental Control System (ECS), housekeeping, scientific purposes, and lighting requirements. (2) Provisions will be made for electrical and i n s t r u mentation support for activities inside the S-IVB LH2 tank. (3) General lighting requirements will be determined and provided for the air lock and the S-IYB LH2 tank. (4) Necessary electrical controls and displays of critical S-IVB spent stage parameters will be centralized on panels to be located within the air lock. b. Instrumentation System ( 1 ) B a s i c i n s t r u m e n t a t i o n w i ll a l l o w m o n i t o r i n g o f air lock environmental control system and housekeeping during pad checkout, ascent, and orbit. Basic system does not include visual coverage or data storage. (2) Telemetry will utilize existing IU antenna system. (3) System checkout and procedures will be compatible with present system. CSM. (4) Vehicle-to-ground voice communication will be by Local voice communication will be by spacecraft system. (5) Lighting requirements for television o r film cameras will be defined if the requirement exists. (6) It will be determined if monitoring of experiments i s required. 2-10 �2.4.7 Environmental Control System (ECS) Flight qualified Gemini, Saturn, or Apollo hardware components will be used whenever expedient. Refurbished flight components are acceptable. a. Function. - The environmental control system will provide atmosphere supply to the S-IVB LH2 tank and the air lock. b. Display. - ECS displays will be located in the air lock c. C o n t r o l s . •• and LH2 tank. (1) ECS controls for the a i r lock and LH2 tank will be located in the air lock. (2) The pressure in the a i r lock may be reduced to vacuum from the air lock or LH2 tank with the aft hatch closed. (3) Dump valves will be provided at the fore, aft, and side hatches of the air lock. (4) The a i r lock and LH2 tank pressures will have the capability of being equalized from the LH2 tank. (5) The a i r lock will have the capability of being pressurized or unpressurized manually. d. Atmosphere Requirements. - The ECS will be com posed of four 20-cubic-foot spheres of metabolic oxygen for pressurization of the LH2 tank and a i r lock and one 3. 5-cubic-foot LEM sphere for resupply of the Portable Life Support System (PLSS). The ECS will permit: (1) Two men to work in the LEM adapter, air lock, and S-IVB hydrogen tank areas for an average of 4 hours per 16-hour period for 20 days. (2) 1.25 charges of the stage hydrogen tank (approxi mately 10, 000 cubic feet) and for 30 pressurizations of the air lock. 2-11 �(3) Leakage rate will be approximately 30 pounds per (4) Fifteen hours of day. extravehicular activity by two men, or a total of 30 manhours. (5) Temperature: 6 5 + 25 ° F w i t h m i n i m a l t e m p e r a t u r e oscillation. (6) Pressure: 3. 5 to 5. 5 psia. (7) Relative humidity: 30-70 percent. (8) Carbon dioxide: 0. 1 psia. 2.4.8 Human Engineering The human engineering design principles presented in MSFC-STD-267A will be used. Criteria in this document will be used as guidelines, 2.4.9 GSE a. MSFC will provide all necessary electrical GSE. b. Maximum use will be made of existing Saturn IB launch complex facilities and equipment. c. Checkout will be conducted in accordance with MSFC document SR-QUAL-64-13, Space Vehicle Stage Analysis and Checkout Guidelines, dated May 1, 1964. d. System checkout equipment and procedures will be compatible with present systems. Systems must also conform to safety regulations of KSC operations. e. No new umbilical plates or swing arms will be permitted. f. Necessary controls and displays for critical parameters will be provided in the launch complex. 2-12 �2.4.10 Weight and Balance Prior to shipment to KSC, measurements will be made to determine weight and 3-axis center of gravity. 2.4.11 Crew Training Requirements Flight crew training will be provided for the activation of the SSESM, passivation/activation of the S-IVB LH2 tank and installation, and operation of the corollary experiments. 2. 5 INSTRUMENT UNIT DESIGN GROUND RULES 2. 5. 1 Configuration Modification of the IU to support the spent stage experi ments will be held to an absolute minimum. 2.6 CREW SYSTEM GROUND RULES The following crew systems criteria reflect astronaut requirements and limitations which have impact on hardware design and mission planning: a . The normal location of the crew when not engaged in S-IVB Workshop, extravehicular, or experimental tasks will be in the CM. b. The crew will be periodically rotated in their tasks during the mission. c. Two crewmen at a time will perform activities outside the CM. d. Pressure suits will be worn by the astronauts when entering a pressurized area for the first time. e. The pressure suit umbilical will not be disconnected in a vacuum on the AS-209 mission. f. Voice communications shall be maintained at all times between the task performers and the CM. 2-13 �g. One crew member shall remain within the CM.at all times except in an emergency. h. The astronauts will not require a maneuvering unit for activities within the Spacecraft LEMAdapter (SLA). A Portable Life Support System (PLSS) and tethers will be utilized for SLA activities. i. The crew will maintain two separate compartments at all times as a safety precaution. j. A 10-minute portable oxygen supply is provided each spac-e-suited astronaut. k. The normal eating, sleeping, personal hygiene, and other station-keeping tasks will be performed in the CM. 1. After the initial entry to a pressurized compartment, and the compartment is verified operational, subsequent entries to the pressurized compartment may be conducted in shirt sleeves. m. The Block II Apollo full pressure suit will be utilized. n. The water-cooled undergarment will be used for astronaut thermal control when the PLSS is required. Three of these will be stored in the air lock. o. The suit pressure will nominally be 3. 5 psi above ambient when the suit is pressurized. p. The nominal suit inlet temperature will be 50°F. q. The nominal suit atmosphere will be 100 percent 02. r. A thermal outergarment is required for all activities in vacuum. s . The optimum size access opening for astronaut transfer while wearing the PLSS and thermal outergarment is 38. 5 inches. t. The two PLSS units normally carried in the LEM will be stored in the air lock. A third PLSS is stowed in the CM. The PLSS will be used for emergency operations or as an alternate mode to the suit umbilical. 2-14 �u. Due to sizing, hygiene, and drying requirements, and to provide the astronaut with immediate access to a space pressure suit, three additional pressure suits will be provided. Two of the suits will be stored in the air lock. v. Tethers will be available for all activities outside the air lock. w. Two pressure suit umbilicals, in addition to those provided in the CM, are located in the air lock. The air lock suit umbilicals will reach all parts of the interior LH2 tank. x. A habitable environment is provided in the pressurized air lock with the following nominal atmospheric conditions: (1) 100 percent Oz (2) 5 psia (3) 70° F (4) 30-50 percent relative humidity y. The air lock has sufficient volume to accommodate two men, pressure suited and pressurized, and the storage of their equip ment. Each man can don and doff the pressure suit, thermal garment, and PLSS in the air lock. z. The air lock pressure will nominally be 5 psia 02 upon reaching orbit. aa. The air lock will be secured to the LH2 tank bulkhead opening during orbit by the astronauts. / bb. The air lock and LH2 tank atmospheric pressures may be equalized at any time from the air lock. cc. The air lock will provide access to the LH2 tank as well as the SLA. less tools. dd. The manhole cover bolts will be removed by reactionConventional tools will be available as backup. 2-15 �ee. The LH2 tank is vented prior to crew egress from the ff. T h e L.H 2 t a n k w i l l n o t b e p r e s s u r i z e d u n t i l a t t a c h m e n t CM. to air lock. • gg. The LH2 tank and air lock are at vacuum when the manhole cover is removed. hh. The LH2 tank and air lock atmosphere must be monitored whenever astronauts are present. Capability must be pro vided to monitor atmosphere both from the CM and locally to provide direct readout and redline alarm. The following must be measured constantly for shirt-sleeve operations: (1) COz Partial Pressure (2) T o t a l P r e s s u r e (3) T e m p e r a t u r e (4) Humidity ii. Vehicle attitude control may be required for thermal control inside the LH2 tank. 2-16 �SECTION 3.0 MISSION SEQUENCE 3. 1 GENERAL This section presents a general and detailed sequence for each event currently defined in the design reference mission. In addition, a typical crew time line summary is presented for the first few mission days. 3.2 GENERAL MISSION SEQUENCE Presented in Figures 3.2-1 through -6 are the initial releases of the S-IVB spent stage experiment design reference mission general sequence for use in analysis and planning. While this sequence is based upon the latest available conceptual design information, it is expected that subsequent design effort will dictate numerous changes to the sequence and provide more data for expanding the sequence to a more detailed level. These changes and additions will be reflected in subsequent releases as necessary to keep the sequence accurate and current during the course of this program. This design reference mission sequence covers the period from the initiation of launch vehicle countdown through the completion of the 20-day S-IVB spent stage experiment. Data presented herein are limited primarily to gross level vehicle/experiment peculiar sequence with such information as the launch vehicle normal countdown and flight sequences being referenced. 3. 3 DETAILED MISSION SEQUENCE Each event scheduled for days 1, 2, and 20 is sequenced in detail on Figures 3.3-1 through 3.3-26. This information supplements the summary presented in paragraph 3. 2. Additional events for days 3 through 19 will be defined as mission plans become better defined. 3. 4 CREW SCHEDULE SUMMARY Data are presented in Figures 3.4-1 and 3.4-2 which define a typical crew schedule for each mission day through five. Specific experiments have not been selected; therefore, only gross times were included in the schedule for experiment activity. The following data describe the assumptions and legend: �a. Astronauts sleep at same time, 7.5 hours/day - divided into two periods of 6 and 1 . 5 hours nap. Time between sleep varies from 6 and 10 hours. b. Two meals and one snack per day - 45 minutes per meal and 30 minutes per snack. c. A CSM check every 8 hours, + 1 hour. d. Periodic safety check by each astronaut each 12 hours. e . Two personal hygiene periods of 30 minutes each - one period after each sleep. f. For each 4-hour period (max) in tank, a period of 12 hours out is required. Two astronauts maximum in tank at one time. 3-2 �Prelauncl 1. FIGURE 3.2-1. - AS -209 DESIGN REFERENCE MISSION SEQUENCE Complete Manual Equipment Check 2. Install Airlock/Workshop Batteries 3. Checkout S age Pa3si< ation Capability 4. Airlock Purge and Leakchecl 5. Pressurize Airlock 6. '•ox Sphere Purge and Ueakcheck 7. Gox Sphere Prepressurizatic n ( i 50C p s i ) 8. Gox Sphere Pressurization (3000 psi) 9. Airlock/'A'orkshop Internal Power Mode on _i -14 -~0 -16 -l -8 -4 HOURS NOTE: I' o r a . y p i c a l d e t a i l e d S a t u r n I B c o u n t d o w n s e q u e n c e see MSFC drawing I )M3T0?. C LO �Li'toff thru S-TV13 "utoff j. . S-IB Ignition 2. Liftoff 3. S-IB Boost 4. S-IB Cutoff 5. S-IB/S-IVB Separation 6. S-IVB Ignition 7. S-IVB Boost 8. S-IVB Cutoff FIGURE 3.2-2. - AS-209 DESIGN REFERENCE MISSION SEQUENCE 10 MINUTES NO""E: I For a typical Saturn IB Flight sequence -see M S F C d r a w i n g I Q M 3 0 1 5 7 . �Day 1 1. S-IVB Engine Cutoff 2. Confirm Orbit Systems Check 3. LH2 Tank Venting 4. box Tank Passivation 5. Separate and Dock 6. CM Experiments 7. Withdraw Docking Probe 8. Enter Airlock and System Check Stage Passivation Airlock Area 10. Depressurize Airlock 11. Stage Passivation - SLA Area 12. Remove & Store Bulkhead 13. Connect Bellows 14. Pressurize Airlock 15. Return to CM I LP FIGURE 3.2-3. - AS-209 DESIGN REFERENCE MISSION SEQUENCE �Day 2 FIGURE 3.2-4. - AS-209 DESIGN REFERENCE MISSION SEQUENCE Enter A1 Depress Airlock Transfer and Install Equipme from Airlock Storage to Workshop Transfer and Install Equip ment from SLA to Workshop Workshop Experiments in Lnpressurized Atmosphere Workshop Pressuriz.ation Return to C'. i— 0 ours �Day 3 thru 19 FIGURE 3.2-5. - AS-209 DESIGN REFERENCE MISSION SEQUENCE A detailed sequence on Day 3 thru Day 19 will be generated when the detailed list of approved experiments becomes available. �Day 20 FIGURE 3.2-6. - AS-209 DESIGN REFERENCE MISSION SEQUENCE 1. Enter Workshop 2. Complete Workshop Experiment 3. Secure Equipment in Workshop 4. Transfer Experiment Containers to CM 5. Enter CM 6. Install Drogue Assembly 7. Install CM Hatches and System Check 8. Ready Earth Return T3D 15 30 45 Minutes 60 75 90 I 105 120 �Day 1 T—— Event 3 FIGURE 3 . 3 - 1 . - AS-209 DESIGN REFERENCE MISSION SEQUENCE — LH^ Tank Venting Hours �D.y 1 Evtr.r 4 F I G U R E 3.3-2. - AS-209 DESIGN REFERENCE MISSION SEQUENCE Man Sub-Eve nt LOX Tank Venting T h e m e t h o d of L O X t a n k p a s s i v a t i o n h a s n o t y e t been determined. Based on Recent proposals, however, it is assumed that passivation can be accomplished within a three to four hour time. v. u> •—< o »* • . ! f * t �Day 1 Even: 7 Sub-Eve nt OJ 1. Open CM Dump Valve 2. Remove CM Pressurization Hatch 3. Store CM Pressurization Hatch 4. Remove CM Thermal Hatch 5. Stow CM Thermal Hatch 6. Remove Docking Probe 7. Stow Docking Probe 8. Remove Drogue Assembly 9. Stow Drogue Assembly 10. FIGURE 3.3-3. - AS-209 DESIGN REFERENCE MISSION SEQUENCE Man Withdraw Docking Probe Secure Final Docking Latches 10 15 MINUTES 20 25 30 �D iy 1 Ev. r: 8 fIGURE 3.3-4. Sub-Event Man 1. O p e n A i r l o c k I n t e r l o c k Dump Va l v e 2 2. O p e n AL F o r w a r d H a t c h 2 3. Enter Airlock 2 3 4. D i s c o n n e c t CM S u i t U m b i l i c a l a n d C o n n e c t AL S u i t U m b i l i c a l 2 3 5. Communications Check 2 3 6. C l o s e CM P r e s s u r e H a t c h 1 7. C l o s e F o r w a r d AL P r e s s u r e H a t c h 3 8. C l o s e CM I n t e r l o c k Dump V a l v e 1 9. C l o s e AL I n t e r l o c k Dump V a l v e 3 Verify Operation Complete 1 2 3 10. AS-209 DESIGN REFERENCE MISSION SEQUENCE Enter Airlock and Systems Check — — — — r u> 1 •— rv d 2 4 6 8 MINUTES • • * 10 �D «> 1 Ev» • FIGURE 3.3-5. - AS-209 DESIGN REFERENCE MISSION SEQUENCE S u b - E v i nr 1. Activate Passivation Panel 2. Activate Switch to Vent Engine Start Bottle, Engine Pneumatic Bottle, Cold Helium Spheres 3. Activate Switch to Vent Stage Pneumatic Helium Bottle 4. A c t i v a t e S w i t c h t o V e n t APS Helium 5. Monitor Pressure Decay on a l l Bottles 6. P r e p a r e f o r EVA ( S u i t s , PLSS, e t c . ) Ma n STAGE PASSIVATION - AIRLOCK AREA oj i Trr "*T 25 Minutes 30 35 -40" �i) i\ 1 11 Evt FIGURE 3.3-6. - AS-209 DESIGN REFERENCE MISSION SEQUENCE Stage Passivation - SLA Area Man Sub E\ i nt 1. Open Airlock Side Hatch 2 2. Translate to SLA Area 2 3. Deactivate S&A Device 2 4. Check LH-, Pressure and Vent if Needed 2 5. Translate to Airlock and Enter 2 6. Close Airlock Side Door 1 wmmmm , O) i 0 •— * 2 • -< 1 4 6 8 MINUTES **- - » j ' 10 12 �Di v 1 Ever.: 12 FIGURE 3.3-7. - AS-209 DESIGN REFERENCE MISSION SEQUENCE Sub-Evi nt 1. Open Airlock Aft Hatch 2. Attach Lights 4. Remove Reactionless Tool from Storage 5. Loosen 72 Bolts 6. Stow Reactionless Tool 7. Remove Airlock Umbilical, Open Airlock Side Door and Translate to SIVB Forward Area 8. Remove Bolts and Place in Utility Bag 9. Remove Bulkhead and Slide out to number 3 10. Secure Bulkhead to Cable Rack 11. Return to Airlock and Connect Airlock Umbilical Man Remove and Store S-IVB Bulkhead Cover oj i w 10 20 30 MINUTES 40 50 60 �Day 1 E v » r.: 1 3 FIGURE 3. 3-8. - S u b -Evi nt 1. Release Bellows from Retainers and Allign at S-IVB Tank Opening 2. Thread 72 Bolts to Connect Bellows to Tank 3. Remove Reactionless Tool from Storage 4. Tighten Bolts 5. Store Reactionless Tool A S - 2 0 9 D E S I G N KEl- E K E N C E M I S S ! J N S E Q U E N C E Ma n Connect Bellows i »— 10 20 MINUTES 30 40 �• * Day 1 E v i ' r.r. 13 FIGURE 3.3-9. - Sub-Evi nt 1. Open Airlock Interlock Valve 2. Open CM Interlock Valve 3. Open Airlock Forward Pressure Hatch 4. Open and Stow CM Pressure Hatch 5. Pass CM Umbilicals into Airlock 6. Disconnect Airlock Umbilicals and Stow Connect CM Umbilicals 7. Enter CM 8. Close Airlock Forward Hatch 9. Check Interlock Valve Position 10. Install and Close CM Pressure Hatch 11. •— -J y Man * AS-209 DESIGN REFERENCE MISSUN SEOuKiMGF Return t o CM Check Interlock Valve Position *>• 10 MINUTES 12 �Day 2 Even: 1 FIGURE 3.3-10. - AS-209 DESIGN REFERENCE MISSION SFOUENCE Sub-Event 1. O p e n CM I n t e r l o c k Dump V a l v e 2 2. R e m o v e CM P r e s s u r e H a t c h 2 3. S t o r e CM P r e s s u r e H a t c h 1 4. Open Airlock Interlock Valve 2 5. Open Airlock Forward Hatch 2 6. Enter Airlock 2 3 7. Connect Airlock Suits Umbilical s 2 R e m o v e CM S u i t s U m b i l i c a l 3 8. Check Communications 9. I n s t a l l CM H a t c h — — — — — 1 2 3 1 10. Close Airlock Forward Pressure Hatch 3 11. C l o s e CM I n t e r l o c k Dump V a l v e 1 12. Enter Airlock Man MB MB M . r* f r Close Airlock Interlock Valve » 3-18 0 3 6 » 9 12 MINUTES a • • « • » 15 . �D iy 2 Evii 3 FIGLRE 3.3-11. - Sub-Evt nt 1. Install Temporary lights Ma n AS-209 L)ES.REFERENCE MISS.ON Sb'UuENCE T r a n s f e r and I n s t a l l E q u i p m e n t f r o m A i r l o c k S t o r a g e t o Workshop 2 3 2. Attach Tethers 2 3 3. T r a n s f e r and i n s t a l l H a n d h o l d s 2 3 4. Transfer and install Tool Kit 2 3 5. 6. 7. Transfer and install six Equipment Racks T r a n s f e r a n d i n s t a l l L i g h t s and Fixtures T r a n s f e r a n d i n s t a l l two F a n s 2 3 2 3 2 3 20 40 60 80 MINUTES oj •— vO NOTE: The events on this page are broken down into more detail in the following seven pages. 100 120 �D»y 2 Evi r: 3-1 F I G U R E 3 . 3 - 1 2 . - A S - 2 0 9 L»ES'. . . N R E F E R E N C E N E S S I J N S E O U ' E N C F Man Sub-Evi nt 1. Open Aft Airlock Hatch 2 2. Remove L i g h t B a n k F r o m A i r f l o w Storage 3 3. Enter Workshop 2 4. Transfer Light t o Workshop 3 5. C l a m p L i g h t t o LH„ T a n k F u e l Probe 2 Workshop Entry - I n s t a l l Temporary Lights — —i 0 5 MINUTES UJ tNJ o * f « �D.«, 2 Ever.: 3-2 F I G U R E 3 . 3 - 1 3 . - A S - 2 0 9 U E S ! ..M KEir E K E N C t : MESS. J N S F U G K N C K Sub-Event 1. Remove Tethers from Airlock Storage and Hand t o number 2 2. Attach Tethers to Probe 3. Enter Workshop 4. Attach Tethers t o S-IVB Aft 5. Attach Second Tether Attach Tethers Man 2 3 i— 12 0 MINUTES M r "" 15 �D-»y 2 Ev. r- 3.3 FIGURE 3. 3-14. - A S - 2 0 9 L>ES . W K E F E K E . V C E M I S S ! J N S F O u K N G F Transfer and Install Handholds Ma n Sub Evt nt 1. Enter Airlock (From Workshop) 3 2. Remove H a n d l o a d s f r o m A i r l o c k Storage and Transfer to number 2 3 3. Attach Handholds on Probe 2 4. Transfer and Permanently Attacl Handholds 2 u> — — \ i 0 2 1 4 MINUTES I 1 I 6 8 10 t\J (SJ > • • f « �D-iy 2 Evi r: 3-4 FIGURE 3.3-15. - AS-209 DESV.N KEr EKENCfc: M:SS; JN SKOOfWLf Sub-Evt nr 1. Remove Tool Kit From Airlock Storage and Transfer to number 2 2. Attach Tool Kit to Probe 3. Transfer t o Permanent Tool Kit Location and Install Man Transfer and Install Tool Kit 10 MINUTES W i IV OJ 6' �D ,y 2 E v f r.r ^-5 FIGURE 3. 3-16. - AS-209 DESIGN REFERENCE M.SS'.J N SKOO K NCF Transfer and I n s t a l l Six Equipment Racks Man Sub-Eve nr 1. Remove Equipment Racks from Airlock Storage and Transfer t o number 2 3 2. Attach each Rack t o Probe (Temporary) 2 3. Enter Airlock to Assist number 2 3 4. Install Racks - one at a time 2 3 — ^0 UJ • 10 20 30 MINUTES # • • �D ,y 2 E v . t.: 3 - 6 F I G U R E 3 . 3 - 1 7 . - A S - 2 0 9 L>ES~^N K E r i l K t N ' C K M I S S I O N S h ' O u K N L K Sab-Ev». nr 1. E n t e r A i r l o c k ( f r o m Workshop) 2. Remove L i g h t s a n d F i x t u r e s from Airlock Storage and hand t o number 2 - o n e a t a t i m e 3. Attach to Probe 4. E n t e r Workshop t o A s s i s t 5. Install Lights and Fixtures One a t a t i m e t o p e r m a n e n t location OJ tNJ Man Transfer and Install Lights and Fixtures 2 3 20 10 MINUTES 30 �D »y 2 Ev. • : 3-7 FIGURE 3. 3-18. - AS-209 UES'.'..N KEi E HENCE MISS1JN SE(jO EHCF Sub-Evi nt 1. Enter Airlock (from Workshop) 2. Remove F a n s f r o m A i r l o c k Storage and Transfer to number 2 3. Attach Fans to Probe 4. Enter Workshop t o Assist 5. Attach to Permanent Locations Man T r a n s f e r a n d I n s t a l l Two F a n s —k. oj i o 2 6 8 10 12 MINUTES J 14 �•Diy 2 E v i r.: 3-6 FIGURE 3.3-17. - AS-209 Sub-Evi nt 1. Man K E r E k r . V t K M^SSI J N S h ' U u K W L F T r a n s f e r a n d I n s t a l l L i g h t s and F i x t u r e s E n t e r A i r l o c k ( f r o m Workshop) Remove L i g h t s a n d F i x t u r e s from Airlock Storage and hand t o number 2 - o n e a t a t i m e 3. Attach to Probe 4. E n t e r Workshop t o A s s i s t 5. Install Lights and Fixtures One a t a t i m e t o p e r m a n e n t location OJ i M 2 3 20 10 MINUTES �Dxy 2 Ev,-- 3-7 F I G U R E 3 . 3 - 1 8 . - AS-209 DESI.-N REFERENCE MISSION SKUub'Wtt' Sub-Evx nt 1. Enter Airlock (from Workshop) 2. Remove Fans from Airlock Storage and Transfer to number 2 3. Attach Fans to Probe 4. Enter Workshop to Assist 5. Attach to Permanent Locations Man Transfer and Install Two Fans 2 3 —i. w i o 2 6 MINUTES 8 10 12 14 �D iy 2 Ev» ? 4 FIGURE 3. 3-19. - Sub Evi nr Man AS-209 UES .N KEr E KE.VCt; lMISS. JN Sb'UuKNCF Transfer and Install Equipment from SLA to Workshop Transfer and Install three Equipment Storage Assemblies (ESAs) Transfer and Install one Scientific Equipment Pod. 16 32 48 MINUTES u> ru -j NOTE: The events on this page are broken down into more detail on the following two pages. 64 80 �D i> 2 Ev* r . r 4-1 FIGURE 3.3-20. - AS-209 DES \.N KEr'EkENCK ivlISS. JN St'Uu t-'i-JC F Sub -Evi nt 1. Enter Airlock Man Transfer and Install Three Equipment Storage Assemblies (ESA's) 3 2 2. Disconnect Airlock Umbilicals 3. Open Airlock Side Door and Translate to SLA 4. Unlatch ESA and Transfer to Airlock Access Hatch 5. Attach Tethers to ESA (both ends) 6. Transfer ESA to Airlock (to Workshop Opening) 7. Enter Airlock 8. Enter Workshop and Translate to Point of EAS Attachment 9. Move ESA to Attachment Point V oo 3 2 3 2 3 10. Translate to ESA Attachment 11. Attach ESA to Probe (Permanent 2 3 12. Return to Airlock 2 3 13. Repeat 2 thru 11 twice for 2 ESA's 2 3 L- 0 10 20 30 MINUTES 40 50 60 �D.y 2 Ev> i 4-2 F I G U R E 3 . 3 - 2 1 . - A S - 2 0 9 D E S ! > N K E F E k E N G f c : M I S S .J N S F U u F H C F Sub-Evt nt 1. Enter Airlock 2. Enter SLA 3. Unlatch SEP and Transfer to Airlock Side Hatch 4. Attach Tethers •* Both Ends 5. Pass SEP into Airlock (to Workshop Opening) o>6. Man Transfer and Install One Scientific Equipment Pod (SEP) Enter Airlock -o 7. Enter Workshop - Move to SEP Attach Point 8. Move SEP to Attach point 2 3 9. 10. Enter Workshop and Move to SEP Attach Point Remove Equipment from POD 2 3 11. Install Equipment on racks 2 3 12 MINUTES 16 20 �O»y 20 Evi r: 3 FIGURE 3.3-22. - A S - 2 0 9 D E S T . N K E r r ' K c ' X C E M I SS I U N S E ( j u F H C F Man S e c u r e Equipment i n Workshop Sab-Evi nt 1. S e c u r e E q u i p m e n t i n Workshop Aft Area 2 3 2. T r a n s l a t e T o Workshop F o r w a r d Area 2 3 3. Secure Forward Area Equipment 2 3 4. Enter Airlock 2 3 5. Close Airlock Aft Hatch 3 • • • > 0 w w o « 5 1 10 • 15 20 —. 25 1 30 1 35 MINUTES f * , r• /• • • , 40 �D «y 2 0 Evi t 4 F I G U R E 3 . 3- 2 3 . - A S - 2 0 9 UES Sub-Evi nr 1. Open Forward Airlock Interlock Valve 2. Open CM Interlock Valve 3. Open Airlock Forward Pressure Hatch 4. Open CM Pressure Hatch and Stow 5. Remove CM Umbilicals from Storage and Pass into Airlock OJ 6. OJ Man .N KEIEKENOE MISS. J N St'OOEiMCE Transfer Equipment Containers to CM Connect CM Umbilicals 7. Disconnect Airlock Umbilicals and Store 8. Transfer Experiment Containers to CM 10 MINUTES 15 20 25 30 �D 20 E v i r: 5 FIGURE 3. 3-24. - AS-209 D Sub-Evi nt 1. Enter CM 2. Close Airlock Forward Pressure Hatch 3. Verify Interlock Valve Closed 4. Release Manual Docking Latches .N REFERENCE MISS1JN SEOUENCE Enter CM 10 MINUTES �Day 20 Evi r 6 FIGURE 3.3-25. - AS-209 DES1• >N KErERENCt MISS.GN Sh'UuKHCf' Sub -Evt nr 1. Remove Drogue Assembly from CM Storage 2. Install Drogue Assembly Man Install Drogue MINUTES �D a y 20 Event 7 FIGURE 3 .3 - 2 6 . - AS-209 DESIGN REFERENCE MISSION SEQUENCE Sub-Event 1. Remove CM Thermal Hatch from Storage 2. Install CM Thermal Hatch 3. Remove CM Pressure Hatch from Storage Man 4. Install CM Pressure Hatch 5. Disconnect Umbilicals and Stow 6. Remove PGA Suits 7. Review Tasks Preformed Checklist 1 u> Install CM Hatches and Systems Check 1 3 10 MINUTES 15 20 25 �F I G U R E DAY - C R E W S C H E D U L E 1 8 0 » 3 C«KirO-rj' T ( liTABi-ISH asrCS CCNf n*o Of pec i SLA r/tNfi S GKS'T * f f.-. SLEEP J < J ft l-.C. 5 • p " * . Aft i» p / . C % V »• srp&t ! SLEEP * V , A / V K ( *& •!' pfiSSII/PT/oN f V Hr. £XPMii?:£'VrS 5L • CP 1 ' L / 0 / 8 I u !M SltrP / ! Z * LAUNCH, DAY 3 . 4 - 1 . o \ j G| ip S,Lt£P » — V * P 2 8 c . '•ji 5 A / T T . 1 1 : . r I r - 8 I 1 V " T T T 1 1 t T ' -r T 1 1 T .. / V f NAP SLEEP SLEEP—— t 8 4 ' f ' 0 Aft 7 Aft ft 8 / 6 ' & /ft e SLEEP ' 5 A M p *C i HHP A F A' t i -NAP �FIGURE 3.4-2. - CREW SCHEDU ~ DAY DAY J �SECTION 4.0 4. I VIBRATION AND ACOUSTIC TESTING ACOUSTIC TEST PROCEDURES 4. 1. 1 Requirements Acoustic environmental qualification testing will be performed in a reverberation chamber. Requirements are outlined in Table 4. 1 -1. 4.1.2 Reverberation Chamber Testing a. The test chamber volume shall be such that the physical b u l k of t h e i t e m u n d e r t e s t w i l l n o t i n t e r f e r e w i t h t h e g e n e r a t i o n a n d maintenance of test conditions. b. The sound pressure field shall be measured with the test item or a suitable dummy mounted in the test chamber. Acoustic measurements shall be made in proximity to each major, dissimilar s u r f a c e of t h e t e s t s p e c i m e n . T h e o v e r a l l s o u n d p r e s s u r e l e v e l , reduced by six decibels, shall be introduced into the test chamber and adjusted to conform with the specified acoustic spectrum. The time required to conduct the survey shall be less than one-fourth of the specified test time, unless the specimen is replaced with a dummy. The sound pressure level and the survey time are reduced to avoid possible premature damage to the test item. The microphone shall be moved around the test item maintaining a distance of approximately 1 inches from the specimen. The measurements made within this volume shall then be averaged and the extreme values shall be noted. c. When (b) is accomplished, the sound pressure level shall be raised to the design specification value and the test shall commence. 4.1.3 Test Spectrum The acoustic test levels shall be those in the specification. 4.1.4 Test Duration Generally the test shall consist of a high-level exposure, immediately followed by a low-level exposure. Time durations for the high- and low-level exposures are given in the specification. 4-1 �TABLE 4. 1-1. - EXTERNAL AND INTERNAL ACOUSTIC SPECIFICATIONS External Sound Pressure Levels One-third Octave Band Geometric Mean Freq. (cps) 5.0 6. 3 8.0 10.0 12. 5 16.0 20. 0 25.0 31.5 40. 0 50. 0 63.0 Internal Sound Pressure Levels Low Level (dB) High Level (dB) Not Applicable o o oo o O o o o 100. 0 125. 0 160. 0 200. 0 250.0 315.0 400. 0 500. 0 630. 0 800.0 1000.0 1250.0 1600.0 2000.0 2500.0 3150.0 4000.0 5000.0 6300.0 8000.0 Overall Sound Pressure Level 4-2 Not Applicable High Level <dB) Low Level (dB) 106. 5 109.0 112. 5 115. 5 118. 0 121. 5 124. 5 127. 5 130. 5 133.0 136.0 139.0 139. 5 139. 5 140.0 140.0 140.0 140. 5 140. 5 141.0 138. 5 136. 5 135.0 134.0 133.0 131.0 129. 5 127.0 124. 5 121. 5 118.0 115.0 111.0 107. 5 100. 0 102. 5 106. 0 109. 0 111.5 115-5 118. 0 121.0 124. 0 126. 5 129. 5 132. 5 133.0 133. 0 133. 5 133- 5 133. 5 134. 0 134.0 134. 5 132.0 130. 0 128. 5 127. 5 126. 5 124. 5 123.0 120. 5 118. 0 115. 0 111.5 108. 5 104. 5 101.0 151.0 144.5 �TABLE 4.1-1.- Concluded STAGE: S-IVB MAJOR ZONE: 15, Station 1541 to Station 1663 - The portion of the S-IVB Stage lying between the plane of juncture of the LH^ container cylindrical section with the forward LH^ bulkhead and the plane of the field splice with the IU. One-Third Octave Band Acoustical Specifications in dB re 2 X 10 High Level 3.0 Minutes Low Level 15.0 Minutes Test Duration: N M �4.1.4 Tolerances a . The test time shall be within -0 to + 10 percent of the time set forth in the test specifications. b. For reverberation chamber testing, the overall sound pressure level and the individual one-third octave band, sound pressure levels shall be within -0 to +4 decibels of the levels set forth in the test specification with the test specimen installed. 4. 2 VIBRATION AND SHOCK CRITERIA 4. 2. 1 General Preliminary flight vibration and shock criteria for the S-IVB Spent Stage Experiment SSESM are presented below^ and in Figures 4.2-1 through 4.2-10. Vibration criteria are presented for (1) Saturn IB primary structure input to the SSESM assembly, and (2) primary unloaded SSESM structure. Detailed individual component vibration test specifications will be derived as required. 4. 2. 2 Air lock Assembly Shock and Vibration Criteria a. Sinusoidal Vibration Criteria (see Figure 4.2-1) 5 to 14 cps @ .044 In. Double Amp. Disp. 14 to 50 cps @ 0.44 g's peak 50 to 111 cps @ 0. 0034 In. Double Amp. Disp. 111 to 600 cps @ 2.2 g's peak 600 to 2000 cps @ -1 g's Peak/Octave 2000 cps @ 0.46 g's peak b. Random Vibration Criteria (see Figure 4.2-2).- Shall consist of three minutes of random noise over the frequency band 5 to 2000 cps at the following input levels: 5 cps @ 0.000204 g2/cps 5 to 35 cps @ 6 db/octave 35 to 400 cps @ 0.01 g2/cps 400 to 2000 cps @ -2 db/octave 2000 cps @ 0.00343 g2/cps Composite Level =3.5 Grmg 4-4 �c. Assembly Shock Criteria (1) Lift-off and separation shock pulse shall consist of a 10-g half sine wave for a duration of 10 milliseconds. (2) Docking shock pulse shall consist of a 20-g half sine w a v e f o r a d u r a t i o n of 1 0 m i l l i s e c o n d s . 4.2.3 SSESM Unloaded Structure Vibration Criteria a. Skin Panel Structure (1) Sinusoidal Vibration Criteria (a) Lift-off and mainstage sinusoidal vibration criteria (see Figure 4.2-3). b to 70 cps @ 0.03 In. Double Amp. Disp. 70 to 210 cps @7.5 g's peak 210 to 305 cps @ .0033 In. Double Amp. Disp. 305 to 500 cps @ 15.6 g's peak 500 to 2000 cps @ -6.45 g's peak/octave 2000 cps @2.7 g's peak (b) Mach 1 and Max Q sinusoidal vibration criteria (see Figure 4 . 2-4). 5 to 66 cps @ 0.0705 In. Double Amp. Disp. 6 6 t o 210 c p s @ 1 5 . 6 g ' s p e a k 210 to 305 cps @ 0.0069 In. Double Amp. Disp. 305 to 500 cps @ 33 g's peak 500 to 2000 cps @ -13.8 g's peak/octave 2000 cps @ 5.4 g's peak (2) Random Vibration Criteria (a) Lift-off and mainstage random vibration criteria ( s e e 1 i g u r e 4 . 2 - ) . - S h a l l c o n s i s t of 2 m i n u t e s o f r a n d o m n o i s e o v e r t h e frequency band 20 to 2000 cps at the following levels: 20 cps @ 0. 0023 g2/cps 20 to 63 cps @ 9 db/octave 63 cps @ 0.07 g2/cps 63 to 380 cps @3.4 db/octave 380 to 420 cps @ 0.54 g^/cps 4-5 �420 to 800 cps @ -3. 75 db/octave 800 cps @ 0.24 g2/cps 800 to 2000 cps @ -9 db/octave 2 0 0 0 c p s (30. 1 5 5 g 2 / c p s Composite Level =17.41 G rms (b) Mach 1 and Max Q random vibration criteria (see b igure 4. 2-6). - Shall consist of one minute of random noise over the frequency band 20 to 2000 cps at the following levels: 20 cps @ 0.01 g2/cps 20 to 63 cps @ 9 db/octave 63 cps @ 0.31 g2/cps 63 to 380 cps @3.4 db/octave 380 to 400 cps @2.4 g /cps 400 to 8i0 cps @ -3.5 db/octave 850 cps @1.0 g2/cps 850 to 2000 cps @ -1.5 db/octave 2000 cps @ 0.065 g2/cps Composite Level = 45.38 G rms (3) Shock Criteria. - The shock pulse shall consist of a 2 0 - g h a l f s i n e w a v e f o r a d u r a t i o n of 1 0 m i l l i s e c o n d s . b. Skin Stiffener Structure (1) Sinusoidal Vibration Criteria (a) Lift-off and mainstage sinusoidal vibration criteria (see Figure 4.2-7) 5 to 50 cps @ 0.0354 In. Double Amp. Disp. 50 to 158 cps @ 4. 5 g's peak 158 to 200 cps @ 0.00351 In. Double Amp. Disp. 200 to 500 cps @7.2 g's peak 500 to 2000 cps @ -2.4 g's peak/octave 2000 cps @ 2.4 g's peak (b) Mach 1 and Max Q sinusoidal vibration criteria (see Figure 4.2-8) 5 to 50 cps @ 0.075 In. Double Amp. Disp. 50 to 169 cps @9.6 g's peak 169 to 210 cps @ 0.0066 In. Double Amp. Disp. 210 to 500 cps @ 15 g's peak 500 to 2000 cps @ -4.8 g's peak/octave 2000 cps @5.4 g's peak 4-6 �(2) Random Vibration Criteria (a) Lift-off and mainstage random vibration c r i t e r i a ( s e e F i g u r e 4 . 2 - 9 ) . - S h a l l c o n s i s t of 2 m i n u t e s o f r a n d o m n o i s e over the frequency band 20 to 2000 cps at the following levels: 20 cps. @ 0.0008 g^/cps 20 to 72 cps @ 8 db/octave 72 cps @ 0.027 g^/cps 72 to 400 cps @2.8 db/octave 400 cps @ 0. 13 g2/cps 400 to 1000 cps @ -3 db/octave 1000 cps @ 0. 052 g2. cps 1000 to 1600 cps @ -10. 5 db/octave 1600 to 2000 cps @0.01 g^/cps Composite Level = 6. 76 G rms (b) Mach 1 and Max Q random vibration criteria (see Figure 4.2-10). - Shall consist of one minute of random noise over the frequency band 20 to 2000 cps at the following levels: 20 cps @ 0. 0035 g2/cps 20 to 70 cps @ 3 db/octave 70 cps @ 0. 12 g /cps 70 to 400 cps @ 2. 65 db/octave 400 cps @ 0. 56 g2/cps 400 to 1000 cps @ -2.8 db/octave 1000 cps @ 0.24 g^/cps 1000 to 1600 cps @ -10.8 db/octave 1600 to 2000 cps @ 0.044 g2/cps Composite Level = 10.85 G rms (3) Shock Criteria. - The shock pulse shall consist of a 20-g half sine wave for a duration of 10 milliseconds. * 4-7 �FIGURE 4. 2-1 AIRLOCK ASSEMBLY SINUSOIDAL FREQUENCY (CPS) * 7A TION ��FIGURE 4 . 2-3 SKIN PANEL STRUCTURE LIFT-OFF AND MAINSTAGE SINUSOIDAL VIBRATION CRITERIA loo /ooo FREQUENCY (cPs) �« S/K/N PANEL STRUCTURE MACH 1 AND MAX Q SINUSOIDAL VIBRATION CRITERIA FREQUENCY (cPs) �PANEL STRUCTURE m /LIFT-OFF £* :M W# AND MAINSTAGE RANDOM VIBRATION FREQUENCY CRITERIA (cPs) 9 �MACH / SKtN PANEL STRUCTURE AND MAX Q RANDOM VJBRAT/ON CRITERIA FREQUENCY (cPs) ��MACH I SX/M STtFFENER STRUCTURE AND MAX Q .SINUSOIDAL VIBRATION /ooo FREQUENCY (cps) �IOOO 0OOB FREQUENCY frs) �FIGURE 4. 2-10 MACH / SKIN ST/FFENER STRUCTURE AND MAX Q RANDOM V/BRATION CRITERIA /oo FREQUENCY fas') /ooo ��SECTION 5.0 ELECTRICAL SYSTEM SCHEMATICS Preliminary schematics are provided here to further define the design and electrical system interfaces as presented in the proposal document. Figures 5.0-1 and -2 define the cable interconnect diagram lor the entire electrical power system. Figures 5.0-3 through -19 are schematics outlining, in detail, interfaces of the electrical power distribution system. No provision has been included in this distribution system for corollary experiments. �Figure 5. 0-1 CM iN'lNfACl OMIT SUIT J2 BATTERY BATTERY NO 4 NOT TOSA7 70JA4 701 AlftLOCK OXYGEN HEATER NO I TOiAS INTER** SUIT OXTCEN HEATER NO 2 70IA4 Jl A. HLOCK 0*rt£H HC AT £P AlROX* LICHT 70«AS Jl 41 8ATT£«* NO 12 IO.NM2 BAT T tRY NO I 5 TONUS Jl BATTERY NO 21 70SA2I BATTERY NO IB 705AI9 SV RMER V*VL* ACCU.SHCN LICHT 70SA2S TOJA25 (SATC) (ARM J OS-70S FREUMNARY A|)H S-EB/V INTERTACC (PASSIVATION) sscsy . CABLE INTERCONNECTION Diagram 40M 3SS7I �jy JZ j* j* MCAS RACK THIS SH 602A7QI jy j2 MCAS RJCK 60?A70? Jl J? jy J-* J6 'y MULTlPuEXCR *2 JO MCAS RACK MCAS RACK 6O2A70S 60?A704 MCAS RACK 60? A70S J9 f y TM ASSY ASSY 60?A706 60?A707 J|l 60? A706 •703*14 F3RF ASSY 60?A709 S-IV6 STAGC UNIT «00 1 uCL TAN* EXP INTERFACE NOT OCClNCO TANK LIGHT NO I 400ASO TANK LIGHT BLOWER NO? 408ASI NO I 408AS? Jl Jl S-170 TANK blower no ? BLOWER NO 3 BlDwCR NO 4 OXYGEN HCAT£R 406AS6 408AS3 4O0AS4 408ASS NEUMINARY SSESM CABLE INTERCONNECTION Diagram # 40MJ557I �Figure 5. 0-3 • \.r - gplBlpiS - ***"| — [ —• j « SSESM ELECTRICAL SCHEMATICS «WR« ndlES WT PTVCNATKJF.S. I ft NQTTS C0*PC*F-T INO€*.POWR^OLF QL^LAT PAS'L PO»C« OCSOATlONS ARE N ACCORDANCE WITH IX IHT OVISJON OF IK SSESM IS SHOWN TO IKS SKIT I PARTIAL REFERENCE CCSOUTIOMS ARE SHOWN WKRE IK "W-SJTC LPATS. ASSEMBLIES. H*> SoOASVKA.CS ARE CWOENT FCFL CCMPLETE RE FT HENCE KWAIW PREFK WITH T»I ANO/OR ASSEKA.Y OCS)GNATCN ANO O.'-.PT AY PFLNF I P\>XFM P»-.THINNR>0^ REFERENCE TK LEFT OF QISIWOUTTON P<»*»P P<STB«INI»R»ON.RPMNIN ELECTRON MSFC-ST0-SA9 COMPQNfNr iNPf X CONTPQC Pflsfi 1 S-IVN VAF.F PFTSS VAIION SRV>Y TTLFVF FH» PQWTH P'.TTMK) HQN TFI R VT TNT tHY*l P C*STN.OTITIQN EACH MEASUREMENT IS OCNOTCO Br A' UEASLOEMENT (AAFFICR AS L6TC0 W IK WSTRVJMCNTATCN PROGRAM ANO COMPONENT LOT THIS NUMBER IS COMROSEO OF A LETTER ACICATING TK PARAMETER UEASUREO. ONE OB MORE OTLTS INDICATING TK SCO/ENCE Of EACH MEASUREMENT Of A PARAMETER A OAS- HUM OCR INOICATNC TK UNIT N WHICH TK MEASUREMENT ORIGINATES MFAS MAC* • O.-A/QL (*MAN*IL IS I-IQ MFA', PACK CO?A7Q, CMA'.NFTS M-?Q VFAS P.VK . J?AW? CMAVNM S I-10 TK PARAMETERS ARE A - ACCELERATION B- ACC0OSTCS MAT* «Q?A/Q» OW.NFIS >1-TO CCS PNTS'-UHF CESIGNATEO AS ANO . FOLLOWS". C- TEMPLHAIVRE CVCNT MCASCPTVTNTS 0- PRESSURE E- VIBRATION FLOW RATE CL*WCNT VQYTACF ASQ GVFNT MC - C- POSlTON H- CUOANCE B CONTROL J - «' t TELEMETRY K - SIGNAL • I. E - LOjiO LEVEL M- VOLTAGE. CURRENT B FREQUENCY N- MISCELLANEOUS R-"ANGULAR VELOCITY S- STRAIN R- RPM « CONTACTS OF CEKRAL PURPOSE RCUTRS ARE SHOWN WITH COO OC-CNCROZEO MACNETIC LATCH AEUW CONTACTS ARE SHOWN WITH CEILS 81-tt OR El-IB LAST EHRGUEO S • • • ASTERISK Sruea. OENOTES SHIELO TCRMPOJ1DN POUTS FOR DISTRIBUTORS ANO FOR CABLE SHCLOCO WRES UNLESS SHOWN ROVOUJLLF TERMINATED PREUMHMT NIL* �Figure 5. 0-4 MilC TcTxr.r foi.r S5Ei: « T O A'"4 �mUWNAW «.!»«• �MIT hOi row RATT. Ni2 703A2 RAM VI 3 703A3 RAM NO 5 703AS 70C.-N 703*>J1 RATI. NO 6 703AR BATT NO 7 703A7 BATT *0 6 703A8 R»TT. NO. 9 703A9 BATT NO K> 703A.0 70COM 70C0M 703W.J. 70C0V 703*U 703WW BATT NO 21 703A?I 70COM 703*<JI VO.TACC 0€T£CT0» NO I VOUAGC OCTCCTO* NO 2 . A2 •7030 •7DIO • 7030 • 7031 70C0M 70 OM 703*1/ 70COM 703*1J 70C0M '03*1/ 70C0M 70C0M 70CGM 703*UI ' BATT. *11} L-,I'H I H'M MTT. W I. | _'0i±'s_ 1— _L UI.J-J BATT. NO IS _ios« | BATT. NO 16 _J _ T22*'« L-w^J I BATT.NO.,' L_ '—<l'l— | _L H'!"— BAT'. NO. '8 | _1 BATT. NO. IB U|.|-J | 703*2 JL 1 BATT NO 20 | l_ tojmo J_ 703£l CFFCCHVT ON [ AS-209 SSCSU ELECTRICAL SCHEMATIC RO-Cfl OtSTSOOTON 40U5SS72 �Figure 5. 0-7 �•70V •701' •7050 «70'0 • 70 0 • 7050 «' •703O •70»O CB33 TOCOV 7C«"C"4 C«i5 C»i7t C«i9t CR20* 70 COM 70CCW TOCO* Jl AIRLOCK HCHT 701A 2 POt*OA LIGHT 703 A 51 TANK LIGHT HO I 400*30 TANK LIGHT HO ? 400*3* BLOWER HQ I 40«*3? BLO*C« HQ 2 400*33 8LO*'C R HO 3 400*34 tfElLWNAM QflCTivE <>n AS - 203 SSESU CLCCTRICAL <ri.» ItfiHf, 70»C» f-V" •»**«• 40V33372 �Figure 5. 0-9 �« Figure AS53 "Tf5 jf'i - _ . fr Pf I |*p. "?P.[ 3 S;tj: - *-V— AS-IGJ ,52 !? ^^ • C7, ptsh SI | * '-JV 4. I?! PLIX 701AG APT UMBILICAL APT UMBILICAL APT UMBILICAL APT UMBILICAL APT UM9IUCAL pjsn J AFLM « APT UM?-LlCAL - pi| «>|« PLUG 70*U 7C*C _ L ARM AMU PLUG ARM PLUG _J0.il 5.0-10 -4'_ 1 I J' «*"» ^ " A^ I JIJ, #• — j PI i — — T 'jv CM;PS!NCY sule-APO — T 1 > -1- H A~y *4I I— • 1!; P1 •i AOCOM «un/MT HYL'MV CLAPILO" ASS CAI? XLW I ±$$8. _l ! I APS I 0« TASK y.oi | APS I fuCL TANK ' J | APSI01 TINA | _«JLTNH*^AAsI1 L^-l^X. APS fUEL TANK —- — [C'EECTIVE ON | AS-2O» SSESU 'ELECTRICAL SCHEMATIC J J-BBSTACC 1 PA5SlVAT.CH SYSTEM 40USSST2 �Figure 5.0-11 • t �Figure 5.-0-12 EEC11 — 1 •ro»o est* 1 •Toy Y •TCO cnj 4TOO au TCOCCM DO COM J I--4 !S • M .L — JI AJQA4 j« Pi - - I a T05W2JI I 70CCAJ •h . U . _LL I "O _ A »2 c 4' j H » "~l MCAS RACX 602AT05 I 1 i r MCAS PACK 402AT04 • I • MfAS RACK GCZATui i PREUVJMARY J*II — ~W«. •>>! - E'fgCTivg "• SSCSM ON 1AS-20S n |S ELECTRICAL SCHEMATIC PO*»ER frSTRifcjTON V-ji 40Mjyw? �Figure 5.0-13 ' '3 ^\LT»U»cn ASS* *02 A 70* , 2 | / CHAN | ^ j CHAN 2 y / CHAN 3 r^A-J.-fc-^ -frlr-fo-* -fc-f.• r 1i '3 MU.Tir\.£UR ASS* A02A70* T Tf a F3 Wuv.TiPuC*CR ASS* 602A70* y CHAN 4 Is t'T" , MEASURING RACK A02A7C4 -CHAN 5 > CHAN * . CHAN 7 c ~ ' ~ J 1 - CI-703 -f—,-sU-L-j f f-jjU-u . ez-roj CJ-7CS . ' CI-TO, -J 1 1 J JL 64-701 . C%-701 1 — z T ~r i 1I Is ' I2 1 1 * 1 . pi ~ 1 1 - 70 H PRELIMINARY *» i > eu tOCClivC ON|AS-20+ SSCSM ELECTRICAL SCHEMATIC MCASuRisO RACK •02A70I CHANNELS l-O 40M35S72 �Figure 5.0-14 �'3 mw.TIJI.CBI* ASS* 602A704 UCASU*INC "AC* 60?A7Q2 Cham 5 CHAH 9 C»«AM 10 SSCSM ELECTRICAL SCHEMATIC VcAS^^.NC AACK tC2A702 CMAWCLS I-IO <0v»3SS72 \ �Figure 5.0-16 I J FI MULTLOLT»T ry MULiii»tCic« ASSF 402AP06 - H —I r .\n ~I MEASURING RACK 402A702 N T ¥ LL5 I f, II 2 1 1* J 1^ A TT JL — — CHAW 13— *_ *_ J « — CHAN 13 V' / — CHAN 20- CHAN 14- F 4 J - •r 1 ! 33 O OW 3 *?© ©y T " " i j Is 1 i _ j PRELIMINARY J»i>n CYKIIVC I — o« IAS-;OS SMSU ELCCTRLCAU SCHEMATIC MCASU**S RACK 402A702 CMANSLLS 11-10 >- mcsi I— II M i l C IIIIULL" »"«I CIIIII 4 0M 33*72 �rj I to?*'04 c*t* 'J WATPLC*£» 402*704 402*704 K3-I 706 COM TO»COM .4SOA7J, 0O-7C* preummaot *** crrccrivc on SSE5M I *wo* CLfCTHiCAL SCIICMATIC CCS rnis'-o«c MCASuNcucnrs 40V33372 ��Figure 5.0-19 �SECTION 6.0 INSTRUMENTATION PROGRAM AND COMPONENTS A listing of the measuring system hardware, composed of telemetry, measuring, and RF components, which are not associated with particular measurements is presented in Table 6.0-1. Also presented, in Tables 6.0-2 through -13 is the complete instrumentation program, which consists of measurements, telemetry channels, applicable measuring components, range, and other pertinent infor mation. 6-1 �INSTRUMENTATION PROGRAM 8c COMPONENTS PARAMETER L 1 N E MEAS. NR. Equipment VEHICLE SSESM PWG. NO MEASURIMIN! NAME AND RANGE OR FLT * INS TELEMETER OR COMPONENT PART NO PER POS ERR ENG CHANNEL Measuring Rack 703A404 50M12271 Measuring Rack 703A405 50M12271 Measuring Rack 703A406 50M12271 Measuring Rack 703A407 50M12271 Measuring Rack 703A408 50M12271 F 1 RF A s s y 7 0 3 A 4 0 1 50M12205 F 1 Tm A s s y 7 0 3 A 4 0 2 50M12206 F1 Multiplexer 703A403 50M12212 Tm C a l i b r a t o r A s s y 50M12416 TABLE 6.0-1 RES. PAGE F L T. c A L R E Q REMARKS 2 4 5 . 3 MC �INSTRUMENTATION PROGRAM 8c COMPONENTS PARAMETER MEAS Temperature NR. VEHICLE MEASUREMENT NAME AND OR COMPONENT RANGE OR FLT. PART NO. PER SSESM DWG. NO % INS. TELEMETER POS ENG. CHANNEL PAGE REMARKS ERR Cl-703 C2-703 C3-703 C4-701 Temp. Oxygen Storage Tank No. 1 Temp. Gauge DC Amplifier -125 to +100°C Temp. Oxygen Storage Tank No. 2 Temp. Gauge DC Amplifier -125 to +100°C Temp. Oxygen Storage Tank No. 3 Temp. Gauge DC Amplifier -125 to +100°C Temp. Reg. (8A) Inlet Temp. Gauge DC Amplifier -125 to +100°C EF3-X-01-01 12S 01 4) EF-X-01-02 12S 01 4) EF3-X-01-03 12S 01 4) EF3-X-01-04 12S 01 4) 5OM12400 5QM12400 50M12400 50M12400 TABLE 6.0-2 �PARAMETER MEAS C5-701 C6-408 C7-701 C8-408 C9-701 NR INSTRUMENTATION PROGRAM & COMPONENTS VEHICLE SSESM DWG. NO Temperature MEASUREMINl NAME AND RANGE OR OR COMPONENT PART NO Temp. Reg. (8A) Outlet Temp. Gauge DC Amplifier -125 to 70°C Temp. Valve (5c) Outlet Temp. Gauge DC Amplifier -75 to +4Q°C Temp. Suit Loop Supply Temp. Gauge DC Amplifier 5 to 15°C Temp. Reg. (9B) Inlet Temp. Gauge DC Amplifier -125 to +100°C Temp. Airlock Temp. Gauge DC Amplifier FLT PER INS. POS. |ENG. ERR PAGE TELEMETER REMARKS CHANNEL EF3-X-01-05 12S 01 EF3-X-01-06 12S 01 4) EF3-X-01-07 12S 01 4) EF3-X-01-08 12S 01 5) EF3-X-01-09 12S 01 4) 4) 50M12400 50M12400 50M12400 50M12400 -100 to +125°F 50M12400 TABLE 6.0-3 �INSTRUMENTATION PROGRAM 8c COMPONENTS r~ PARAMETER MEAS C10-703 Cll-703 C12-703 C13-703 C14-703 NR Temperature MEASUREMENT NAME AND OR COMPONENT Temp. Battery No. 1 Temp. Gauge DC Amplifier VEHICLE RANGE OR FLT. PART NO. PER SSESM PAGE DWG. NO % INS. TELEMETER POS ENG. CHANNEL REMARKS ERR 3 to 70°C EF3-X-01-10 12S 02 EF3-X-02-01 12S 02 EF3-X-02-02 12S 02 EF3-X-02-03 12S 02 ;F3-X-02-04 12S 02 50M12400 Temp. Battery No. 3 Temp. Gauge DC Amplifier 0 to 70°C Temp. Battery No. 5 Temp. Gauge pC Amplifier 0 to 70°C Temp. Battery No. 7 Temp. Gauge DC Amplifier 0 to 70°C Temp. Battery No. 9 Temp. Gauge DC Amplifier 0 to 70°C 50M12400 50M12400 50M12400 50M12400 TABLE 6.0-4 �INSTRUMENTATION PROGRAM & COMPONENTS PARAMETER L 1 N E MEAS. NR C15-703 C16-703 C17-703 C18-703 C19-703 C20-703 _ Temperature MEASUREMENT NAME AND OR COMPONENT RANGE OR PART NO. Temp. Battery No. 11 Temp. Gauge DC Amplifier 0 to 70°C Temp. Battery No. 13 Temp. Gauge DC Amplifier 0 to 70°C Temp. Battery No. 15 Temp. Gauge DC Amplifier 0 to 70°C Temp. Battery No. 17 Temp. Gauge DC Amplifier 0 to 70°C Temp. Battery No. 19 Temp. Gauge DC Amplifier 0 to 70°C Temp. Battery No. 21 Temp. Gauge DC Amplifier 0 to 70°C VEHICLE FLT PER % INS POS ENG ERR SSF.SM TELEMETER CHANNEL DWG PAGE NO RES. F L T C A L R E O EF3-X-02-05 12S Y 02 EF3-X-02-06 12S Y 02 EF3-X-02-07 12S Y 02 EF3-X-02-08 12S Y 02 EF3-X-02-09 12S Y 02 EF3-X-02-10 12S Y 02 50M12400 50M12400 50M12400 50M12400 50M12400 50M12400 TABLE 6. 0 - 5 t REMARKS �« I N S T R U M E N T A T I O N PROGRAM 8c COMPONENTS PARAMETER L 1 N MTAS. NR. Temperature MEASUR1MI N! NAME AND OR COMPONENT VEHICLE RANGE OR PART NO. FLT. PER SSESM % INS. POS ENG. DWG. NO RES. R E O EF3-X-05-02 12S Y 01 5) EF3-X-05-03 12S Y 01 5) EF3-X-05-04 12S Y 01 5) EF3-X-05-05 12S Y 01 5) EF3-X-05-06 12S Y 01 6) EF3-X-05-07 12S Y 01 6) EF3-X-05-08 12S Y 01 6) EF3-X-05-09 12S Y 01 6) TELEMETER CHANNEL ERR E C21-408 C22-408 C23-408 C24-408 C25-408 C26-408 C27-408 C28-408 T e m p LH2 T a n k , I n t Temp Gauge DC A m p l i f i e r 30 to 65°C T e m p LH2 T a n k , I n t Temp Gauge DC A m p l i f i e r 30 to 653C Temp LH2 T a n k , I n t Temp Gauge DC A m p l i f i e r Temp LH2 T a n k , I n t Temp Gauge DC A m p l i f i e r T e m p LH2 T a n k , I n t Temp Gauge DC A m p l i f i e r T e m p LH2 T a n k , I n t Temp Gauge DC A m p l i f i e r PAGE F L T C A L REMARKS 50M12400 50M12400 30 t o 65°C 50M12400 30 to 65°C 50M12400 30 to 65°C 50M12400 30 to 65°C 50M12400 T e m p LH2 T a n k , I n t Temp Gauge DC A m p l i f i e r 30 t o 65°C Temp LH2 T a n k , I n t Temp Gauge DC A m p l i f i e r 30 t o 65°C 50M12400 50M12400 1 xO o TABLE 6. �INSTRUMENTATION PROGRAM & COMPONENTS PARAMETER MEAS NR. Temperature VEHICLE MEASUREMENT NAME AND OR COMPONENT RANGE OR PART NO. FLT. PER «4 POS SSESM DWG. NO INS TELEMETER ENG CHANNEL PAGE REMARKS ERR C29-409 C30-409 T e m p LH2 T a n k , E x t Temp Gauge DC A m p l i f i e r -60 to 100°C Temp LH2 Tank Ext Temp Gauge DC A m p l i f i e r -60 to 100°C EF3-X-05-10 12S 01 6) EF3-X-06-01 12S 01 6) 50M12400 50M12400 TABLE 6.0-7 �I N S T R U M E N T A T I O N P R O G R A M 8c C O M P O N E N T S Pressure VEHICLE MEASURI.MI NT NAME AND OR COMPONENT RANGE OR PART NO. SSESM DWG. NO PAGE TELEMETER POS CHANNEL REMARKS ERR Pressure Oxygen Storage Tank No. I Press. Gauge 50M12344 Hardwire Display for preflight 4) 6) 50M12344 Hardwire Display for preflight 4)6) Pressure, Oxygen Storage Tank No. 3 Press. Gauge 50M12344 Hardwire Display for preflight 4)6) Inlet Pressure, Oxygen Supply System Press. Gauge 50M12344 Pressure, Oxygen Storage Tank No. 2 Press. Gauge D3-703 D4-701 TABLE 6..0-8 �INSTRUMENTATION PROGRAM & COMPONENTS PARAMETER L 1 N E MEAS. NR. Pressure VEHICLE MEASUREMENT NAME AND OR COMPONENT RANGE OR PART NO. INS. FLT. % PER POS ENG. ERR SSESM TELEMETER CHANNEL PAGE NO RES. F L T. C A L R E O REMARKS D5-701 Regulator (8A) Outlet Pressure Press Gauge 0 to 400 PSI EF3-X-03-05 12S Y 01 4) D6-701 Pressure, Suit Loop Supply Press Gauge 0 to 15 PSI EF3-X-03-06 12S Y 0 4) D7-701 Regulator (7A) Outlet Pressure Press Gauge 05 to 1500 PSI EF3-X-03-07 12S Y 0 4) D8-701 Airlock Pressure Press Gauge 0 to 20 PSI 50M10259 EF3-X-03-08 12S Y o: Hardwire Display for preflight 4) 5) 6) D9-408 P r e s s u r e , LH2 T a n k Press Gauge 0 to 10 PSI EF3-X-03-09 12S Y o; 4) 50M10262 TABLE 6.0-9 • r t 5) 6) �INSTRUMENTATION PROGRAM 8c COMPONENTS PARAMETER MEAS. NR. Pressure VEHICL MEASUREMENT NAME AND OR COMPONENT RANGE OR PART NO. FLT. PER * POS £SESM INS. ENG DWG. NO TELEMETER CHANNEL PAGE RES. REMARKS ERR D10-201 C02 P a r t i a l Pressure Airlock Gauge Assy 0 to .15 psi EF3-X-03-10 12S 01 4) 6) Dl1-408 C 0 2 P a r t i a l P r e s s u r e LH2 T a n k 0 to .15 psi EF3-X-04-01 12S 01 4) 5) TABLE 6.0-10 �INSTRUMENTATION PROGRAM 8c COMPONENTS PARAMETER L 1 N E MEAS. NR. F1-408 F^OW VEHICLE MEASUREMENT NAME AND OR COMPONENT F l o w - ECS F l o w m e t e r DC A m p l i f i e r RANGE OR PART NO. FLT. PER % POS ERR 0.2 to 3 lb/hr 50M12400 TABLE 6.0-11 INS. ENG. SSESM TELEMETER CHANNEL EF3-X-05-01 DWG. NO RES. 45 PAGE F L T. C A L Y R E Q 01 5) REMARKS �INSTRUMENTATION PROGRAM & COMPONENTS PARAMETER L 1 N E MEAS. NR. Signal VEHICLE MEASUREMENT NAME AND OR COMPONENT RANGE OR PART NO. FLT. * INS. PER POS ENG ERR SSESM TELEMETER CHANNEL PAGE . NO RES. F L T. C A L R E O Kl-701 Voltage Sensor No. 1 0 or 5 VDC EF3-X-04-02 12S Y 02 K2-701 Voltage Sensor No. 2 0 or 5 VDC EF3-X-04-03 12S Y 02 K6-701 Lights LH2 Tank 0 or 5 VDC EF3-X-05-05 12S Y 02 K7-701 Lights LH2 Tank 0 or 5 VDC EF3-X-05-06 12S Y 02 K8-701 Blowers On 0 or 5 VDC EF3-X-05-07 12S Y 02 K9-701 Oxygen Heater 701A6 0 or 5 VDC EF3-X-05-08 12S Y 02 K10-701 Oxygen Heater 701A7 On 0 or 5 VDC EF3-X-05-08 12S Y 02 Kll-701 Exterior Lights On 0 or 5 VDC EF3-X-05-09 12S Y 02 K12-701 Airlock Light On 0 or 5 VDC EF3-X-05-10 12S Y 02 On TABLE 6.0-12 REMARKS �INSTRUMENTATION PROGRAM 8c COMPONENTS PARAMETER MEAS. NR. Voltage, Current & Frequency VEHICLE RANGE OR MEASUREMENT NAME AND OR COMPONENT PART NO. FLT PER % INS. POS. ENG. ERR SSESM PAGE DWG. NO. TELEMETER CHANNEL REMARKS Ml-701 V o l t a g e Bus 7D10 0 t o 2 8 VDC EF3-X-04-04 12S 02 4) M2-701 V o l t a g e Bus 7D30 0 t o 2 8 VDC EF3-X-04-05 12S 02 4) M3-701 V o l t a g e B u s 7D30 0 t o 2 8 VDC EF3-X-04-06 12S 0 4) M4-701 C u r r e n t Bus 7D10 DC A m p l i f i e r 0 t o 1 2 0 Amps EF3-X-04-07 12S 0 4) M5-701 C u r r e n t B u s 7D30 DC A m p l i f i e r 0 to 2 4 Amps EF3-X-04-08 12S 02 4) 12S 02 4) 4) 12S 02 M6-701 C u r r e n t B u s 7D50 DC A m p l i f i e r 0 t o 1 2 0 Amps EF3-X-04-09 M7-701 V o l t a g e 5 VDC M e a s u r i n g Supply 0 t o 5 VDC EF3-X-04-10 T A B L E 6. 0 - 1 3 �SECTION 7.0 HANDLING SEQUENCE 7. 1 GENERAL This Section describes receiving the SSESM at KSC, checkout of SLA, SSESM installation in SLA, SLA and IU mating, and spacecraft mating and forward buildup. 7.2 RECEIVING OF SSESM AT KSC (Figures 7.2-1 through -3) 7. 2. 1 The SSESM is shipped from MSFC, Huntsville, to KSC. 7.2.2 The SSESM is transferred to Manned Spacecraft Operations Building (MSOB), MILA. 7. 2. 3 The SSESM is removed from the shipping container by: a. R e m o v a l o f u p p e r s e c t i o n of t h e c o n t a i n e r . b. Installation of handling ring on SSESM. c. Removal of all clamping devices on the SSESM, freeing i t f r o m t h e l o w e r s e c t i o n of t h e s h i p p i n g c o n t a i n e r . d. Using a hoisting sling and the crane facilities at MSOB. w 7-1 �F I G U R E 7 . 2 - 1 - A R R I V A L O F SSESM A T T H E T E S T A N D C H E C K O U T F A C I L I T I E S 7-2 �THE METEROID LHHLL H, I I TIC--EL IN 4 PLACES HOR CLA.V.P INSTALLATION HOISTING FIGURE 7.2-2 - METHOD OF HOISTING SSESM 7-3 I �HO SL AIRLOCK UNIT FIGURE 7.2-3 - REMOVAL OF SSESM FROM STORAGE CONTAINER 7-4 �7* 3 CHECKOUT OF SLA PRIOR TO SSESM INSTALLATION ( F i g u r e 7 . 3 - 1) 7. 3. 1 Receive SLA and install in the work stand at MSOB. 7.3.2 Perform inspection. 7.3.3 Install open items: a. Separation system b. Umbilical c. Associated wiring d. Instrumentation 7.3.4 Perform continuity check. 7. 3 . 5 D e m a t e S L A . 7.3.6 Transfer SLA upper section to the next station. 7-5 �FIGURE 7. 3-1 - SLA SEPARATED 7-6 �I 7.4 SSESM INSTALLATION IN SLA LOWER SECTION (Figures 7.4-1 through -3) 7.4. 1 Install SSESM in the SLA lower section. 7.4.Z Adjust the attachment fittings. 7.4.3 Verify the alignment. 7.4.4 Mate the electrical connectors and verify their compati bility. 7. 4. 5 Demate. 7.4.6 Transfer the SSESM to the next station. I f * 7-7 ��FIGURE 7.4-2 - SSESM AND LOWER SLA ASSEMBLY 7-9 �t �7. 5 SLA LOWER SECTION AND IU MATING FOR TEST AND CHECKOUT (Figure 7. 5-1) ~~ " 7. 5 . 1 Receive IU. 7. 5. 2 Mate SLA lower section to IU. 7. 5 . 3 P e r f o r m m e c h a n i c a l f i t c h e c k a n d v e r i f y m e c h a n i c a l alignment. 7.5.4 Perform electrical fit check. 7. 5 . 5 D e m a t e S L A f r o m I U . 7.5.6 Transfer IU and SLA lower section to the next station. 7. 5 . 7 N o t s h o w n : V e r i f i c a t i o n of C M / S L A m e c h a n i c a l c o m patibility and storage of SLA. 7-11 �F I G U R E 1 0 - i - L O W E R S L A M A T E D T O I U F O R T E S T AND C H E C K O U T {-Li �# 7. 6 SPACECRAFT MATE AND FORWARD BUILDUP (Figure 7.6-1 through -3) 7. 6 . 1 I n s t a l l c o m p l e t e S S E S M i n S L A l o w e r s e c t i o n . 7. 6 . 2 V e r i f y i n t e r f a c e a n d a l i g n m e n t . 7.6.3 Mate SLA upper section to SLA lower section. 7.6.4 Install internal access platform set. 7. 6 . 5 M e c h a n i c a l l y m a t e C S M t o S L A . 7.6.6 Verify CSM/SLA mechanical alignment. 7. 6 . 7 Electrically mate CSM to SLA. 7.6.8 Verify CSM/SLA electrical interfaces. 7.6.9 Buildup forward deck. 7. 6 . 1 0 I n s t a l l f o r w a r d h e a t s h i e l d . 7. 6 . 1 1 I n s t a l l o r d n a n c e d e v i c e s . 7.6. 12 Spacecraft transferred to Launch Complex (LC). 7-13 �AIRL^C UNIT LOWER SLA HANDLING RING F I G U R E ( . D - 1 - S S ES M I N S T A L L A T I O N I N L O W E R S L A P R I O R T O M A T I N G WITH THE FLIGHT VEHICLE 7-14 ��t-IC.LRE i . o - i - CM/SM/SLA/ SSESM MATING TO VEHICLE i - lo �SECTION 8.0 MAINTENANCE CONCEPT 8. 1 INTRODUCTION 8. I. 1 Purpose The maintenance concept for the SSESM is presented in this Section. It shall be used by MSFC and contractors when developing maintenance program plans to insure adequate maintenance for the SSESM. 8.1.2 Scope This concept applies to all orbital maintenance activities occurring on the SSESM system after docking takes place. 8.1.3 Objectives The principal objective of this maintenance concept is to provide a baseline for systematic maintenance planning for the SSESM logistics support. Systematic maintenance planning is required in order to accomplish the following: a. Increased equipment availability. b. Increased repair reliability. c. Increased safety for equipment and personnel. d. Reduced probability of human e r r o r . The above objectives are attained by achieving the following: a. Verified maintenance procedures and maintenance technical support data. b. Compatible man-machine relationships for successful completion of maintenance activities. c. of the SSESM. Adequate training for personnel to perform maintenance 8-1 �8.1.4 Concept Revisions This concept provides the preliminary maintenance program for all organizations performing logistics planning functions. As analysis and program definition proceed, this concept will be subject to additions, deletions, and modifications. These changes should be justified by appro priate technical or management studies. 8.1.5 Applicable Documents The following documents shall be used for reference to aid in the maintenance planning for the SSESM. In case of conflict between this document and the referenced documents, the referenced documents shall apply: Astronaut Training Plan (not released) Apollo Logistics Support Plan (NHB 7500. 1) SSESM Maintenance Plan (not released) 8. 2 BASIC CONCEPTS 8. 2. 1 Mission Concept The present mission concept requires that, in the event of a malfunction in any critical system, the mission will be aborted. It is the intent of this maintenance concept to extend the mission concept to permit an attempt to repair the system prior to issuing an order to abort. 8. 2. 2 Spares Concept A limited number of spare parts will be provided for inspace maintenance. Candidates for spares will be identified as the result of performance of a maintenance requirements a n a l y s i s . The actual spares to be transported with the SSESM will be determined from a detailed spare parts analysis. This spare parts analysis will consider, a s a m i n i m u m , t h e f o l l o w i n g : ( a ) R e l i a b i l i t y ; (l>) C r i t i c a l i t y ; ( c ) F e a s i b i l i t y ; (d) Weight Constraints. Spare parts will only be considered for support of the Environmental Control System (ECS). 8-2 �8.2.3 Maintenance Concept Maintenance on the SSESM will be performed by removing and replacing malfunctioned components. Disposal of defective components will be accomplished by stowing them in appropriate locations in the Spent Stage. No attempt will be made to return defective components to Earth. Structural repair will be considered, depending on development of adequate repair techniques. The maintenance requirements, tool requirements, astronaut training requirements, etc. , will be identified by a maintenance analysis (to be performed in accordance with NHB 7500. 1). Repair, in lieu of component replacement, will be considered if justification is provided by means of maintenance analysis or other trade studies. Components which a r e capable of being removed and replaced o r repaired will be identified in the SSESM maintenance plan (to be developed at a later date). Maintenance will be considered only on the SSESM Environ mental Control System (ECS) due to the high mission criticality of this system. 8. 3 TYPES OF MAINTENANCE 8.3.1 Preventive Maintenance (Scheduled Maintenance) Preventive maintenance is defined as any planned mainte nance action which is performed to maintain the system in a satisfactory operational condition. This consists, normally, of systematic inspections, servicing, and the detection and correction of incipient malfunctions before they occur or develop into major malfunctions. 8.3.2 Corrective Maintenance (Unscheduled Maintenance) Corrective maintenance is any maintenance action which is performed as the result of a failure and is performed in order to restore the equipment to satisfactory operational condition. 8. 4 MAINTENANCE LEVELS Levels of maintenance have been identified in order to categorize maintenance activities on a functional and location basis. Levels of maintenance for the S-IVB Workshop are described as follows: 8.4.1 First Level First-level maintenance includes all maintenance activities accomplished directly on system-installed hardware. This includes fault 8-3 �isolation, removal and replacement of components, servicing, replenishing, inspection, and repair-in-place activities performed on the Workshop whether it be in space or on the ground prior to launch. 8.4.2 Second Level Second-level maintenance includes all activities performed in direct support of first-level maintenance and involves disposition o r repair of hardware removed during first-level maintenance activities. In view of the philosophy discussed in paragraph 10. 2. 3, no second-level or lower-level maintenance will be required. 8. 5 MAINTENANCE STANDARDS Space maintenance activities demand the application of high quality standard maintenance proctices. Specifications must be developed which delineate in-space maintenance requirements to be met in regard to torque, cleanliness, bonding soldering, and lockwiring. Maintenance directives and procedures shall implement these specifications as applicable. 8-4 �SECTION 9.0 TEST AND SIMULATION FACILITIES 9. 1 GENERAL Substantial test facility capability exists at the MSFC with present and planned facilities. The applicability of the existing facilities to the development and test of a SSESM is discussed in this Section. 9.2 EXISTING FACILITIES To supplement the mechanically-induced vibration spectrum, use could be made of the recently-completed acoustical Test Position 116. This unique facility provides a clean acoustical environment which can subject the SSESM to a simulated acoustical spectrum equivalent to that encountered during CM detaching and docking maneuve rs. The structural integrity of the air lock and the docking structure could be verified by tethering both the assembled air lock and CM from the top of the 425-foot-high Saturn V Dynamic Test Stand. The extreme length of the suspension cables would induce negligible horizontal components and permit simulated in-space docking maneuvers. The Saturn V Dynamic Test Stand also houses the largest U.S. Low Gravity Test Facility. This facility could be utilized to verify the design and to establish in-flight fluid flow characteristics such as would be encountered by the environmental control and other gaseous or fluid systems. The CTL Area can accommodate component system development and verification tests involving hazardous propellants and high-pressure gases as employed by the slug environmental control system. In addition, newly and especially developed components, such as valves, regulators, switches, gauges, and heat exchangers, could be evaluated for system compatibility and response characteristics. The recently-completed Test Position 500 could be employed in the development of hazardous cryogenic handling, transfer, storage, and dumping techniques as would be encountered during orbital hydrogen tank blowdown, as well as facilitate the solution to inevitable unforseen problems which frequently occur in system design and development efforts. �The currently-functional GSE Area could be utilized in develop ment of SLA panel explosive removal techniques. The random motion devices could be employed to simulate the action of the S-IVB Workshop in a perturbed orbit while activating SLA panel deployment. In general, the aforementioned test facilities are but a few of those existing which could considerably benefit an austere in-house development of the SSESM. All of the test positions and areas a r e fully instrumented to sense and record the required design and test phenomena. As the program guidelines and operational requirements solidify, it is anticipated that other existing Test Laboratory facilities and component test positions can be used to greater advantage than presently envisioned. 9-2 �SECTION 10.0 10. 1 CREW FAMILIARIZATION PLAN GENERAL A description of a proposed Crew Familiarization Program for the S-IVB Workshop and spent stage experiments is presented in this Section. This plan will assure timely identification and integration of all familiarization resources and services necessary to insure adequate, timely, and economical familiarization support for the crew members. This plan shall be conducted within the guidelines and ground rules established for the overall astronaut familiarization program and shall be controlled and monitored by MSC. This plan conforms to NHB-7500. 1, Apollo Logistics Require ments Plan, November 1965; MSFC Logistics Support Requirements Plan, January 1966; and NPC 500.1, Apollo Configuration Management Manual, May 1964.. 10.2 FAMILIARIZATION CONCEPT 10.2.1 Description This familiarization concept is a proposed method of accomplishing crew familiarization for the S-IVB spent stage, the SSESM, and the experiments. This concept will assure the effective control and management required to identify, develop, provide, and maintain a familiarization program for the orbital workshop. All crew members will be trained in the deployment and use of air lock and workshop equipment, including equipment required in MSFC-developed experiments. Contingency time will be included throughout the familiarization program to allow for unexpected events or task difficulties. It is estimated that three or four months will be required for actual crew familiarization. This will cover five primary familiari zation areas and will be divided into four phases. 10-1 1 �10.2.2 Familiarization Areas The primary familiarization areas are as follows: a. Crew system equipment handling and operation. b. S-IVB Workshop activation and passivation procedures c. Experiment equipment transfer, operation, and data collection. d. S-IVB Workshop shutdown. e. Safety procedures and contingencies. 10.2.3 Familiarization Phase The program will be divided into the following phases: a. Orientation of mission requirements and subsystems capabilities. Astronaut/equipment interface will be defined and component functions will be introduced. b. Simulation of man-machine mission requirements to validate equipment locations and layout. c. Simulation of man-machine mission requirements incorporating recommended modifications. d. Total mission simulation; reduced gravity, high fidelity simulation of equipment and man-equipment functional requirements. After the orientation period, integrated mission simulation will be conducted in a Spent Stage functional mockup. Reduced gravity, vacuum, and atmospheric conditions to be encountered during the actual mission will be simulated where necessary. A con tinuous evaluation of the familiarization program will be conducted to determine that familiarization course objectives are met. 10-2 �10.2.4 Elements Required The elements required to identify, provide control of, and manage the familiarization program are the following: a. Familiarization Requirements Analysis. - A systematic familiarization requirements analysis will be made of the post docking to CSM-SSESM separation sequence of events, systems analysis, maintenance analysis, and experiment outputs to identify those crew member tasks that require familiarization and associated lamiliarization equipment. The familiarization requirements analysis will be made along the guidelines detailed in paragraph 10.3. The analysis will form the basis of the familiarization plans and familiari zation equipment specification. b. Familiarization Plans- -Familiarization plans will be developed to cover equipment and familiarization requirements identified in the familiarization requirements analysis. Each will be developed along the guidelines detailed in paragraph 10.4. A program plan will be developed that will give visibility to the total familiarization requirements and will indicate areas for cross-training and unscheduled redundancies. c* Implementation. - Some of the prime considerations during the implementation period are inter-Center schedule milestones, interface familiarization requirements, and mission requirements. MSFC will provide a technical coordinator to NASA Headquarters and MSC. d. Management. -MSC will provide the necessary program coordination and control to assure that the familiarization program covered herein meets MSC program milestones and standards. Necessary management control through directives, instructions, and procedures will be provided. Techniques such as PERT, EDS, con figuration management, etc., will be utilized for effective and econo mical management of the familiarization program. 10• 3 FAMILIARIZATION REQUIREMENTS ANALYSIS 10. 3. 1 Purpose The purpose of the familiarization requirements analysis is to identify specific familiarization requirements and 10-3 �familiarization equipment for the S-IVB Workshop mission- This analysis will be a systematic review of the SSESM experiments and their related operations and maintenance tasks. A part of this opera tions and maintenance analysis has already been accomplished. 10.3.2 Flight Equipment Analysis Flight equipment that requires crew familiarization for satisfactory operation will be identified and categorized in accordance with its mission criticality, complexity of operation, physical constraints imposed upon crew members, interface with other equipment, safety considerations, and contingencies. Expend able and recoverable equipment will be identified and their stowage procedures defined. 10. 3. 3 Task Analysis Tasks required to perform each normal/emergency operational function will be defined. A comprehensive and systematic review of the flight equipment and task analyses will be conducted to determine total task familiarization and individual task familiarization requirements. Specific task procedures will be defined. Estimates of time, in minutes, required to perform each task will be made. T h e s e estimates will be revised a t the end of the crew familiarization program to indicate a more realistic task time factor based upon simulated operation time. Each task will be identified to indicate its criticality to mission success, degradation of equipment, perceptual requirements, motor skill demands, judgmental requirements, and number of crew members required. 10.3.4 Familiarization Equipment and Facilities Analysis Familiarization equipment and facilities analyses will be made to determine requirements and availability dates. Selection and provisioning of familiarization equipment will be made based on this analysis. Before fabrication, familiarization equipment specifi cation will be prepared and approved for each familiarization equip ment end item. Appropriate configuration control procedures will be implemented to maintain familiarization equipment end item compati bility with the operational program equipment. 10-4 �10.3.5 Nature of Familiarization The most economical and effective methods of teaching will be used. Familiarization aids, components, operational equip ment, and simulators will be used for orientation and task-based familiarization. Orientation of mission requirements, subsystem capabilities and component functions is required to familiarize the crew members with tasks to be performed. Equipment built to actual operational system specifications and simulators will be used to develop exact unique skills and to meet specific familiarization objec tives. Existing operational equipment and simulators will be fully utilized. Familiarization facilities, as determined by the facilities analysis, will be provided. Extensive renovation will not be accom plished unless it is considered critical to the familiarization program mission. 10.3.6 Familiarization Outline A familiarization outline will be prepared from the familiarization requirements analysis data. The outline will define the courses, equipment, integrated resources, and services necessary for crew familiarization in each program phase as stated in para graph 10.2. This outline will provide a basis for the familiarization plans, and the estimated time required to complete each course. 10. 4 FAMILIARIZATION PLANS 10.4. 1 Purpose The familiarization plan will provide documented sources for identifying lesson plans, resources and controls to assure that familiarization requirements are met. 10.4.2 Course Description and Outline A course description and outline will be prepared from the familiarization outline data for each program phase (see para graph 10.2). It will contain the basic organization material and an itemized listing of each familiarization requirement, including the time clement required for familiarization. The data will contain information such as security classification, course objective and 10-6 �scope, course length in manhours, location of familiarization, familiarization methods to be used, required familiarization equip ment, and contingencies. The course description and outline data will be used to develop lesson plans. 10.4.3 Lesson Plans Lesson plans will be prepared for each program operation to define the familiarization accomplishments required for daily performance. In addition to operational and equipment procedures, the lesson plans will include contingencies, equipment relationships and interfaces, mission criticality, safety procedures, evaluation data, and conditions that would necessitate abort. Simul taneous crew participation at different work stations will be covered. 10.4.4 Schedules Schedules will be developed from the course descrip tion and outline, the latest Apollo Program schedules, and MSC astronaut familiarization schedule. They will contain provisioning data relative to familiarization equipment, facilities, lesson plans, instructors, and crew members. This part of the familiarization plan will give visibility to the total crew familiarization program and will clearly portray major familiarization milestones, critical familiarization events, schedule slippage or compromise provisioning inadequacies and current status. 10.4.5 Familiarization Evaluation A performance measurement system will be developed to assure an effective familiarization program and crew-system integration. MSC will evaluate the crew proficiency in relation to the familiarization course objectives. Approval of crew efficiency to successfully conduct mission operations will be the responsibility of MSC. 10-6 �10.5 IMPLEMENTATION The preparation for crew familiarization will consist of the following: a. A detailed preparation and presentation of data identified in the familiarization requirements analysis and familiarization plans. b. Design and fabrication of additional familiarization equipment defined in the familiarization requirements analysis. c. Utilization of equipment and facilities identified in the familiarization requirements analysis. d. An evaluation of knowledge and skills required to conduct crew familiarization. To assure crew proficiency, crew familiarization will be conducted using the course description and outline, lesson plans, familiarization equipment and facilities identified/developed in the technical requirements analysis and familiarization plan developed phases. NASA configuration management techniques will be used for familiarization equipment provisioning and control to assure that the equipment is current with flight hardware configuration and program schedules. A monthly status report will be submitted. In addition to the information required by the reporting procedures, the report will contain any problem encountered and the solution, schedule slippages with justification and recommended corrective action, and current status. Familiarization evaluation reports will be submitted by the instructor at the completion of each lesson. This report will contain lesson number and title, name of instructor, names of crew members participating, actual time required for course completion, evaluation of crew proficiency, degree of familiarization equipment efficiency, recommendations to improve lesson plan, and recommen dations concerning crew-system interfaces. 10-7 �10.6 FAMILIARIZATION MANAGEMENT The methods and procedures specified herein will provide assurance that the crew familiarization requirements for the S-IVB Spent Stage Experiment will be satisfied. It will assure that requirements are identified and satisfied in a manner and time frame permitting effective integration and control of this program with the MSC astronaut training program. Major milestones, program elements, and functional flow paths are shown in Figure 10.6-1. Each function is shown within its program element and is defined within the program element text shown for that function. Each function will be further defined and maintained during the life of the program. The documentation developed for each of the functions is shown in Figure 10.6-2. The documentation used will be structured to per mit common use in establishing the familiarization baselines and in performing program requirements. Documentation will be revised throughout the program to maintain familiarization and equipment current with program configuration and schedules. 10-8 �FIGURE 10.6-1 FAMILIARIZATION PLAN FLOW PATH FAMILIARIZATION EQUIPMENT FAMILIARIZATION PROVISIONING EQUIPMENT / SPECIFICATION MSC * 'FAMILIARIZATION \ I SCHEDULE 4 I \APOLLO PROGRAM ' SCHEDULE / I / OPS 4 MAINT ANALYSIS 4 EXPERIMENTS \ SSESM J COURSE FAMILIARIZATION FLIGHT DESCRIPTION EQUIPMENT » EQUIPMENT CREW FACILITIES ANALYSIS . / EVALUATION FAMILIARIZATION OUTLINE ANALYSIS FUNCTIONS TASK SCHEDULES ANALYSIS PROGRAM PROGRAM FAMILIARIZATION LESSON OUTLINE PLANS _ FAMILIARIZATION IMPLEMENTATION DEVELOPMENT (CREW FAMILIARIZATION!" FAMILIARIZATION ANALYSIS ELEMENTS _ « M W « « N T S V COMMENCE MILESTONES: OF DETERMINATION FAMILIARIZATION PROGRAM REQUIREMENTS COMMENCE FAMILIARIZATION PLANS DEVELOPMENT FAMILIARIZATION PLANS CREW APPROVAL AND PROFICIENCY IMPLEMENTATION OBTAINED �FIGURE 10.6-2 - FAMILIARIZATION FUNCTIONS AND RELATED DOCUMENTATION * DOCUMENTATION �� 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 Richard Heckman 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 sdsp_skyl_000055 Title A name given to the resource "APPENDIX TO SPENT STAGE EXPERIMENT SUPPORT MODULE PROPOSAL." 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 1966-06-01 Temporal Coverage Temporal characteristics of the resource. 1965-1970 Subject The topic of the resource George C. Marshall Space Flight Center Skylab Program Apollo applications program Spent Stage Workshop Saturn launch vehicles Experimentation Space habitats Airlock modules Multiple docking adapters Provisioning Onboard equipment Type The nature or genre of the resource Reports Text Source A related resource from which the described resource is derived Richard Heckman Collection Box 1, Folder 12 University of Alabama in Huntsville Archives and Special Collections, 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 Skylab Document Scanning Project Metadata Skylab 50th Anniversary https://digitalprojects.uah.edu/files/original/20/2331/spc_stnv_000103.pdf 8fd9b54f533bbebb57c0fa9081a909cf 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 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 <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <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. 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. 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. 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_000103 Title A name given to the resource "Application of Data to Design: Design of Space Vehicle Structures for Vibration and Acoustic Environments." Description An account of the resource According to the abstract, this paper discusses the need for a uniform design approach throughout the aerospace industry for space vehicle structural vibrations in order to keep pace with improvements in environment definition and testing. Creator An entity primarily responsible for making the resource Lifer, C. E. Date A point or period of time associated with an event in the lifecycle of the resource 1963-12 Subject The topic of the resource Saturn Project (U.S.) Space vehicles--Acoustic engineering Space vehicles--Design and construction Space vehicles--Vibration Source A related resource from which the described resource is derived Saturn V Collection Box 10, Folder 11 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_000075_000118 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. http://libarchstor.uah.edu:8081/repositories/2/archival_objects/16883 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Type The nature or genre of the resource Reports Text https://digitalprojects.uah.edu/files/original/20/2332/spc_stnv_000104.pdf 185f149d61703e718ad3b0c4c0796029 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 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 <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <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. 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. 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. 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_000104 Title A name given to the resource "Application of Nuclear Propulsion to the Mars Manned Landing Mission." Description An account of the resource This report has been prepared to provide Aerojet management and the interested NASA offices with nuclear propulsion decision aid data. The primary intent of these analyses is to evaluate potential space missions which may utilize nuclear propulsion in an effort to determine the most desirable characteristics of a nuclear propulsion system. Creator An entity primarily responsible for making the resource Advanced Concepts, Reon Division, Aerojet-General Corporation. Date A point or period of time associated with an event in the lifecycle of the resource 1967-03 Subject The topic of the resource Mars (Planet)--Exploration Nuclear rocket engines Saturn Project (U.S.) Spacecraft propulsion Space flight to Mars Source A related resource from which the described resource is derived Saturn V Collection Box 11, Folder 3 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_000075_000118 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. http://libarchstor.uah.edu:8081/repositories/2/archival_objects/16922 Alternative Title An alternative name for the resource. The distinction between titles and alternative titles is application-specific. REON Report RN-S-0068 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Type The nature or genre of the resource Reports Still Image Text https://digitalprojects.uah.edu/files/original/20/2334/spc_stnv_000106.pdf 26520a2d638b8d67636320a4697bfded 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 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 <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <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. 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. 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. 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_000106 Title A name given to the resource "Application of Saturn Systems to Orbit Launch Operations." Description An account of the resource Presented at the AIAA/AAS Stepping Stones to Mars Meeting, this paper compares the "payload velocity spectrum for existing and future missions" with Saturn V capabilities. Creator An entity primarily responsible for making the resource Sapp, T. P. Date A point or period of time associated with an event in the lifecycle of the resource 1966-03-28 Subject The topic of the resource Astronautics--United States Orbital launching Saturn launch vehicles Saturn Project (U.S.) Space exploration Technology utilization Source A related resource from which the described resource is derived Saturn V Collection Box 17, Folder 2 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_000075_000118 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. <a href="%E2%80%9Dhttp%3A//libarchstor.uah.edu:8081/repositories/2/archival_objects/17425%E2%80%9D">View item in ArchivesSpace</a> Temporal Coverage Temporal characteristics of the resource. 1960-1969 Type The nature or genre of the resource Reports Still Image Text Alternative Title An alternative name for the resource. The distinction between titles and alternative titles is application-specific. Douglas Paper No. 3431. https://digitalprojects.uah.edu/files/original/20/2333/spc_stnv_000105.pdf d6b7ecdf18d3344a543134527e06b80c 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 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 <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <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. 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. 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. 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_000105 Title A name given to the resource "Application of the Saturn V Launch Vehicle to Unmanned Scientific Exploration of the Solar System." Description An account of the resource According to the foreword, "This paper presents the results of a twelve-week mission and systems analysis of a combined Jupiter orbiter/solar probe mission utilizing the Saturn V launch vehicle." Creator An entity primarily responsible for making the resource Brown, B. G. Hill, A. S. MacKenzie, C. M. Odom, P. R. Thadani, M. C. Subject The topic of the resource Astronautics Saturn Project (U.S.) Saturn 5 launch vehicles Space probes Space vehicles Source A related resource from which the described resource is derived Saturn V Collection Box 19, Folder 7 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_000075_000118 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. <a href="http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17528"> View this item in ArchivesSpace</a> Alternative Title An alternative name for the resource. The distinction between titles and alternative titles is application-specific. Douglas Paper No. 3431 Date A point or period of time associated with an event in the lifecycle of the resource 1966-09 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Type The nature or genre of the resource Reports Still Image Text https://digitalprojects.uah.edu/files/original/20/2336/spc_stnv_000108.pdf b4721929f813ac70d2a24937dec724c6 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 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 <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <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. 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. 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. 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_000108 Title A name given to the resource "Approach in Achieving High Reliability for Saturn Class Vehicles." Description An account of the resource This paper focuses on an approach for achieving high reliability within the Navigation, Guidance, and Control systems of the Saturn class launch vehicles. Creator An entity primarily responsible for making the resource Rees, Eberhard Date A point or period of time associated with an event in the lifecycle of the resource 1967-03 Subject The topic of the resource Project Apollo (U.S.) Reliability engineering Saturn launch vehicles Saturn Project (U.S.) Spacecraft electronic equipment Spacecraft reliability Source A related resource from which the described resource is derived Saturn V Collection Box 21, Folder 5 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_000075_000118 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. <a href="%E2%80%9Dhttp%3A//libarchstor.uah.edu:8081/repositories/2/archival_objects/17632%E2%80%9D">View this item in ArchivesSpace</a> Temporal Coverage Temporal characteristics of the resource. 1960-1969 Type The nature or genre of the resource Reports Still image Text