381 20 8242 https://digitalprojects.uah.edu/files/original/68/1176/loc_jojr_000067_000070.pdf f7b17b5964ba2a37883d72436fa5defd PDF Text Text ���� Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context John Rison Jones Collection Title A name given to the resource John Rison Jones Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/56" target="_blank" rel="noreferrer noopener">View the John Rison Jones Collection finding aid in ArchivesSpace</a> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context loc_jojr_000067_000070 Title A name given to the resource Program from the 2006 Yom Hashoah Holocaust Remembrance Service held at Temple B'nai Sholom in Huntsville, Alabama. Description An account of the resource The program includes a short biographical sketch of John Rison Jones. Jones lit the seventh candle during the service and received the 7th Candle Award, presented by Margaret Anne Goldsmith. Creator An entity primarily responsible for making the resource Jewish Federation of Huntsville and North Alabama Date A point or period of time associated with an event in the lifecycle of the resource 2006-04-26 Temporal Coverage Temporal characteristics of the resource. 2000-2009 Subject The topic of the resource Jones, John Rison Holocaust Remembrance Day Holocaust, Jewish--1939-1945 Temple B'nai Sholom (Huntsville, Ala.) Huntsville (Ala.) Madison County (Ala.) Type The nature or genre of the resource Programs Text Source A related resource from which the described resource is derived John Rison Jones, Jr. Collection Box 1 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 loc_jojr_2019_11 https://digitalprojects.uah.edu/files/original/68/1175/loc_jojr_000063_000066.pdf 5d60ff6513c7daed264392f2291ae701 PDF Text Text ���� Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context John Rison Jones Collection Title A name given to the resource John Rison Jones Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/56" target="_blank" rel="noreferrer noopener">View the John Rison Jones Collection finding aid in ArchivesSpace</a> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context loc_jojr_000063_000066 Title A name given to the resource John Rison Jones' handwritten notes describing conditions at Dora-Mittelbau. Description An account of the resource Jones was one of the American soldiers who liberated the camp in April 1945. In these notes, he details the structure of the camp and its role as a "large industrial complex for the V-2 missile program." Jones also describes the conditions of the camp at the time of liberation. Creator An entity primarily responsible for making the resource Jones, John Rison Temporal Coverage Temporal characteristics of the resource. 2000-2009 Subject The topic of the resource Jones, John Rison Concentration camps--Germany Dora (Concentration camp) World War, 1939-1945--Concentration camps--Germany World War, 1939-1945--Concentration camps--Liberation Type The nature or genre of the resource Notes (documents) Text Source A related resource from which the described resource is derived John Rison Jones, Jr. Collection Box 1 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 loc_jojr_2019_11 https://digitalprojects.uah.edu/files/original/68/1174/loc_jojr_000062.pdf 8c79dfe33eb80c608f8bd833eb010ff1 PDF Text Text � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context John Rison Jones Collection Title A name given to the resource John Rison Jones Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/56" target="_blank" rel="noreferrer noopener">View the John Rison Jones Collection finding aid in ArchivesSpace</a> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context loc_jojr_000062 Title A name given to the resource 104th Timberwolves arriving at Staten Island, New York, Pier 16, on the S.S. <i>Monterey</i>. Creator An entity primarily responsible for making the resource Jones, John Rison Date A point or period of time associated with an event in the lifecycle of the resource 1945-07-11 Temporal Coverage Temporal characteristics of the resource. 1940-1949 Subject The topic of the resource Soldiers United States. Army. Infantry Division, 104th United States. Army--Demobilization World War, 1939-1945--Military personnel Staten Island (New York, N.Y.) Type The nature or genre of the resource Photographs Still Image Source A related resource from which the described resource is derived John Rison Jones, Jr. Collection Box 1 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 loc_jojr_2019_11 https://digitalprojects.uah.edu/files/original/68/1173/loc_jojr_000061.pdf 134ef2805560bbd8fa49ac29d0556020 PDF Text Text � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context John Rison Jones Collection Title A name given to the resource John Rison Jones Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/56" target="_blank" rel="noreferrer noopener">View the John Rison Jones Collection finding aid in ArchivesSpace</a> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context loc_jojr_000061 Title A name given to the resource 104th Timberwolves arriving at Staten Island, New York, Pier 16, on the S.S. <i>Monterey</i>. Creator An entity primarily responsible for making the resource Jones, John Rison Date A point or period of time associated with an event in the lifecycle of the resource 1945-07-11 Temporal Coverage Temporal characteristics of the resource. 1940-1949 Subject The topic of the resource Soldiers United States. Army. Infantry Division, 104th United States. Army--Demobilization World War, 1939-1945--Military personnel Staten Island (New York, N.Y.) Type The nature or genre of the resource Photographs Still Image Source A related resource from which the described resource is derived John Rison Jones, Jr. Collection Box 1 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 loc_jojr_2019_11 https://digitalprojects.uah.edu/files/original/68/1172/loc_jojr_000059_000060.pdf ab678970ed38b26f9b201a16203b4cdd PDF Text Text �� Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context John Rison Jones Collection Title A name given to the resource John Rison Jones Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/56" target="_blank" rel="noreferrer noopener">View the John Rison Jones Collection finding aid in ArchivesSpace</a> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context loc_jojr_000059_000060 Title A name given to the resource World War II safe conduct pass. Description An account of the resource The pass notes, "The German soldier who carries this safe conduct pass is using it as a sign of his genuine wish to give himself up. He is to be disarmed, to be well looked after, to receive food and medical attention as required, and to be removed from the danger zone as soon as possible." Creator An entity primarily responsible for making the resource Allied Expeditionary Force Date A point or period of time associated with an event in the lifecycle of the resource 1945 Temporal Coverage Temporal characteristics of the resource. 1940-1949 Subject The topic of the resource Military passes Safe-conducts World War, 1939-1945--Europe--End Type The nature or genre of the resource Military passes Text Source A related resource from which the described resource is derived John Rison Jones, Jr. Collection Box 1 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 loc_jojr_2019_11 https://digitalprojects.uah.edu/files/original/68/1171/loc_jojr_000052_000058.pdf 345afad9f6258d47c60bfc8d99faee31 PDF Text Text ������� Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context John Rison Jones Collection Title A name given to the resource John Rison Jones Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/56" target="_blank" rel="noreferrer noopener">View the John Rison Jones Collection finding aid in ArchivesSpace</a> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context loc_jojr_000052_000058 Title A name given to the resource Battalion history of the Third Battalion, 414th Infantry of the U.S. Army. Creator An entity primarily responsible for making the resource Third Battalion, 414th Infantry, United States Army Date A point or period of time associated with an event in the lifecycle of the resource 1945-05-15 Temporal Coverage Temporal characteristics of the resource. 1940-1949 Subject The topic of the resource United States. Army. Infantry Regiment, 414th Combat World War, 1939-1945--Campaigns--Europe Type The nature or genre of the resource Histories (literary works) Text Source A related resource from which the described resource is derived John Rison Jones, Jr. Collection Box 1 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource de en fr 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 loc_jojr_2019_11 https://digitalprojects.uah.edu/files/original/68/1170/loc_jojr_000050_000051.pdf ff2bacbbc2e8476d1281d1c5f8c4a46f PDF Text Text �� Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context John Rison Jones Collection Title A name given to the resource John Rison Jones Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/56" target="_blank" rel="noreferrer noopener">View the John Rison Jones Collection finding aid in ArchivesSpace</a> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context loc_jojr_000050_000051 Title A name given to the resource Letter from Lt. Gen. J. Lawton Collins commending the 104th Infantry "Timberwolf" Division for its role in capturing German territory at the end of World War II. Description An account of the resource The letter was forwarded to all members of the division by Maj. Gen. Terry Allen of the 104th Infantry Division. Collins chronicles the Timberwolves' accomplishments in campaigns in western Germany, including the capture of Cologne and the Ruhr region. Creator An entity primarily responsible for making the resource Allen, Terry de la Mesa, 1888-1969 Collins, J. Lawton Date A point or period of time associated with an event in the lifecycle of the resource 1945-06-01 Temporal Coverage Temporal characteristics of the resource. 1940-1949 Subject The topic of the resource Allen, Terry de la Mesa, 1888-1969 Collins, J. Lawton (Joseph Lawton) Combat United States. Army. Infantry Division, 104th World War, 1939-1945--Campaigns--Europe Type The nature or genre of the resource Correspondence Text Source A related resource from which the described resource is derived John Rison Jones, Jr. Collection Box 1 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 loc_jojr_2019_11 https://digitalprojects.uah.edu/files/original/68/1169/loc_jojr_000048_000049.pdf 454f3e8e19aead3403e475146f58d196 PDF Text Text �� Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context John Rison Jones Collection Title A name given to the resource John Rison Jones Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/56" target="_blank" rel="noreferrer noopener">View the John Rison Jones Collection finding aid in ArchivesSpace</a> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context loc_jojr_000048_000049 Title A name given to the resource Letter from Maj. Gen. Terry Allen to the 104th Infantry "Timberwolf" Division. Description An account of the resource In this letter, Allen describes the division's achievements in "six months of continuous combat," detailing its role in the liberation of the Netherlands and the capture of the Ruhr region and Cologne. Allen includes an excerpt from a letter from J. Lawton Collins. Creator An entity primarily responsible for making the resource Allen, Terry de la Mesa, 1888-1969 Date A point or period of time associated with an event in the lifecycle of the resource 1945-04-23 Temporal Coverage Temporal characteristics of the resource. 1940-1949 Subject The topic of the resource Allen, Terry de la Mesa, 1888-1969 Collins, J. Lawton (Joseph Lawton) Combat United States. Army. Infantry Division, 104th World War, 1939-1945--Campaigns--Europe Type The nature or genre of the resource Correspondence Text Source A related resource from which the described resource is derived John Rison Jones, Jr. Collection Box 1 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 loc_jojr_2019_11 https://digitalprojects.uah.edu/files/original/68/1168/loc_jojr_000045.pdf 5fff9f7f71ac6fc6356412f72fd8766d PDF Text Text � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context John Rison Jones Collection Title A name given to the resource John Rison Jones Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/56" target="_blank" rel="noreferrer noopener">View the John Rison Jones Collection finding aid in ArchivesSpace</a> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context loc_jojr_000045 Title A name given to the resource Certificate verifying John Rison Jones' return to the United States from France on the M.S. <i>John Ericsson</i>. Temporal Coverage Temporal characteristics of the resource. 1940-1949 Subject The topic of the resource Jones, John Rison Soldiers United States. Army. Infantry Division, 104th United States. Army--Demobilization World War, 1939-1945--Military personnel Type The nature or genre of the resource Certificates Text Source A related resource from which the described resource is derived John Rison Jones, Jr. Collection Box 1 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 loc_jojr_2019_11 Creator An entity primarily responsible for making the resource United States Lines Company https://digitalprojects.uah.edu/files/original/68/1167/loc_jojr_000044.pdf 2d00e92935c90215da1313a3635b3b78 PDF Text Text � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context John Rison Jones Collection Title A name given to the resource John Rison Jones Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/56" target="_blank" rel="noreferrer noopener">View the John Rison Jones Collection finding aid in ArchivesSpace</a> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context loc_jojr_000044 Title A name given to the resource "Paris Pass (Form #1)." Description An account of the resource This pass grants John Rison Jones 72 hours in Paris, France, in May 1945. Date A point or period of time associated with an event in the lifecycle of the resource 1945-05-12 Temporal Coverage Temporal characteristics of the resource. 1940-1949 Subject The topic of the resource Jones, John Rison Military passes United States. Army. Infantry Division, 104th World War, 1939-1945--Military personnel Paris (France) Type The nature or genre of the resource Military passes Text Source A related resource from which the described resource is derived John Rison Jones, Jr. Collection Box 1 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 loc_jojr_2019_11 Creator An entity primarily responsible for making the resource United States. Army. Infantry Regiment, 414th https://digitalprojects.uah.edu/files/original/68/1166/loc_jojr_000041_000043.pdf 30125f4847d49352a8012554a302ae94 PDF Text Text �� Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context John Rison Jones Collection Title A name given to the resource John Rison Jones Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/56" target="_blank" rel="noreferrer noopener">View the John Rison Jones Collection finding aid in ArchivesSpace</a> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context loc_jojr_000041_000043 Title A name given to the resource "Owner's Inventory with Certificates, Affidavits and Customs Declaration." Description An account of the resource This inventory details John Rison Jones' belongings that were shipped to Fort McPherson, Georgia, from Europe after World War II. The list includes clothing and equipment, including a camera with accessories, film, and postcards. Date A point or period of time associated with an event in the lifecycle of the resource 1945-06-20 Temporal Coverage Temporal characteristics of the resource. 1940-1949 Subject The topic of the resource Jones, John Rison United States. Army--Demobilization United States. Army. Infantry Division, 104th World War, 1939-1945--Military personnel Type The nature or genre of the resource Inventories Text Source A related resource from which the described resource is derived John Rison Jones, Jr. Collection Box 1 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 loc_jojr_2019_11 Creator An entity primarily responsible for making the resource United States. Army https://digitalprojects.uah.edu/files/original/68/1165/loc_jojr_000034_000040.pdf 4967800fcf2e6fc5913e023c7fccd135 PDF Text Text ������� Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context John Rison Jones Collection Title A name given to the resource John Rison Jones Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/56" target="_blank" rel="noreferrer noopener">View the John Rison Jones Collection finding aid in ArchivesSpace</a> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context loc_jojr_000034_000040 Title A name given to the resource "Soldier's Individual Pay Record." Description An account of the resource The booklet belonged to Private First Class John Rison Jones of Huntsville, Alabama. Date A point or period of time associated with an event in the lifecycle of the resource 1942-12-07 Temporal Coverage Temporal characteristics of the resource. 1940-1949 Subject The topic of the resource Jones, John Rison Soldiers United States. Army. Infantry Division, 104th World War, 1939-1945--Military personnel Type The nature or genre of the resource Wages Text Source A related resource from which the described resource is derived John Rison Jones, Jr. Collection Box 1 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 loc_jojr_2019_11 Creator An entity primarily responsible for making the resource United States. Army https://digitalprojects.uah.edu/files/original/68/1164/loc_jojr_000032_000033.pdf 9a49ca325e4c5307331d08cdd0773d89 PDF Text Text �� Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context John Rison Jones Collection Title A name given to the resource John Rison Jones Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/56" target="_blank" rel="noreferrer noopener">View the John Rison Jones Collection finding aid in ArchivesSpace</a> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context loc_jojr_000032_000033 Title A name given to the resource Roster of Alabama Polytechnic Institute student reservists called to World War II active duty. Description An account of the resource Alabama Polytechnic Institute is known today as Auburn University. The reservists listed were assigned to report to Fort Oglethorpe, Georgia; Camp Blanding, Florida; Camp Shelby, Mississippi; and Fort McPherson, Georgia for basic training. Creator An entity primarily responsible for making the resource United States. War Department Date A point or period of time associated with an event in the lifecycle of the resource 1943-06-19 Temporal Coverage Temporal characteristics of the resource. 1940-1949 Subject The topic of the resource Jones, John Rison Armed Forces--Reserves Auburn University (Ala.) Basic training (Military education) Soldiers United States. Army World War, 1939-1945--Military personnel Auburn (Ala.) Lee County (Ala.) Type The nature or genre of the resource Orders (military directives) Text Source A related resource from which the described resource is derived John Rison Jones, Jr. Collection Box 1 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 loc_jojr_2019_11 https://digitalprojects.uah.edu/files/original/68/1163/loc_jojr_000028_000031.pdf 7969602dd445c931041921639b273907 PDF Text Text �� Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context John Rison Jones Collection Title A name given to the resource John Rison Jones Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/56" target="_blank" rel="noreferrer noopener">View the John Rison Jones Collection finding aid in ArchivesSpace</a> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context loc_jojr_000028_000031 Title A name given to the resource Certified Copy of Army of the United States Honorable Discharge belonging to John Rison Jones. Description An account of the resource The form notes that Jones was a rifleman and "Expert &amp; Combat Infantry Man Sharpshooter." It also includes details of Jones' enlistment, qualifications, decorations, pay, and service dates and locations. Creator An entity primarily responsible for making the resource United States. Army Date A point or period of time associated with an event in the lifecycle of the resource 1946-08-31 Temporal Coverage Temporal characteristics of the resource. 1940-1949 Subject The topic of the resource Jones, John Rison Military discharge--United States Soldiers United States. Army. Infantry Division, 104th World War, 1939-1945--Military personnel Type The nature or genre of the resource Military discharges Text Source A related resource from which the described resource is derived John Rison Jones, Jr. Collection Box 1 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 loc_jojr_2019_11 https://digitalprojects.uah.edu/files/original/68/1162/loc_jojr_000007_000027.pdf d717f404ddf88ea0d9a4b222287a7768 PDF Text Text ��������������������� Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context John Rison Jones Collection Title A name given to the resource John Rison Jones Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/56" target="_blank" rel="noreferrer noopener">View the John Rison Jones Collection finding aid in ArchivesSpace</a> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context loc_jojr_000007_000027 Title A name given to the resource "104th Infantry Division Timberwolves." Description An account of the resource John Rison Jones of Huntsville, Alabama served with the Timberwolves. This pamphlet includes a combat history and photographs of the 104th Infantry Division during World War II. The inside front cover notes, "Passed by censor for mailing home." Temporal Coverage Temporal characteristics of the resource. 1940-1949 Subject The topic of the resource Soldiers United States. Army. Infantry Division, 104th World War, 1939-1945--Campaigns--Europe Type The nature or genre of the resource Pamphlets Still Image Text Source A related resource from which the described resource is derived John Rison Jones, Jr. Collection Box 1 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 loc_jojr_2019_11 Creator An entity primarily responsible for making the resource United States. Army. Infantry Division, 104th https://digitalprojects.uah.edu/files/original/20/1158/spc_stnv_000074.pdf 582f903466de2079bb829d2764795375 PDF Text Text APOLLO 6 PRE-LAUNCH PRESS CONFERENCE Cape Royal Mews Center, 'Cocoa Beach John F. Kennedy Space Center IJational Aeronautics and Space Administration Wednesday, April 3, 1968 Participants William C. Schneider, Apollo ~ i s s i b nDirector, NASA Geargo, M Low, Apol lo Spacecraft Manager ,i\IASA Clifford Charlesiyorth, Apollo 6 Flight Director, Manned Spacecraft Center, NASA Dr. Arthur Rudotpf~, Saturn V Proyrs.m Office, Mzushali Space Fli yht Center,NASA Rocco A. Pctrone, Apollo 6 Launch Director, l(cnnedy Space Center, NASA Cof. Royce Olson, USAF, Director DOD Lhnned Spacerlight Suppott Orfice, Patrick AFB Chris Kraft, Director of Fliai~tOperations, Manned Spaceciaft Center . �Mr. King: May I have your attention please? We're ready to proceed with the Apollo 6 prelaunch briefing at this time. I ' d l i k e t o cover a few logistics before we go into the actual conference here. W e ' l l be open a l l night tonight. The phone nunrber for any new arrivals who have not been with us before i s 783-7781. We'll have somebody on duty a l l night and through the morning hours leading up t o launch. You've a l l been accredited. You have your badges. You have the instructions you require to find your way out to the press site a t Launch Complex 3'9. You w i l l be able to take your own transportation out there. There w i l l be a guard who w i l l direct you to the parking lot which i s located right i n front of the press site itself. We request that you don't go up on the mound a t the press site, but bring your car into the parking lot i n front. W e ' l l start a commentary at about 2 a.m. tomorrow rnouning, rugning about every half hour until the crowd grows a l i t t l e larger. We w i l l be giving a complete commentary later i n the c o ~ l n t . The countdown commentary w i l l be handled from here until we clear thc tower a t l ifkoff a t which time it w i l l switch to the Manned Spacecraft Center i n tlouston, I n addition to your own transportation we w i l l have a bus departing here roughly on the hour, starting at r i i d n i ~ k t , with i t s last departure from the News Center at 5 : 3 0 a.m. tomorrow. You a l l might keep i n mind that i t ' s possible there could be some pretty good traffic i n the xrea as we get close to launct.1 time and it might behoove you a l l l o consider leaving early enough to notgget caught i n traffic a t the last minute. W e ' l l have a post-launch briefing at the press site at T plus 60 minutes. T h i s w i l l be followed by a second conference, a post-*mission briefing, which w i l l occur about ten hours after launch. This also will be a twoway conference, with participants from both the Kennedy Space Center and the PJlanned Spacecraft Center i n Houston. I ' d now like to introduce these gentlemen to you here, and one gentleman who i s also standing by for us at the PAanned Spacecraft Center i n I-louston. T h i s w i l l also be a two-way conference. We w i l l first take questions from here and then stvitch to your colleaqiies i n !-!ouston so that they will also have an opportunity to asl: questions. �To niy right, here at l<SC, Mr. George M. Low, viho i s Apollo Program Manager for the NASA Manned Spacecraft Center. Mext, Mr. \Nilliani Schneider, Office of Maniiecl Spaceflight, NASA Headquarters MrSchneider i s Apollo blission Director. Next Rocco Petrone, w l ~ oi s Director of Launch Operations for the Kennedy Space Center, and Launch Director for tlie Apollo 6 fligf~t. Next wc have Dr. Arthur Rudolph. Dr. Rudolph i s the Saturn V Progratn Manager from the Marsl~allSpace Fliglit Center. And Colonel Royce Olson, who i s Director of the Department of Defense F.4anned Spaceflight Support Office a t Patrick A i r Force Base. Also, standing by i n Houston, i s Mr. Cliff Charlesworth, who i s the 5 0 2 Flight Director, the Apollo 6 Flight Director for this mission at MSC. -- Mr. Kraft: I'd now like to turn it over to Mr. Schneider. Excuse me. I also understand, l'nl sorry Chris, we also have Mr. Chris Kraft, who i s Director of Fliglit Operations for the Manned Spacecraft Center, also standing by i n Houston. .Bill, would you take over please., Mr. Schneider: Good afternoon, ladies and gentlen~en. First I'd like to'apologize for the hour and a half delay. 1 assure you we were worlting and weren't just loafing. We have just completed oirr final review of the spacecrafi and tlie lairnch ve'l~icleand the entire comp!ex' as well as the netci~orkand the BOD forces, and we've conipleted our review of the weather, and everything i s at this time GO!. . The weather situation, as reported to 11sby the ESSA people, i s basically that early i n the morning the weather w i l l be much like this, as it i s out here today, that is, with clear and gentle winds, with deterio:ating conditions toward the afternoon, with ar. expected wind velocity reaching as rnuch as a peak of 25 knots sonletirnc later i n tlie day. But v ~ eare on scttediile aild moving out for an 0700 launch tomorrow morning, that's 0 7 0 0 Eastern Standard. The close of the window for tomorrow w i l l be dependent upon ille conditior?~ i n the recovery zone. VIe have set a requirerr~entthat t f con:litions ~ in thc recovery zone be such that the onsite commander can give us reasona!)ie assurance that he w i l l be able to successfully vecover the spacecraft. Vie expecl the close of that window to be, i f contlitions arc very good, on t t ~ c order of noon cr 1230 EST. �T h i s is, of course, the final qualification flight on the Saturn V launch vehicle, since we have previously qualified the command and service modules and the lunar module for manned flight i n previous missions. We are looking forward to having a goocl la~lnchvehicle flight, and as a niatter of fact, a good spacecraft flight, too, George, but as I said, the spacecraft objectives are on this tnission, secondary. It i s even conceivable that, and I stress the word conceivable, that the mission may have accomplished a l l of i t s primary mission objectives at the time of insertion into orbit, although, of course, that couldn't be determined for quite a long time. We do have one, I shall not call it a dark cloud, but one question mark, and this i s the question that kept us out at the Launch Control Center for the past couple hours. That i s the question of a temperature that we experienced during the Countdown Demonstration Test on the S-Il stage J-2 engines where some of the propellant pump discharge temperatures were a few degrees above what we call our redlinc values, that i s the values that we expect to achieve for launch. We have taken some corrective action and we have examined it. We think we've solved the problem. We have reaso~ablehope that we've solved the problem. However, there i s no way to test whether we w i l l achieve the proper redline withoui going through a cryogenic test and so the cryogenic test i s going to be i n the morning. If, for example, we do not achieve this proper temperature on the first cycle we w i l l be forced to do what we did during the CDDT, and that is, namely, cut off, stop at about 22 seconds 0: thereabouts and recycle back t o about 24 minutes, then wait and assess the problem and see whether or not we can stabilize conditions again, and try again. Wopefully that w i l l not happen, but it i s a very distinct possibility. With that, I'd like to turn it over to Rocco and ask Col. Petronit i f he would now give LIS a discussion of how things have been going out at the Cape. �Mr. Petrone: Well, we have been busy, as yo11 know. We finished our Countdown Demonstration Sunday, then we had to recycle for the count and also work our way throtrgh.sorne of the things we found i n the Countdown Demonstration, but we succeeded in picking up the count at one o'clock this morning. We have a final 24hour terminal count which we picked up at one, and at the time as of now, I understand the count is on . we left tliere schedule. We plan a hold at the eight-hour mark, T minus eight hours. We plan a hold of six hours. We have no scheduled work and at this time it does not appear that there will be any necessary within that hold; We zre on schedule with a!l of our checks, everything is going fine. So, roughly at 1700, in another hour and fifteen minutes, we w i l l complete our task on schedule, We w i l l have a six-hour hold and pick up again at 11o'clock tonight for the Final portion of the count of eight hours to a seven o'clock l iftoff. -- -- A t 10:30 p,m. we w i l l have a look at the weather to see i f the situation has changed. Right now, the forecast would indicate tfiat our niort~ingtime is the best time to go, that is Thursday morning. We w i l l take a look at the weather at lO:30, then commit at 1 1 : 0 0 p.m., that is EST, at T rnitius eight in our count for the launcli. A t T minus seven hours vie stait our cryogenic tanking and shortly theuezfter we will stati getting cryogenics into the stage. Up until T minus eight hours vJe can s i t there and . recycle on a 24-hour basis. I f we dccidc not to pick up the count a t 13.:00, and assuming we had no prob!er?i causir~g11s to go i n and change something, we could s i t there and hold,, 'vV~can do that through Saturday as tve now see it. We could wait through Thursday, Friday and Saturday on our latrnch attempts, asstlining far. some reason 'at T minus eight Iiouus we do not want to pick up the count, other than for hardware difficulties somewht?~in the program, Once we get our cryoga~icsaboard the stage we thei~are in the . positiot~of a 72-hour recycle. These are my conclusior~son wherz we have been and what we have bee!^ doing since our CDDT ended, and now we expt.ct to pick up the count at 11:GO p.m. for a launch s t 7: 0 0 a.m. Col. Olsot~: Departn:ent of Defense support for this mission is essentially the 50 1, hie have roi~yhl.y45 airsame as it was for Apollo 4 craft and 1.1 ships involved. CZ'c are taking advantage of this unmanned mission, of col!ae, to fuither t~ai!; o w crews and check S zrt? con~ir~g iilto the out the eyuipn~entOII the new Y C S D ~ ~ Y C Cti:zk -- �inventory to support Apollo, such as the Apollo ships and the ARIA aircraft, There w i l l be two aircraft in the Hawaiian area for reentry, there w i l l be three of them out here in the Atlantic, There are three Apollo ships involved. One of them, the Mercury, is sitting out here in the port, but we are getting training as the spacecraft passes over, so i f you're interested in Apollo ships, there is one right here at the port. Question: I'd like a recap on the postponements, the seriousness of them, etc,, from March 2 1. There have been five postponements, is that correct? MY, Schneider: I don't know the numbers. We did stark out for March 21, We did have a number of minor probtems, normal problems. Perhaps Rocco would like to go into them, Mr. Petrone: , Those of us working in the program, doing the job day by day, perhaps don't see much of the calendar shifts -- there are shifts throughout our scheduleo I can't think of anything -- you see, in the CDDT we did have three attempts. On one attempt we had a leak in the facility, that we had to repair. On a second attempt we had fuel difficulties. So it was those kind of problems that went on and moved us from the 2 I s t to the 4 t h -- throughout our preparation schedule, 1 can't recall a single large item that we changed out,, There was additive work, things took a l i t t l e longer at;d on some of our tasks, either we didn't hit it the First time or had to go. back i n and change a component, but there was nothing significantly large that gave us a two week s l i p by itself, There were many additive situations. Question: I'd I ike to ask George Low if a!! the objectives of thc spacecraft are regarded as secondary as f a as he is concerned, is there anything that could happen to the spacecraft, including washout or failure to recover, that might mxke you want to have another preparztory fl ight before manned flight ? Mrb Low: Wel I, I have to say yes to that question, but I can't give you a more specific answer, IF we should lose a spacecraft because of a spacecraft failure, we would hate to lool< at that failur2 t o determine whether we would need another flight or car? solve it by ground test or analysis or what have you, These questions are very difficult to answer before a flight, b[r"tome very easy after a fl iyht, �Question: For Mr. Sctllreider or Mr, Petrone, Can you explain in a little further detail the J-2 pump discharge problem? Mr. Petrone: We have a redl ine that we have to zchieve in order to assure that whe1.1your turbopump starts pumping your liquid oxygen or your l iquid hydrogen into your engine, that you do not cavitate. The term means that you don't convert the fluids into gases, because you want to deliver liquids. You want to del iver a good sol i d liquid, This has to do with ten~peratureand pressure. So we have a temperature reading that we look for at the engine inlet, The redl ine we're looking for and we're set at, is minus 286 degrees Fahrenheit, It .is now, with looking at the engines specifically and having run through our Countdown Demonstrat ion Thursday, we have, in effect, raised that two degrees to minus 284 and what you're doing here is looking for a number that ~ v j l assure l that the pumps function properly so that the liquid doesn't gasify as it goes through the pumps. These are very cold liquids and as you s i t there, you tend to pick up heat, just by virtue 6f the fact that they ar2 cryogenic. So the question of a redline on an engine, and it has to do with these particular engines and the head that you have on it, the prim2 purpose of it is to prevent cavitation or to prevent the Iiquids from being converted to a gas before you get t o the injector of that engine, �Question: May I follow up on that? M r . Petrone: Yes. Quest ion: This was on the oxygen side, rather than on the hydrogen? Mr. Petrone: We had actually, Bill, three on the oxygen side and one on the hydrogen side. We had one hydrogen feed line and three oxygen feed lines i n the second stage wherein we were, say, a few degrees hotter than the redl ine l imits . Quest ion: You don't redline hydrogen at any temperature as high as minus 286, do you? M r . Petrone: No. The number I gave was for oxygen. Hydrogen i s minus 420, i f my memory serves, minus 420. Question: Can you account for the heat sources? Dr. Rudolph: No. Really , t h i s i s not so easy to explain. We know that there must be a change i n the heat source, but what it really i s we are s t i l l struggling with. It could be. . . .. . . Question: I s this a novel situation? Has it ever happened before? Dr. Rudolph: It has not happened before. Mr. Petrone: It did not happen on 5 Q l . However, i t has beet1 seen on prior programs. Dr. Rudolph: Maybe 1 can say the following. Since this compartment where these engines are we can only test here at the Cape for the f i r s t time, not i n our captivefirirrjs on our test stands, and therefore the conditions are entirely differetit because n~!rdthe engines are enclosed and are between the oxygen tank of the second stage and the oxygen tank on the first stag?. .So we have to d2liver h2aE to protect against too much cold. Now any slight cha~gc!in the construction, an insulation change, would affect the condition in there We ti;lve taken covrcctive action by inproving insulation and as Racco already meniioned, we changed the rc;dli;le so we c-an accept a highet. tenrpeiature, but what it w i l l really turn o ~ r tomorrow t rilorniny, we don't kuov~for suye. . �Question: One part of my question may.have been answered. You changed the redline. Was that the figure you gave, Rocco ,two degrees difference; and how much different.was it; was it the CDDT when this turned up? How many degrees was it past the redline value? Mr. Petrone: It was about four or five below---or hotter---with these temperatures we're working i n the negative. We were five degrees warmer than we wanted toebe and there was some variation between the engines, but about five degrees. Dr. Rudolph: That was the worst one. The others were better. Now here we can, we have done some improved insulating and I think it w i l l contribute to a better condition and also, we changed the redline. We give two degrees, so that we think w i l l get off i n the stock box, what we call it. The engines are very sensitive to temperatures and pressures and that should do the trick. Again, we are not sure. Question: I s this only on the S-ll? Dr .. Rudolph: That's only on the S-li Question: What i s getting too hot, the cryogznics or some of the metal? Mr. Petrone: The cryogenics. Tile cryogenics ur,der the head and under the pressures in effect get superheated and that!s what this increase i n temperature is. Question: This i s for Mr. Schneider. Last week Bob Moser told us that his people are anxious to get the 503 vehicle out on the pad within ten days, i f it has to be unmanned, and he'd like to have a decision from you within seven days whether it's going to be manned or unmanned. Could you give him one i n t!mt time? Mr. Schneider: Well, I'll hasten to state that tile decision i s not mine. (Laughter). . A l l 1 car1 say i s that ttls decision w i l l be made as soon as there i s an adequate analysis of the data, so that we can determine whether or not the mission satisfied all of our requirements. As a little aside, it's difficult sometimes at the completion of 2 mission to determice whether or not it is a completely si~ccessfulmission, because you've got to await analysis of all of the data. You can have what appeals to bc a pcrfect mission 2nd i f you had a telemetry t Iiave no clata frorn thc tcchrrical link go out or a niuliiplexer yo o ~and statidpoint, it's a cornpletz failiire . �Similarly, on the other hand, you can have one where things change considerably during the mission, such as what happened on Apollo 5, but you get a i l of the data that you've been really looking for in the flight. So it w i l l take some time to make tha: decision and we a l l know how everyone wants the decision as early as possible. So that's a l l I can say now. Question: To follow that up, i f you don't say have a decision within ten or twelve days but it s t i l l looks goad, would you hold up the rollout of the 503 to the pad? Mr. Schneider: I think we'd wait, that we'd hold that decision and make that wtien we see how good the data i s or how bad the data i s . W e ' l l maice that depending on how it looks. Quest ion: Regarding the engine, again. Did this affect a l l engines and secondly, at what point w i l l you know wtiether it has been solved? Mr. Petrone: It affected three of the five of the liquid oxygen feed ducts and one of the five of the liquid hydrogen. \fire w i l l not know we have solved it to proceed w i t h the mission ufitil 22 seconds before liftoff. Q~testion: F o r B i l l Schneider. B i l l , you said i t ' s possible a l l the pritnary mission objectives w i l l be acenmplishcd by insertion into otbit. What has to be accomplished by ii~sertioninto orbit to meet a l l of your primary objectives? M r . Schneider: Well, let me hasten to add thzt a l l of the primary objectives, as listed i n your press kit, do include an S-IV-43 restart and we w i l l be mightily disappointed and w i l l not consider the rilissiorl a complete success i f we do n ~ yct t that. What 1 am saying i s that, i f for some reason or ckher we do not get a restart, we may arid D hasten to say "may", we may have sufficient information to make a ptaper decision on whether or not th? Saiirun V i s ready for man rating. We w i i l not know that until long after- ihe f l i yht , because that would be as 2 result of catefli2 analysis of t f ~ data. ~: Question: I'd like to go back to the hzating problerri, just for a moment. 1"Y'hen the.. .This pvoblt.ri1 occurs, as I LII-iderstand i t , as thc cryogenics are being pumped into the tanks? . �Mr. Petrone: No. The problem actually is seen when we go into automatic sequence at three minutes and, I believe, seven seconds. We started pressurization activity. The cryogenics heat up under the pressures. These are the flight pressures that we're building up. Now what we have to do i s read, and we do this on every flight, we read the temperature at the inlet.to the engine. We establish a band width. Vie call it a redline and wd say we must be within. that band width or below that redline in order to function properly, and on the S-ll you're reading a value on the ground and actually the engine isn't going to ignite until some two and a half minutes, so what you're doing i s extrapolating a ground condition into what it will be two and a half minutes later, but you see your temperature rise, in your automatic sequence. It's the or11y time we can see it.. That's the reason Dr. Rudolph mentioned we've got to go through our terminal sequence. We'l l be reading these values and our tinies are down to minus.22 seconds. If we are within the redline, we would then proceed. I f we're not, we plan to cut off. Question: A t the time the fuel i s injected into the engine, i n which state is it? is it liquid and then it gasifies in the engine? Mr. Petrone: You gc through the injector as a liquid with your liquid oxygen. The difficulty comes at your pump i f you start to cavitate .or build up an air bubble there. The pump w i l l not work efficiently and therefore your mixing ratios are entirefy different than what you've planfied and you can get any mixi~igratio, which can lead, of 'course, to many consequences, whether it would go in the engine properly, or whether you would get too much fuel ancl not enough oxygen, but basically, what you do, is you're upsetting your ratio of fuel to oxidizer going into the engine. Dr. Rudolph: And you want to start fircl rich, not oxygen rich. Both are liquid. Question: For George Low. George, what's the status of the spacecraft for the 503 mission? Where is it and how soon can you bring it out to the VAB to stack it, assuming that the flight tomorrow i s a success? . hlr Low: Are you tal king about a spacecraft for an unmanned or a manned flight? Wel I, George, that would be comrnand modulc 103, whic11 i s about to go into clieckont i r l Dowt~eyanrl LM-3 which has bcer~in ctleckout at Bztilpagc f3r S O ~ ! Itirria. C~ tdeitl~evoite of tliese vehicles arz schsduled for dslivery t~eveuntil surnrr;crtin;e. �Question: I'm a little confused, then, on the basis of Howard Benedict's question and then the answer to this last one,, what i s the sweat about moving the next Saturn V out to the pad i f you don't have the command module and the lunar module for the manned flight here? Answer: Well, because of some of.thz interactions i n getting some of our work done out on our remote sites, some of the programs that must be put in. We have a situation where our missions are pressing one on the other. . . Answer: I believe we've got a boilerplate on 503 now, and i f tihe decision was made to f l y unmanned, and what we have planned and brought up to this point, we have on board a boilerplate spacecraft with a l l the weights and the simulations i n there and that's what v~ould fly. Question: And you'd want to gct that out i n a hurry i n order to make way f o i 504, which would then be ycur first manned flight? But.. Answer: That's our planning as o f today. We've broughl the 5 03 to tlie point of checkout, where it's near rollout within these ten days that Howard mention~d. Now v ~ e ' l llook at tlie results of 5 0 2 . before we make further decisioiis. We have brought it to the point where the boilerplate that would f l y for the eventuality that we have to launch it, we would not wait on another delivery of a spacecraft. I believe that was the question that was raised. Question: I n other words, i f you decided that you were going to have another.. i f you decided that your next flight was going to be the manned one, then you would not be in a hurry to get the Saturn V out of the ..... VAB? Answer: That's correct. Question: Two more brief qirestions on the temperature problem. Ro'cco, I'm s t i l l not sure whether one of tlie J-2 ellgines or two of then1 were not affected i n any way by this problem, and secondly, do you have any indication of villy they were not affected and the others were? Mr. 'Petrone: It turns out that the t h r w that were affected by l i q ~ i i doxygen,and two were not. The otie that was affected by liquid h'yduo5cn was, not affected by liquid oxygen. So vie !lad the cr?nter engine that VJC ran fickter on tile liquid hycluogzn that did not, t f ~ was t within . �the redline, on the liquid oxygen. So what you have i s a case of three engines where they're out of spec. on liquid oxygen and one engine out of spec. on liquid hydrogen, not the same engines. Question: Can you explain in anyway why the first engine did not have this problem on either side? Mr. Petrbnz: No Dr. Rudolph: No, the fifth engine had the problem on the hydrogen side, the center engine, the hydrogen side, and it has a longer feed duct. You see, the feed duct comcs down the side of the stage and then goes to the engines, and they are not all down on one side, but are distributed. Now theti, the lines are equally long for the four outer engines, but the center engine, being farther away, needs a longer f ~ e dline, so it i s therefore more sensitive to any temperature changes which might occur in that stretch of the line t o the center engine. Mr. Petrone: It's a frrtiction of geometry and heat distribution, as Dr. Rudolph mentioned. The flow in that interstage, the only time you see it is here at the launch site. The only time you have a first stage to sit on topof and therefore the fuel conditioi~syoit get. We have electror~lcsin there and actually v:t? nitlst pump warrn air in there. Now you get a series of factors so that you end up with a result: and therz's going to be same movemet;t of values, the inlet temperatures, and literally, one can only experiment with it here to see what the end result i s going to be. It cannot be done on a test site. Mr. Klng: We had two patient hands i n the front row and there's a third hand up now. Vde'll take these two questions 11t;vrt ,then we'll go to Houston for questions, therl we'il ccltrle back here far anybody who has questions. Go ahead. Question: Another question on this heat probier;!. If you go to F mint!s 22 seconds and havc to hold, w i i l that be a prolonged hof d or.. Mu. Petronz: We wiff not hold at T minus 22. At I"r n i n ~ ~22 s secofids, anybyhere after three minutes seven seconds, we w i l l revert back, we'i t go back to T minus 24 minutes. .*.. .... �Question: Is there some quick fix or do you have something in'mind that you can make a change .to get the temperature down again? Mr. Petrone:. By observing the particular trace of the temperature, we'll be watching the temperature on. the recorder and have it plotted. There are adjustments, such as inlet, temperatures of that interstage. That i s one adjustment we can make ., Dr. Rudolph: We also expect that we had during the CDDT, that on the second round as we call it, the situation had improved. It did. on the first attempt, or rather on the second attempt, during the CDDT, improve, Only one LOX side was out of the specs. or the .redline. Que.stion: I believe this i s for Dr. Rudolph. A t an earlier briefing, Bob Moser told us that i f vie go manned on 503., the S-11 stage w i l l go back. to Michoud for man rating and certain modifications. 1-le specifically nlentioned possible relocation or strenthening of the baffles, the LOX baffles which hzve given some troubleon 5 0 1 . Could you pinpoint this and explain a little b i t about it. Dr. Rudolph: Yes, you talk two different i s s ~ e sat the same time, so that we talk fir'st about a one where you mention the second stage, th3 S-11 would go back to the test site. That's correct. We would indicate that 503 would be manned, take the second stage, ship it'back to the Mississippi Test Facility znd make a cryogenic proof test, so that answers one question, I believe. The other one .is that during the 5 0 1 LOX loading in the .S-I!, we had damage of baffles and i n order to save time during the countdown and avoid crew fatigue we want to go to a fast f i l l on 503 manned. Now since we had this problem with the. baffle damage of 501, we have to do something to the baffles. Strengthen them for instance. Question: What? Specifically, how? Dr. Rudolph: Well, we, for instance, changed the baffles, which are shaped like a rhomboid and s i t down at the bottom of the LOX sun,p. We took the lower half off, so i n a way, LV.,~ took them out of ti12 stream of the incoming liquid oxygen. That helps, but we also have to stirdy the flow dynamics inside. It isn't all that simple. As I say it here, and again, you can only find that out by testing, not by anaf.ysis, by sitting down at your desk ancl trying in your mind to figure o.ut what the f ~ r c e sare. 'Any~lay,tvt? tilink we, by also niaking certain changes to the facility, Kocccr, understand the probler~i well eno:!gh that on 503, manned, we c2n fast load zgaln. �Mr. King: Thank you. We'll now switch to Houston. I understand both M r . Kraft and M r . Chaviescvorth have a statement. \lo ice : T h i s i s I-lauston. We have one logistical announcement to make f i r s t . The Houston News Center w i l l be open until ten p .me, Central time, this evening and reopen at fowr a.m., Central time, tomorrow morning. Next w e ' l l hear from M r . Kraft and M r . Charlesworth. �Mr. Kraft: I ivot~ldlike to point out that this is another ~~nmanned flight of a manned vehicle and therefore another complex job for the flight control and ground crew to accomplistl. There are a large number of things that we can and may have to do and it may be a difficult m i s s i o ~from l that p o i ~ of t view. The other point I would like to make i s that we have been making a large number of modifications to the whole network over the last two years and this flight i n itself i s sort of a dress rehearsal for our upcoming .first manned flight of the 101 Spacecraft. We have made a lot of changes, we've added a lot of equipment and we feel now that this flight w i l l he proof that all of that equipment i s ready to support our manned space flight program. About all 1 would like to add that we have completed our tralning to date with what I thirlk is good results a i d i t seems prepared to do whatever i s required to he done. I n terns of the facilities, our ground support facilities, computers, network, etc. ,are proceeding along normally with our part of the count to meet the pad's. We have no problems at this time, and based on past testing support and the CDDT we don't really expect any and we expect to be ready to Meet the pad launch in the morning and have a good flight. Okay, we are open now here in klouston for questiorrs, Assuming a lar~nchtomorrow morning, has anyone recalculated the apogee and perigee of the S-IVB, and how mzny degrees it wifi' miss the moon, and whether it wil! come hack to earth ? Mr. Kraft: Mr. Chaulesworth has. l t v e got a few nirrnbeus, 1 knew someone would ask. Assuming we launch on time, the best ififormation I have i s to expect the apogee of the S-IVS to be some 279 thousand 13autica.l miles. With a perigee, that i s wker; it comes back to the earth, of around 1700 m i l e s , with a period of some 16 clays. Now we don't expect it tc enter essentially the area of the moon's sphere of infiuence, i f we go on time. Nov~, i f you try to pin me down v1itl.1 launch delays or different days I can't t~onestfyanswer it becairse it i s a variable depending .on the time of the day you launch, location , day of the month, eir:. Question: What about i n reentering the atmosphere? LViII i t corrle back and dn that under ihe present plans. Mr. Kraft: The first time out i t d;oesnlt look like it will ,but the next time around i f we get into the spherz of the ~ O D ~ I ' Sit-rfiuence becatlse of the trajectory, i t could, It's probably a good probability that it w i l i come in. Any further questions Fiom I-louston here ? �Mr. King: Thank you. We'll continue the questions here as has been the practice and is the practice once again. Mr. Schneider passed oil a note t o me to remind me that he does have an airplane to catch. We w i l l continue this for a short while. Question: If we had t o put a dollar value on that beast out there from the top of the L E S down to the base of the model what would that figure be? Mr. Lodge:. We don't judge our program that way. It's kind of meaning!ess There are so, many things that you don't see that you pay for that there is no real way of coming up with what the dollar value i s of that. The do1lar value i s immense when you con sider the value to the United States. The value to the United States is incalculable. What it costs, I don't have any way of figurir~gout. Question: Rocco, how many times is it feasible to recycle back t o 24 minutes, Would you do it just one time or.. Mr. Petrorie: No. We have a multiple opportunity. We are looking for a rnaximum .of four.. That is going to depend upon many things. As far as gaseous hydrogen that we use to charge our bottles for the J-2 engine, we feel vde have 4 recycles that the time duration goes back t o T -24 does not mean'we w i l l go back and pick up and then yo in again. You have to loolc at data, look at the va,lues, lool<'at the occurenccs, the trends, temperatures and all, and wait for certain things to stabilize and then go i n again.. Right now we are hoping we have worked these values so that the First time tfirough, of course, is our best'gilkss. We will, based on what we see ar~dwhat we know happened Sunday be able to plot two points on the curve and make another extrapolation forward at the second attempt. Question: I am sure this w i l l be an easy one. How much damage from a monetary standpoint did this first Saturn V cost to the piid and how long did it take to fix it, and have you taken any steps to perhaps I~aveless damage this ti'me? Mr. Petrone: Yes. We have taken steps to hatie !ess damage. The items of the pad and launcher are sornewhai. sepamie. The launcher g2ts a l i t t l e more damage than the pad itself. \rVe would anticipate tl.~at,say for an average launch and what we found in 501, that we could have the pad in shape within 10 days to receive another launcher. The launcher itself is going to take longer in the neighborhood of thrcc weeks, and maybe Four. The monetary value we have not - - . . - ' - �collected as part of our refurbishment and maintenance, if you go into maintenafice items and refurbishment. However I must say that I was most pleased with the very limited damage on the 501 and I only hope it i s an indication of what we wil I continue to see i n the future. It was very, very minor in the larger picture. Question: Well, from a money standpoint, can you give us the ballpark. Was it under one hundred m i l lion? - It was more than $10. Somewhere along there must be faily close. Answeu: That's a pretty big broad spectrum you put out. Why don't we just use that? Question: You must be able to do better than that. No - let's say yes. It's between those two numbers. Question: Aviation Week i n the current issue says that if tomoru~w'sflight goes v~ell, there i s a good chance that tbe manned flight to the moon could go in the first half of 1969. Would you comment please? Mr. Low: There can be a lot of problems t o take yet between tomorrow's flight and the first fiight t:, the moon. Vde /lave to get manned flight i n Apallo in earth orbit and we have to do a number of earth orbital rendezvous flights on the Sziurn V, and then with the LM and the CSNI, f think it w i l l be a most difficuit'job to get the lunar landing by the end of 1969. 1 think we've got a very good chance of doing that. Question: Isense a certain ~'eiuctai~cc to talk about money. However, I have to press this question a little b i t to Mr. Schneider. In testimony before the sub-committee last fdair'ch 16, 1967, I believe it was, von Braun put a price tag, a fairly precise one of $205 million for a laut~chedSaturn V. Peopie at NASA tell me that that figure i s still kind of hanging and that's alright. Nr~wif von Braun can be as precise in 1967 when zsked by Congress about the price of a vehicle, why can't we be equally precise in 3-968 when aslced by the puess. I don't agree that this is just an editorial comment is pqssing it i s kind of meaningless to talk about the price of anything. Mr. Schneider: I am ;he mission clirectou - not the Senate director. As mission director I couldn't 'even tell rot! what u!lu bt~dgctis. I am not in that business. That's why i cannot answer that qtiestiot~. - �Question: Wel I , can anyone ? Answer: Nobody here at the table has the answer for you and we w i l l do our best to get it for you. We'll check. Question: For B i l l Schneider. Bill, just so I fairly accurately understand this point. If yoLi don't get a second stage burn of the S-IVB,have you met your primary mission objective? Can you man rate for 503 and start manned flights with 503? Mr. Schneider: The answer to the first one is no. We would not have met the primary mission objectives as stated in the document because they do include anS-IVB restart. The answer to the second question is it is perfectly coi~ceivablethat after analysis of the data we could 'find that the reason for restart failure had no implications on whether or not the vehicle was man-ratable. The first planned Saturn V mission does not currently include the manned restart of the S-IVB. - Question: For George Low. Why is the new hatch being flown aboard this spacecraft other than the fact i t was ready. Mr. Lovr: I guess you have almost answered your own question, Joe. We did at the time we made the decision on the nevi hatch know that we could not get it oil Spacecraft 017. LVe knew we c o ~ ~get l d it on Spacecraft 0 2 0 so we nloved it outand pit it on 0 20 t o get the best possible test of the hatch at the speeds, heat transfer rates, etc., but we have completed some very satisfactory ground tests. We have more to go and also we have seen the very low heating rate i n that area on Spacecraft 017 so that since that decision was made we have convinced ourselves that we don't need a flight test of this hatch for man rating pi.!rposes, Question: I have two short questions. The first one is what is the official lifting capacity of the Saturn V. Dr. Rudolph: Question: 2 0 0 , 0 0 0 pounds? Then this is an increase of 10,000 pounds i n about the last three or f o i i ~years is i t ? Dr. Rudolph: No. For the last 2 years, i f my nlernory serves pounds. rile right., 98,000 �Question: Second question. The S-IVB trajectory, and I siippose this might go to Mr. Charlesworth in Houston. I believe this is one of the few and possibly the only circ~imlunartrajectory that we have flown. Possibly there has been one, or maybe a scientific experiment has flown this way. As I understand it, this is an orbit that goes around both the Earth and the Moon - is it not - am I wrong about that? I see Mr. Schneider shaking his head. Weii, I can just add this. Is this the kind of trajectory that one would f l y i f one were flying men around the moon? Answer: In terms of energy imparted to the trajectory, yes. In terms of the actual taigeting , no. LVe are essentially shooting for a fictitioirs moon, so to,speal<. lye do not expect tcmorrovi for this trajectory to go around both the Earth and the Moon. We do not expect it to enter into the sphere of influence of the PJoon. Question: I'm a i i t t l e b i t confused about this S-IVB. We were told by Mr. Charleswouth that we had a 279,000 nautical mile apogee and a 1,700 nautical mile perigee. That is frain the Moon, is that right, or frorn the Earth? You just told Diet< Le\.vis it did not go aroilt?d both of them. W i l l somebody please maybe use a blackhoard and tell us what it is going to do. Mr. Charlesworth: i t goes out t o lunar distances, but it does not go around the Moon itself. Mr. Schneider: It is a high!y elliptical orbit that at its closest point ccmes within I! ,700 rriiles of the Eatth and at its furthest ciistance goes t o 279,060 miles f(om the Earth. Quest 'Ion: Wl~atis the lifetime? Answer: The period i s 26 days. Mr. Charlesworth: The period for this orbit, this I?igltly elliptical orbit, i s 16 days. When i t comes bzck through 2nd starts up, depending on where the Moon is, we will prciiabfy get some pertirrbatioix, it is difficult to predict-- 1 can't predict--wf~at ~ j i fl i,appen on the next pzss. It niay very li!ceiy rc"c1r.n is Earih. Let me p ~ i n out t that fcr the f i g ~ ~ r eused s fcr the S--IVB that i f you a:c o f f only a few feet per second or several ierlths af a cie<jr.cc it is going to have a Irernzncloils effect on the apctgee and perigee relative to the Earth. So yo\i shouldn't take t i i ~ f i nt l l i i i ~ k ? ! ' ~2 s gospel. �Question: i just want t o reiterate this point since it was raised again. As I understood, the ascent part, the orbit of the S-IVB would go around the Moon and then on its return would go around the Earth and then go back up to the Moon. Answer: Why don't t draw you a picture after we're done here. Question: One more time on the J-2's. Bid you detect this problem i n the CDDT? And also in some way you detected it today. I'm confused on that. Answer: Just on the C D D I ; Sort of been living with it ever since. Dr. Rudolph: Yes. Discussing it, analyzing it, looking at what shifts we should make. But in order to detect it, you have to have cryogenic support and go through your terminal sequence. Question: The fuel flow has to stail before you detect i t ? Dr. Rudolph: You don't have to start fuel flow. No, you've got static conditions of the fuel i n the pump. You've got a valve downstream of that pump. When you are measuring your temgeuature and pressure, geometry-wise just above the entrance to the engine itself. You do not measure the flow. We get the flow at ignitior~on the first stage. On the second stage there would not be flow until you start, actualiy 2-1/2 minutes into the mission. - Question: Mr. Schneider, if for some reason you are unable to mail rate this vehicle tomorrow, how firm are your plans to go t o a dua! laurrch concept using the Saturn IB after the 205 flight? Mr. Schneider: We have that i n our plans and we w i l l retain it in our plans. However, i f we do not have a satisfactcry Flight on t.l~isone, the 502 flight, our current plans are to go out with 503 boiler plates. Mow i f we do that. and that is a successful flight then it is conceiveable that we would go to the Saturn V matlned launch on the 504 and not clo a dual launch, but we w i l l retain that capability until some later date. Question: Jack., any pilots i n training and i f so how maily and w i l l they be watching it tomorrow. , Mr. King: We are supposed to be getting a list, George, of which astronauts w i l l be here for the launch. 1111 check on that as soon as this i s over and wllatevcr information we have we w i l l be glad to pass i t on. 1 certainly expect ve; wilt habe it by tonio;:roa rnorillng. �Question: i would like to ask one question. What are the reasons, a l l the reasons for the S-IVB shooting for this fictitious moon target? Dr. Rudolph: You would exeiScisethe antennas on the stage and find out whether you can communicate. That is, whether you can receive signals or can send signals up and have them bounce back, There i s certainly one very significant advantage and y.ou would also find out whether you achieved your velocities you are looking for. I would like to add something so that there is no misconception. The S-IVB has a guaranteed l i f e of about six hours, but we hope that w i l l go on ,to about 1 0 or I 1 hours. As you hcard earlier, this has a 15-day period, so we would only be able to get actual signals back from the S-lVB for those first 1 0 hours - not out at lunar distances. Question: I woilld like to pursue Mr. Lewis' questiori further. You said that the Saturn V is now rated to lift 1 0 0 , 0 0 0 pounds. The present weight, the payload for tornorrow, comes to just under 94,000 pounds, according to the press information. However, this is only a 6 , 0 0 0 pound lunar test a r t i ~ l e . The real load, as I understand it, w i l l be about 3 2 , 0 0 0 , maybe Inore, If we add this 6 , 0 0 0 we w i l l just barely make it w i t h 1 0 0 , 0 0 0 pounds of payload in a vehicle capable of l i f t i n g 9 0 0 , 0 0 0 pounds. Very marginal. Maybe Mr. LOW would l i k e to answer. Mr. Low: True. We do have a weiglit problem in Apollo. Comrnand Service modules and the lunar moduie are esscniialfy at the limit of w c i g i ~ t that we can fly. Vlle have the s i l ~ ~ a t i under o i ~ control, the cornmand/service modules ren~ainec!steady ellough though a t t h e i r current weight for the last 4 or 5 m o t 2 t i ~ . I am talking about the comrnand/scrvice module from the Block 2 vellicle that w i l l be on the lur;ar rrrissioii. P,nd we s t i l l hzve som? margirl left. Thc situation on the lunar module is sotneavhat tighter since we made the post-accident changes s o ~ ~ ~ e wlater h a l and we did riot get tila weights on the control as q ~ i i c k l y , b u t they loo are leveling off now aud with very tight weight coi~ivoiand sorrle possible weight recfuction I am confident we are going to niako it, but v,e esscrltialiy arc at the lirnit. Mr. King: I am afraid we are going to have to terinlnatc the conference now. Thai~!<yorl very inuch. � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000074 Title A name given to the resource "Apollo 6 Pre-Launch Press Conference." Description An account of the resource The press conference was given at Cape Royal News Center in Cocoa Beach, Florida, on Wednesday, April 3, 1968, at 3:30 PM. Participants: William C. Schneider, Apollo Mission Director, NASA; George M. Low, Apollo Spacecraft Manager, NASA; Clifford Charlesworth, Apollo 6 Flight Director, Manned Spacecraft Center, NASA; Dr. Arthur Rudolph, Saturn V Program Office, Marshall Space Flight Center, NASA; Rocco A. Petrone, Apollo 6 Launch Director, Kennedy Space Center, NASA; Col. Royce Olson, USAF, Director DOD Manned Spaceflight Support Office, Patrick AFB; Chris Kraft, Director of Flight Operations, Manned Spacecraft Center. Creator An entity primarily responsible for making the resource United States. National Aeronautics and Space Administration Date A point or period of time associated with an event in the lifecycle of the resource 1968-04-03 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Apollo 6 flight Apollo spacecraft John F. Kennedy Space Center Project Apollo (U.S.) Saturn launch vehicles Saturn Project (U.S.) Type The nature or genre of the resource Press releases Text Source A related resource from which the described resource is derived Saturn V Collection Box 26, Folder 19 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000051_000074 https://digitalprojects.uah.edu/files/original/20/1157/spc_stnv_000073.pdf ece137d305c88eda64e48bf9f34ff4e3 PDF Text Text nRt!fr C L ~ M S k~f r ' *F 8) J,. ' . Mr, David L. Christensen Documentation Coordinator Saturn History Program University of Alabama Huntsville, Alabama 35 8 0 7 I ��STACKING - Bendix cranes lift the 294,900-pound first stage of the Saturn 5 with ease. preparing to place it atop the mobile launcher inThe high b%y of the VAB. Launch Support D i t '-? is responsible for the stacking operations of all stages and t spacecr'aft, in preparing i t for "roll ouP1 to the launch pad. . INTRODUCTION I f you have been fortunate i n this historic hour to watch the events surrounding the pre-launch and launch of Apollo 11 unfold, either from a vantage point at the Kennedy Space Center, o r along the banks of the Indian and Banana Rivers, o r from motel rooms along the Florida East Coast, then y o w have been privileged to see first hand the greatest human achievement i n the annals of mankind. NASA and its team of aerospace contractors are now reaching for just one of their goals -- landing a man o n the surface of the moon and returning h i m safely to earth. There are yet other space conquests in America's exploration of buter space which will call for even more determined spiritwhich has been the backbone of NASA's space program. The pages of t h i s booklet are designed to acquaint you with facts of the Saturn 5, the Apollo soacecraft and t h Lunar Module moonship, and to keep you informed of the day-today scheduled missions as they are now planned, for the duration of this 8-day mission. This booklet may also be a souvenir to r e m ~ n dyou for many years to come that you were here during the flight of Apollo 11, the greatest adventure story since Christopher Columbus began his perilous voyage into the unknown. THE BENDIX CORPORATION I �ROLL OUT- The Bendix-operated 6 million pound CrawlerlTransporter lumbers lowly to the pad carrying its precious cargo, ApollolSaturn 5. Known as one of the strongest, slowest, noisiest, strangest land vehicles i n the world, the giant tractor moves at less than one mile per h o u r during missions, SATURN V - APOLLO 11 AS-5061CSM - 1071LM-5 MAJOR OBJECTIVES 1. Perform a manned lunar landing and return to earth. 2. Perform selenological inspection and sampling, including contingencyllunar bulk sample collection. 3. Obtain data to assess the capability and limitations of the astronaut and his equipment i n the lunar enviranment, including: Inertial Measurement Unit (IMU) lunar surface operations and lunar surface EVA operations. 4. Obtain data o n characteristics and mechanical behavior of lunar surface. 5. Obtain data o n landing effects o n LM. 6. Determine position of LM o n the lunar surface. 7. Obtain data o n effects of illumination and contrast conditions on crew visual perception. 8. Demonstrate procedures and hardware used to prevent contamination of the earth's biosphere. 9. Obtain photographic coverage during lunar landing and lunar stay period. �APOLLO 'GAS STATION' - The Bendix Corporation's Launch Support Division High Pressure Gas Department and the Propellant Section combine to provide the world's largest "gas station", offering high and low pressure gasses and propellant delivery for NASA's Apollo Program. MISSION OBJECTIVES 10. Obtain television coverage during lunar stay period 11. Deploy the Early Apollo Scientific Experiments Package (EASEP). 12. Demonstrate operational launch vehicle (LV) capability by injecting a fully loaded Apollo Spacecrafl (SC) onto a specific circumlunar conic. 13. Demonstrate the adequacy of all SC systems and operational procedures for translunar and transearth fliqht. 14. Demonstrate the adequacy of deep space navigation techniques and of guidance accuracy during translunar and transearth midcourse corrections. 1 Demonstrate acceptable service propulsion system (SPS) performance and SC guidance during the lunar orbit insertion boost and the transearth injection boost. 16. Demonstrate acceptable Lunar Module (LMI systems performance during the descent-to-hover boost. 17. Demonstrate acceptable LM systems performance during the ascent and rendezvous mode. �A BIG JOB - Although itweighs less than a pound, this sensor is capable of initiating shut-down of the 1.5 million-pound-thrust engines of the S- IC, the initial booster stage of NASA's Saturn 5. The sensors is built by The Bendix Corporation Instruments and Life Support Division, Davenport, Iowa. PERTINENT DATA Saturn V Launch Vehicle PRE-LAUNCH LAJJNU Y F H I a E GROSS WEIGHT 5 6.3MI.W POUNDS SATURN V STAGE MRNUFACTUREl MRNUFACTURER NORTH AMERICAN-ROCKWELL M I N I M VACUUM THRUST AT lUIDF t A1 170.000 FT. AN0 70'F ? NWINAL V A W W THRUST AT NOTE: M R L 6 T VALUES. WEIGHTS. RND BURN T I W ARE ALL APPPXINATIOHS. 6O.F �COVER UP - An inertral guidance system of the type assigned to keeping the Saturn V r o c k t on course during Apollo 11 moan shot. The unit is built by Navigation and Control Divis~on,Teterboro, N. J, Lunar Module Reaction Control Descent Propulsion System (DPS) TRW Corporation r o t o r pmv~der 10,500 l b r . Thrust Total We~ght - 30,531 lbs. �OUTLINE OF FLIGHT PROFiLE Launch and Earth Parking Orbit Insertion - The Saturn V Vehicle will insert the S-IVBIIUlLiWCSM into a 100 NM circular orbit at 11 minutes, 24 seconds after liftoff. The S- IVBII U and Spacecraft checkout will be accomplished during the orbital coast phase. Translunar Injection and Coast - The Launch Vehicle S-IVB stage will be reignited during the second parking orbit, to inject the S-IVB, LM and CSM into a translunar trajectory. This nominal injection will provide a "free return" to Earth i f the insertion into lunar parking orbit cannot be accomplished. The CSMwill separate from the S-IVB, transpose, dock, and initiate ejection of the LM. Midcourse corrections will be made, as required, utilizing the Manned Space Flight Network (MSFN) for navigation. Lunar Orbit Insertion - Service Propulsion System (SPS) will insert the Spacecraft into an initla1 orblt of 60 X 170 NM. Following insertion and systems checks and two revolutions in this orbit, the orbitwill be circularized at @ NM. I Lunar Module Descent and Landing - The Commander (CDR) and LM Pilot (LMP) will enter the LM and separate from the CSM using the S M - Reaction Control System (RCS). The LM l used for powered Descent Propulsion System (DPS) w ~ l be descent to the lunar surface. The vertical descent portion of the landing phase will start at an altltude of 150 feet. Rest oeriods will follow. Flight Profile Lunar Surface Operations - The staytime o n the lunar surface is planned at 21 hours, 33 minutes, and 21 seconds. Stay will include rest periods and EVA of 2 hours and 40 minutes at not over 70 feet radius from the LM. Planned activities include photography, TV, sample collection, LM inspection, assessment of astronaut capabilities, and limitations and experiment deployment. Lunar Module Ascent - At the completion of the lunar surface activities the LM-Ascent Propulsion System (APS) and the LMRCS w i II be used to launch, rendezvous and dock to the CSM. The LM will coast from insertion to an elliptical orbit (9 X 45 NM) for one hour after which several maneuvers will be made to bring the LM and CSM range to within one nautical mile. Braki n g from this point will be performed manually. Once docked to the CSM the two LM Crewmen will transfer to the CSMwith sam- ' ples of lunar surface material. The CSM will be separated from the LM using the SM-RCS. Transearth Injection and Coast - The S P 5 w i l l be used to inject the CSM into the transearthtrajectory. Traosearth return time will be 63 hours, 51 minutes, 50'seconds. During the transearth coast Intermediate midcourse corrections will be mede, if required, utilizing the MSFN for navigation. Entry and Recovery - P r i o r to atmosphere entry the Command Module will be separated from the Service Module using the SMRCS The drogue parachute deployment sequence will start at a n altitude of 23,300 feet, the three main parachutes at 10,500 feet altltude. The nom~nalrange from the entry interface at 400,(MO feet alt~tudeto touchdown will be 1285 nautical miles Earth touchdown will be i n the Mid-Pacific. �LUNAR LANDING MISSION PROFILE ' �MAJOR SCHEDULE AND COUNTDOWN EVENTS T - 4 months, 2 weeks T - 3 months, 1week Erected Launch Vehicle S-IC, S-11, SIVB, and I U Erected Spacecraft CSM-107 and and LM-5 - 'I . . 2: T - 2 months l nstalled SIC and LV 0 r d n a k e ' and LES and Transferred SV to Pad A T - 1 month, 2 weeks Conducted SV - Flight Readiness Test - FRT T - 1 month Hypergolic Loading and RP-, loading of SV T - 3 weeks ' . -21 Begin Countdown Demonstration Test - Wet and Dry -% ; ' *s Countdown T - 114 hours Begin Countdown T - 106 hours, 30 min. Monitor GH2 Facility and Provide GN2 and GHe for Duration of Test T - 93 hours Begin Space Vehicle Ordnance Operations T - 89 hours Begin Launch Vehicle Ordnance Operations T - 85 hours Provide SCAPE Support �APQLLO TRACKING - B e n C i men operate the Devil's Ashpit station o n tiny volcanic-extinct Ascension Island, 5,m miles downrange from Cape Kennedy. This is one of the 12 sfations maintained and operated for NASA's Goddard Space Flight Center by the Bendix Field Engineering Corporation. Countdown T - 25 hours T - 24 hours T - 22 hours T - 20 hours T - 15 hours, 45 min. T - 15 hours, 30 min. Validate Astronaut Vans Inspect MSS for Travel Configuration Activate First Industrial Water Engine and Bring Up to Speed lnstall and Soap Plywood Surface at Pad Start and Stabilize Crawler Transporter Secure Hammerhead Crane for Launch Pressurize and Leak Check GH2 Cross Country Lines T - 13 hours, 45 min. Propel CIT to Top of Ramp T - 13 hours, 15 min. Propel CIT to Mate MSS T - 12 hours, 45 min. Jack CIT to Mate MSS T - l l hours lnstall and Soap Plywood Surface at MSS Parksite Release Weather Balloon T - 10 hours, 45 min. Jack MSS up to Clearance Height T - 10 hours, 15 min. Propel MSS to Parksite T - 9 hours, 45 min. - T 9 hours, 30 min. Provide Generator Support at CCF Until End of Mission Verify 11 Scott Air Packs in the ECS Room and 23 i n the Blast Room �countdown T - 9 hours Begin Built-in Hold of 6 hours Slide Wire Preps Complete and Ready to Support T - 8 hours, 15 min. Begin LV Propellant Loading T - 8 hours Begin LV Cryogenic Loading T - 7 hours Clear Route for Astro Van Activate 2nd and 3rd Industrial Water Engines T - 6 hours, 45 min. MSS Mated at Parksite T - 6 hours, 15 min. MSS is Hard Down o n Mounts T - 6 hours Release Weather Balloon T - 3 hours, 45 min. MSS Parksite Clear of Personnel T - 3 hours, 15 min. Prime Crew Enter Astro Van at MSO B ldg. T - 2 hours, 45 min. Crew Ingress at C-39 Pad A T - l hour Support RP-1 Fuel Level Pdjust merit o n LV T - 7 min. Verify GO for Launch *T - 3 min. Terminate LV Liquid Oxygen and Hydrogen Replenishment *T - 2 min., 47 sec. pressurize S-IVB LOX Tank *T - 1 min., 37 sec. pressurize S-IC, S-l I and S-IVB Fuel Tanks Countdown. 'T - 1 min., 22 sec. "T - 1 min., 12 sec. T - 1 min. 'T - 40 sec. Pressurize S-I I Liquid Hydrogen Tank Pressurize S-IC LOX Tank Pad Industrial Water On Flame Deflection Cooling Water On T - 9 sec. Ignition Sequence Start T - 2 sec. All 5 Engines Running "May not be exact time - actual countdown not available at this time. �FIRST DAY Wednesday T - 9 sec. lgnition Command T- 0 Liftoff T t 2 min., 14 sec. S-IC Inboard Engine Cutoff (1) I T S- I C Outboard Engine Cutoff (4) 2 min., 40 sec. t T t 2 min., 41 sec. S- ICIS-I I Separation T t 2 min., 42 sec. S-l l (2nd Stage) lgnition Jettison Launch Escape Tower (LET) T t 8 min., 50 sec. S- II Engine Cutoff (51 S-I IIS- IVB Separation T t 8 min., 51 sec. S- IVB (3rd Stage) 1st lgnition T + 11min., 21 sec. S-IVB Velocity Cutoff - Orbit Insertion - 100 N M T t 2 hrs., 44 min., 18 sec. S-IVB 2nd lgnition on 2nd Revolution T t 2 hrs., 49 rnin., 39 sec. S-IVB Cutoff - Translunar I n j e d i o n (TLI) T t 3 hrs., 12 min. CSM Separation from S-IVBIIUILM-5 and T ~ a n ~ p o ~ i t i o n T t 3 hrs., 22 min. Dock CSM with LM T t 4 hrs., 10 min. Eject LM from T t 4 hrs., 39 min., 37 sec. S- IVB Evasive Maneuver - SPS lgnition of CSMILM FIRST DAY T + 4 hrs., 49 min. S- IVB 3rd lgnition - Slingshot Maneuver - Orbit S-IVBIIU Around Sun T t 7 hrs. 39, Wc N M from Earth T t 11 h r s , 16 min. Midcourse Correction Maneuver No. 1 (MCC #1)of CSMILM-5 T + 19 hrs. SF,00'! NM from Earth SECOND DAY Th ursday T + 26 hrs., 3 min. MCC %2(if required) T + 43 hrs. 150,DM NM from Earth THIRD DAY Friday T + 53 hrs., 55 min. MCC 8 (if required) T t 56 hrs., 17 min. Lunar Module Pilot (LMP) - tntraVehicular Transfer (IVT) to LM Commander (CDR) - Transfer Equipment to LMP i n LM T + 57 hrs., 5 min. CDR - IVT to LM T + 58 h r s . LMP and CDR r e t u r n to CSM 180,000 N M from Earth T + 70 hrs., 55 min. MCC W (if required) �FOURTH DAY Saturday T + 73 hrs. GO-NO-GO for Lunar Orbit Insertion -#I(1011) T t 75 h r s , 55 min , 03 sec. 'Loll M N M X 170NM Orbit B u r n Time - 6 min., 5 sec. T Lunar Revolution # 3 t 80 hrs., 10 min T + 80 hrs., 12 min , 01 sec. + 81 h r s . , T LO12 m N M X @NM Orbit B u r n Time14 sec 48 min. LMP - Returns to CSM T t 83 hrs., 48 min Lunar Revolution $5 T + 84 hrs., 07 T + 94 hrs., 26 min. LMP - IVT to LM T + $4 h r s . , 50 min. CDR- I C T t 0 L M min. FIFTH DAY Sunday T + 97 hrs., 30 min. GO-NO-GO for Undocking T + 97 hrs., 58 min. L u m r Revolution #12 T + 98 h r s Undock LM from CSM , 18 min. T + 98 hrs., 43 min LM Separation from CSM T + 99 hrs., 42 min., 27 sec. Descent Orbit Insertion (DO!) B u r n Time - 35 sec. T + 100 h r s . , 38 min., 57 sec. PDI T Touchdown o n Moon + 100 hrs., 50 min., 5D sec. FIFTH DAY T + 100 hrs., 54 min. T + 101 hrs., 01 min. GO-NO-GO for 7 min. Stay GO-NO-GO for 1Lunar Revolution of CSM T + 101 hrs., 52 min. Lunar Revolution #14 for CSM T + 102 hrs., 10 min. T + 108 hrs., 32 min. Begin preparations for Egress T + 109 hrs., 50 min. Lunar Revolution #18 for CSM T + 110 hrs., 30 min. CDR - Start Extravehicular Activity (EVA) T + 110 hrs., 40 min. CDR - l nitial EVA with LMP Assistance and Monitoring Sequence c Camera - TV T + 110 hrs., 55 min. Contingency Sample Collection T + I l l hrs., 08 min. CDR - Rest and Photograph LMP - EVA T N Deployment qolar Wind Component (SWC) Deployment Bulk Sample Collection EVA and Environment Evaluation t 111 hrs., 30 min. GO-NO-GO for Lunar Stay T + 111 hrs.. 42 min. Perform LM Inspection T + I l l hrs., 45 min. Lunar Revolution #19 - LM T + 112 hrs. Early Apollo Scientific Equipment Package IEASEP) Deployment T + 112 hrs., 08 min. Documented Sample Collect ion �FIFTH DAY T + 112 hrs., 40 min. LMP - EVA Termination T + 112 hrs., 45 min. CDR - Rock and Transfer Sample Ret u r n Container (SRC) CDR - EVA Termination (Total EVA- 2 hrs., 40 min ) + 113 hrs. T T + 113 hrs.. 43 min. T Lunar Revolution #a- CSM Jettison Surplus Equipment Eat and Rest + 114 hrs., 21 min. SIXTH DAY Monday T + 122 hrs., 28 min., I1 sec. LWAS-Liftoff-Ascent Propulsion (APS) System - B u r n Time - 400 sec. T + lT2 hrs., 35 min., 25 sec. Orbit Insertion of L W A S T + 123 hrs., 26 min., 27 sec. LM-RCS-Coelliptic Sequence Initiation Maneuver - (CSI) B u r n Time - 46 sec. + 123 hrs., 25 min., 27 sec. T CSM Backup CSI B u r n T + 124 hrs., 24 min., 25 sec. LM-RCS Constant Delta Altitude Maneuver (CDH) B u r n Time - 2.8 SeC. T + 124 hrs., 27 min., 25 sec. CSM Backup - CDH B u r n T + 124 hrs., 02 min., 46 sec. LM-RCS Terminal Phase initiation Maneuver (TPI) B u r n Time - 23.3 T + 125 h rs. , 17 min. , 46 sec. LM- RCS-MCC #1 SIXTH DAY T + 125 hrs. , 32 min. , 46 sec. LM-RCS-MCC #2 T + 125 hrs., 42 min., 22 sec. LM-RCS Braking Maneuvers B u r n Time - 1.5 sec., Range - 1.0 NM T + 125 hrs., 44 min., 05 sec. LM-RCS B r a k i n ~ M a n e u v e r sB u r n Time- 9.6 sec., Range- .5 NM T + 125 hrs., 45 min., 14 sec. LM-RCS Braking Maneuvers B u r n Time - 9.0 sec., Range - . 2 N M LM-RCS Braking Maneuvers B u r n Ti me - 4.3 sec. , Range - .08NM T + 125 hrs., 47 min., 02 sec. T + 125 hrs., 48 min., 03 sec. LM-RCS Braking Maneuvers B u r n Time - 4.2 sec. , Range - 0.3 NM I T + 126 hrs. LM Actlve Docking with CSM T + 126 hrs., 48 min. CDR - IVT to CSM T + 127 hrs. LMP - IVT to CSM T + 128 hrs. Jettison LM-AS T + 129 hrs. , 32 min. Lunar Revolution #28 T + 131 hrs., 28 min., 43 sec. Transearth Insertion (TEI) B u r n Time SPS - 2 min., 20 sec., Lunar Revolution #29 SEVENTH DAY Tuesday T + 148 hrs., 32 min. MCC #5 (if required) �EIGHTH DAY Wednesday MCC #6 (if required) Earth insertion (El) - 22 hrs. T + 172 hrs., 58 min. NINTH DAY Thursday + 192 hrs. , 06 T min. MCC #7 (if required) EI- 3 hrs. T t 194 hrs., 57 min. CMiSM Separation T t 195 hrs., 06 min., 27 sec. Earth Insertion - Altitude - 4n0,%0 ft. T + 195 hrs., Enter, S-Band Blackbut T t T + 195 hrs., 06 min., 53 sec. 195 hrs., 07 min,, 51 sec. 07 min., 53sec. Astronauts Experience Peak G Force Exit. S-Band Blackout T + 195 hrs. , 15 rnin. Drogue Chutes Deployment 23,300 feet altitude T t 195 hrs., 15 min., 49 sec. Drogue Chutes Disconnect and 3 Main Parachutes Deploy at 10,500 feet altitude T t 195 hrs., 20 min. , 42 sec. Splashdown - Pacific Ocean FOOT STEPS ON THE MOON - Apollo 11astronauts will carry this self-contained seismic station as part o f the Early Apollo Scientific Experimental Package (EASEPI, to be placed on the moon. When operating, the seismometer may transmit to earth listeners the sound of the astronaut's footsteps. Ron Redick, of the Bendix Corporat~on'sAerospace Systems Division, A n n Arbor. Mich~gan, simulates the moon deployment. � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000073 Title A name given to the resource "Apollo 11 Mission Profile." Creator An entity primarily responsible for making the resource Bendix Field Engineering Corporation Date A point or period of time associated with an event in the lifecycle of the resource 1969-01-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Apollo 11 (Spacecraft) Project Apollo (U.S.) Saturn Project (U.S.) Saturn launch vehicles Space flight to the moon Type The nature or genre of the resource Pamphlets Text Source A related resource from which the described resource is derived Saturn V Collection Box 29, Folder 61 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000051_000074 https://digitalprojects.uah.edu/files/original/20/1156/spc_stnv_000072.pdf 2ec7547066c97c2fd55fea4efa5420fd PDF Text Text ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............. .......................... ............ ............. ............ ............... . N A T I O N A L A E R O N A U T I C S A N D SPACE ADMINISTRATIO ............................. .......... .:..,. . . .,&:.:.:.:.:.:.:.:.: . i.x:.:.:.:.:.:.:.:.:. ..................... ............ ............. FINAL ;;,. ..,........... ............. ..., .... .;. ..&:::::::: ...................... . . . . . . . . .SATURN I-IISTORY CCCUMENT .......... ................... . . ............. . .............. . . . . . . . ...... Universi~yof: Alabcma Ec :.-arch !nstitute 1 - a .:- !<j.%.:.:.:.:.:.:.:.:. History of Science C. Tecl..nofcgy Group .., . ?.-.~.-.~.~.~.~.~.~.~.~ . ,;-:*.:.:.:.:.;.;.:.:.:.:.:. ..... .i' ............... * ........... Date --- - - - - - - - Doc. No. - - - ----........... ............ ............. ............. ... ....,,. . .!<' ........... ..... ...*....-.m...-.*.*,-.-...-.-. c.;: .. .*;:+:.::.>>:.:.:.:. +:.-......: ............. .:?........::... . ............................. ............ .................. ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ PREPARED BY ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ LUNAR SURFACE OPERATIONS 0 FFICE ........... ............ ........... ............ ........... ............ ........... MISSION OPERATI.0NS BRANCH ............ ........... ............ ........... ............ ........... ............ ........... FLIGHT CREW SUPPORT DIVISION ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ JUNE 27,1969 ........... ............ ........... ............ ........... < ., : . , 11;';. , ,: a : , , . ', '. x .$., ~ *.~,:t.: ; . I + ,,,,---,, APOLLO 11 LUNAR SURFACE OPERATIONS PLAN M A N N E D SPACECRAFT C E N 1 HOUSTON.TEXAS ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... ............ ........... �FINAL EDITION APOLLO I1 LUNAR SURFACE OPERATIONS PLAN JUNE 13, 1969 Prepared by : w.. H . Wood, Jr. Lunar Surface operatio$. Off i c e Approved by : Lunar surflace Operations Off i c e H . A. Kuehnel Chief, Mission Operations Branch - C. H . Woodling \ \ Assistant Chief f o r Crew'Tra3,ning Chief, fight brew Support Division S~c33 k -. U ... . - Donald K . Slayton /\ Director of Flight( c ew Operations - -3 �APOLLO 11 LUNAR SURFACE OPERATIONS PLAN (FINAL EDITION) PREFACE This document h a s been prepared by t h e F l i g h t Crew Support D i v i s i o n , F l i g h t Crew Operations D i r e c t o r a t e , Manned S p a c e c r a f t C e n t e r , Houston, Texas. The i n f o r m a t i o n contained w i t h i n t h i s document r e p r e s e n t s t h e Lunar S u r f a c e Operations P l a n f o r Ap0110'11, t h e f i r s t planned l u n a r landing m i s s ion. T h i s i s t h e f i n a l e d i t i o n of t h e Apollo 11 Lunar S u r f a c e Operations P l a n . The p l a n i s under t h e c o n f i g u r a t i o n c o n t r o l of t h e Crew Procedures Control Board (CPCB) and a l l proposed changes t o t h i s document should b e submitted t o t h e CPCB v i a a Crew Procedures Change Request. Changes and comments t o t h e p l a n should b e d i r e c t e d t o W. H. Wood, Jr., Lunar S u r f a c e Operations O f f i c e , FCSD. �CONTENTS Page Preface iii L i s t of F i g u r e s and Tables vii 1.0 INTRODUCTION 1 2.0 MISSION PLAN 2.1 2.2 2.3 3.0 Mission Mission Summary 2.3.1 2.3.2 Purpose Description of Mission Requirements Introduction Mission Objectives and Experiments NOMINAL LUNAR EVA 3.1 3.2 3.3 3.4 3.5 Timeline D e s c r i p t i o n and R a t i o n a l e 3.1.1 Lunar Surface Stay 3.1.2 Extravehicular Activity Task and Data D e s c r i p t i o n s 3.2.1 Environmental F a m i l i a r i z a t i o n 3.2.2 Preliminary Checks 3.2.3 T e l e v i s i o n Coverage 3.2.4 S-band E r e c t a b l e Antenna Deployment 3.2.5 Photography 3.2.6 EVA and Environment E v a l u a t i o n 3.2.7 Sample C o l l e c t i o n s 3.2.8 LM I n s p e c t i o n 3.2.9 Experiment Deployments 3.2.10 Use of Lunar Equipment Conveyor 3.2.11 EVA Termination Summary Timeline Timeline D e t a i l e d Procedures 3.5.1 Nominal A c t i v i t i e s Sequence 3.5.2 Procedures �ALTERNATE AND CONTINGENT PLANS 4.1 4.2 4.3 A l t e r n a t e EVA (With S-band E r e c t a b l e Antenna ~ e p l o y m e n t ) 4.1.1 D e s c r i p t i o n and R a t i o n a l e 4.1.2 Summary T i m e l i n e 4.1.3 Timeline 4.1.4 D e t a i l e d Procedures C o n t i n g e n t EVA 1-Minimum Time, One Man 4.2.1 D e s c r i p t i o n and R a t i o n a l e 4.2.2 Summary T i m e l i n e 4.2.3 Timeline C o n t i n g e n t EVA 2-One Man, Two Hours 4.3.1 D e s c r i p t i o n and R a t i o n a l e 4.3.2 Summary T i m e l i n e 4.3.3 Timeline APPENDIX 5.1 5.2 5.3 5.4 5.5 Abbreviations D e t a i l e d O b j e c t i v e s and Experiments 5.2.1 Introduction 5.2.2 Definitions 5.2.3' Objectives 5.2.4 Experiments Lunar S u r f a c e O p e r a t i o n a l C o n s t r a i n t s 5.3.1 Introduction 5.3.2 Constraints Classification 5.3.2.1 Constraint Categories 5.3.2.2 Violation Classification 5.3.3 Mission O p e r a t i o n s C o n s t r a i n t s 5.3.4 Lunar S u r f a c e O p e r a t i o n s C o n s t r a i n t s 5.3.5 Equipment O p e r a t i o n C o n s t r a i n t s 5.3.6. Equipment Design C o n s t r a i n t s 5.3.7 General C o n s t r a i n t s Nominal Lunar S u r f a c e EVA M e t a b o l i c P r o f i l e s 5.4.1 Introduction 5.4.2 CDR M e t a b o l i c P r o f i l e 5.4.3 LMP M e t a b o l i c P r o f i l e References PAGE �FIGURES Figure Number Title Lunar s u r f a c e a c t i v i t y t i m e l i n e f o r 22-hour s t a y Radar coverage during l u n a r . s t a y f o r launch d a t e of J u l y 16 . TV f i e l d of view from MESA TV f i e l d of view from t r i p o d (with Lunar Day lens) Quad I i n s p e c t i o n p o i n t s Quad I1 i n s p e c t i o n p o i n t s Quad 111 i n s p e c t i o n p o i n t s Quad I V i n s p e c t i o n p o i n t s Probable a r e a s f o r l u n a r s u r f a c e a c t i v i t y TABLES Table No. 3- 1 Performance margins f o r LM communications 3-2 Loose equipment l e f t on l u n a r s u r f a c e vii Page , 12 �SECTION 1.0 INTRODUCTION �1.0 INTRODUCTION This final edition of the Lunar Surface Operations'Plan defines equipment requirements, crewlequipment interfaces, and final flight planning and crew activities for lunar surface EVA operations during the first manned lunar landing mission. This plan delineates how the lunar surface operational and scientific objectives for the first manned lunar landing mission will be accomplished through pre-mission timelining and procedures definition. Although the primary concern of this plan is the lunar surface EVA operational aspects of the mission, interface relationships are presented to provide clarity and continuity to the overall mission plan. The nominal plan is for a single two-man lunar excursion. The planned duration will be two hours and forty minutes or upon reaching a pre-determined red line on one of the PLSS consumable~. The red line is defined as having either a 30 minute supply of oxygen or a 30 minute supply of feedwater remaining after repressurization. The battery is not considered to be a constraint on the lunar surface time for this mission. Based on an estimation of each crewman's BTU expenditure to accomplish his respective EVA tasks, a PLSS expendable red line should not be reached during the EVA. The Commander is expected to expead approximately 3625 BTU's which will leave a 1175 BTU PLSS reserve or approximately 50 minutes Lunar surface time. (Metabolic profiles are presented in the Appendix, Section 5.4) In addition to the nominal timeline, the plan presents three other timelines for the lunar EVA. One timeline is referred to as an alternate timeline and two are referred to as contingent timelines. These timelines differ from the nominal primarily by additions or deletions of tasks. The major difference in the alternate timeline, from the nominal, is the addition of the S-band erectable antenna deployment which reduces the time available for the documented sample collection. The first contingent timeline, Contingent EVA 1, is a presentation of activities for a minimum-time, one-man EVA. The second contingent timeline, Contingent EVA 2, is for a one-man, two-hour EVA. . �The p l a n a l s o p r e s e n t s two forms of t i m e l i n e s . The l i n e s and a t i m e l i n e f o r t h e complete l u n a r s u r f a c e touchdown t o l i f t o f f , a r e i n summary form. Each of t i m e l i n e s i s a l s o p r e s e n t e d i n an expanded t i m e l i n e v i a t e d procedures form. EVA times t a y , from t h e EVA and abbre- D e t a i l e d procedures a r e included f o r t h e nominal l u n a r EVA. S i n c e t h e a l t e r n a t e t i m e l i n e , i n g e n e r a l , only adds t h e deployment of t h e e r e c t a b l e antenna and reduces t h e time f o r c o l l e c t i o n of a documented sample, d e t a i l e d procedures f o r t h e e n t i r e a l t e r n a t e EVA would b e redundant. Thus, only d e t a i l e d procedures f o r t h e S-band e r e c t a b l e antenna deployment a r e included. For t h e c o n t i n g e n t EVA'S, t h e t i m e l i n e s p r e s e n t t h e procedures i n s u f f i c i e n t d e t a i l t h a t , with a n understanding o r r e f e r e n c e t o t h e nominal procedures, s e p a r a t e procedures a r e unnecessary. �SECTION 2.0 MISSION PLAN �MISSION PLAN Mission Purpose The primary purpose of t h e Apollo 11 mission i s t ~ ' ~ e r f o r m a manned l u n a r landing and r e t u r n . Subordinate o b j e c t i v e s a r e t o perform l i m i t e d s e l e n o l o g i c a l i n s p e c t i o n , photography, survey, e v a l u a t i o n , and sampling during t h e l u n a r s t a y . Data w i l l b e obtained t o a s s e s s t h e c a p a b i l i t y and l i m i t a t i o n s of t h e a s t r o n a u t and h i s equipment i n t h e l u n a r environment. The accomplishment of t h e d e t a i l e d l u n a r s u r f a c e mission' o b j e c t i v e s and experiments w i l l c o n t r i b u t e a n e s s e n t i a l p a r. t . t o t h e success of t h e mission. 2.2 Mission Description This s e c t i o n provides a b r i e f summary of t h e major events f o r a J u l y 16, 1969 launch date. Launch t o Earth Orbit: The J u l y 16 mission w i l l allow a range of launch azimuths from 72 t o 108 degrees with a window opening a t 13:32:00 The s p a c e c r a f t (hr:min:sec) gmt f o r a d u r a t i o n of 4:24:00. w i l l b e i n s e r t e d i n t o an approximately 100 n a u t i c a l m i l e c i r c u l a r e a r t h parking o r b i t f o r s p a c e c r a f t checkout. Translunar I n j e c t i o n (TLI) : The J u l y window permits a P a c i f i c t r a n s l u n a r i n j e c t i o n . The S-IVB w i l l b e re-ignited during t h e second e a r t h p a r k i n g o r b i t t o provide t h e nominal i n j e c t i o n . Translunar Coast: Two hours a f t e r TLI, t h e CSM w i l l s e p a r a t e from t h e S-IV, transpose, dock and i n i t i a t e e j e c t i o n of t h e LM/CSM. P r i o r t o l u n a r o r b i t i n s e r t i o n (LOI), two a s t r o n a u t s w i l l e n t e r t h e LM, accomplish a l i m i t e d s t a t u s check, and r e t u r n t o t h e command module. �Lunar Orbit Insertion: The service module propulsion system will insert the spacecraft into an orbit of approximately 60 by 170 nautical miles. After two revolutions in this orbit for spacecraft system and orbit parameter checks, the orbit will be reduced to 66 by 54 nautical miles.. Lunar Module Descent: During the thirteenth orbit after the Lunar Orbit ~nsertion, LM/CSM undocking is accomplished in preparation for lunar landing. The powered descent maneuver is initialized at pericynthion of the descent transfer orbit. For the July 16 launch, the lunar landing will be at Site 2 (previously designated 11-P-6 and located at 0" 43' N, 23" 42' E). The range of sun elevation angles, for landing, will be from 10.5 to 13.5 degrees. Lunar Surface Operations: The planned lunar surface staytime is 22 hours. The nominal plan provides for a single, two-man EVA, with a duration of two hours and forty minutes. . . . Immediately after landing, the LM will be checked to assess its launch capability. After the post-landing checks, there will be a four hour rest period, with eat periods before and after, prior to preparation for EVA. Following the EVA and post-EVA activities, there will be another rest period, of four hours and forty minutes duration, prior to preparation for liftoff. In addition to the tasks required to successfully complete the landing and.ascent and the pre-EVA and post-EVA operations, the lunar surface activities will include the following major items in order of priority: 1) Photographs of the landing area through the LM cabin window. 2) Contingency sample collection. �3) EVA e v a l u a t i o n . 4) LM i n s p e c t i o n . 5) Bulk sample c o l l e c t i o n . 6) Deployment of experiments : Early Apollo . S c i e n t i f i c Experiments Package (S-031, Lunar P a s s i v e Seismology and S-078, Laser Ranging Retro-Reflector) and S-080, S o l a r Wind Composition. 7) Documented sample c o l l e c t i o n . Real time TV coverage w i l l b e provided e a r l y i n t h e EVA u s i n g t h e s t e e r a b l e antenna o r , i f r e q u i r e d , t h e e r e c t a b l e antenna. Both t h e Goldstone and Parkes 210-foot antennas w i l l b e u t i l i z e d as a v a i l a b l e . Photography w i l l b e employed throughout t h e EVA t o document t h e a c t i v i t i e s and o b s e r v a t i o n s . LM A s c e n t : During t h e LM l u n a r s u r f a c e s t a y , t h e CSM w i l l make t h e r e q u i r e d p l a n e change t o permit a nominally coplanar rendezvous. A f t e r LM a s c e n t and docking t o t h e CSM, t h e two crewmen w i l l t r a n s f e r t o t h e CSM w i t h exposed f i l m and samples of t h e l u n a r s u r f a c e . The CSM w i l l then j e t t i s o n t h e LM u s i n g t h e SM RCS. Transearth Injection: The s e r v i c e module p r o p u l s i o n system w i l l b e used t o b o o s t t h e CSM o u t of l u n a r o r b i t . The r e t u r n f l i g h t d u r a t i o n s h a l l n o t exceed 110 hours and t h e r e t u r n i n c l i n a t i o n s h a l l n o t exceed 40 degrees. Entry and Recovery: P r i o r t o atmospheric e n t r y , t h e command module w i l l b e s e p a r a t e d from t h e s e r v i c e module u s i n g t h e SM RCS. The nominal range from 400,000 f e e t a l t i t u d e t o touchdown s h a l l b e 1285 n a u t i c a l miles.. Touchdown w i l l be i n t h e P a c i f i c n e a r Hawaii approximately 11 days a f t e r launch from e a r t h . �P o s t Landing Operations: Following splashdown, t h e crew w i l l e g r e s s t h e CM a f t e r t h e f l o t a t i o n c o l l a r h a s been a t t a c h e d , don b i o l o g i c a l i s o l a t i o n garments, t r a n s f e r t o t h e recovery s h i p by h e l i c o p t e r and immediately e n t e r t h e Mobile Quarantine F a c i l i t y (MQF) They w i l l b e t r a n s p o r t e d i n t h e MQF t o t h e LRL a t MSC. The CM, sample r e t u r n c o n t a i n e r s , f i l m , t a p e s and a s t r o n a u t l o g s w i l l a l s o b e t r a n s p o r t e d t o t h e LRL. . I n o r d e r t o minimize t h e r i s k of contamination of t h e e a r t h ' s b i o s p h e r e by l u n a r m a t e r i a l , q u a r a n t i n e measures w i l l b e enforced. The crew w i l l b e q u a r a n t i n e d f o r approximately 2 1 days a f t e r l i f t o f f from t h e l u n a r s u r f a c e . 2.3 Summary of Mission Requirements 2.3.1 Introduction The f o l l o w i n g i n f o r m a t i o n i s from t h e "Mission Requirements SA-506lCSM-107lLM-5 G Type Mission, Lunar Landing", Dated A p r i l 17, 1969. (Revised May 1, 1969) The f o l l o w i n g s i n g l e primary mission o b j e c t i v e i s a s s i g n e d t o t h i s . m i s s i o n by t h e O f f i c e of Manned Space F l i g h t (OMSF): 1) Perform manned l u n a r l a n d i n g and r e t u r n . I n a d d i t i o n , t h e f o l l o w i n g s u b o r d i n a t e o b j e c t i v e s a r e del i n a t e d by OMSF: 1) P e r f orm s e l e n o l o g i c a l i n s p e c t i o n and sampling. 2) Obtain d a t a t o a s s e s s t h e c a p a b i l i t y and l i m i t a t i o n s of t h e a s t r o n a u t and h i s equipment i n t h e l u n a r s u r f a c e environment. F i n a l l y , t h e f o l l o w i n g experiments have been a s s i g n e d t o t h i s mission: 1) S-031 Lunar P a s s i v e Seismology 2) S-078 L a s e r Ranging Retro-Reflector �. . 3) S-080 S o l a r Wind Composition 4) S-151 Cosmic Ray Detection 5) T-029 P i l o t Describing Function . . . . . The Mission Requirements document i n c o r p o r a t e s t h e s e v a r i o u s o b j e c t i v e s and experiments, d e t a i l s them where necessary, and places them i n t h e proper order of p r i o r i t y , thereby providing t h e l e v e l of d e t a i l necessary f o r mission planning. The document n o t e s , however, t h a t : . There a r e no Detailed Objectives, a s such, which have been derived from t h e primary o b j e c t i v e of "perform manned l u n a r landing and return"., D e t a i l e d Objectives have, however, been derived from t h e two OMSF subordinate o b j e c t i v e s . The mission w i l l b e flown as an o p e r a t i o n a l mission i n t h e sense t h a t i t w i l l b e performed i n t h e most expeditious manner p o s s i b l e with no i n t e r f e r e n c e from s p e c i a l tests o r operations which a r e n o t necessary f o r t h e performance of t h i s b a s i c o b j e c t i v e . The manner i n which t h e detailed.performance of t h i s o b j e c t i v e i s met w i l l be contained i n t h e Mission Report. 2) Experiments a r e d e t a i l e d and p r i o r i t i e d i n t h e requirements document only when they a r e such a s t o r e q u i r e some a c t i o n by t h e crew o r otherwise impact t h e timeline. Thus, t h e Cosmic Ray Detection experiment, S-151, a passive experiment l i m i t e d t o p o s t mission a n a l y s i s of t h e f l i g h t helmets, is only mentioned and does n o t appear i n t h e p r i o r i t y list o r a s a detailed objective. S i m i l a r l y , ' t h e P i l o t Describing Function experiment, T-029, only r e q u i r e s c e r t a i n p o r t i o n s of voice and telemetry d a t a recordings and does n o t appear i n t h e l i s t of o b j e c t i v e s and experiments. The Detailed Objectives f o r t h e f i r s t l u n a r landing mission w i l l b e o b j e c t i v e s which concern equipment and crew o p e r a t i o n s only during t h e l u n a r surf ace phase of t h e mission. The c a p a b i l i t y t o s u c c e s s f u l l y complete o t h e r mission phases w i l l have been demonstrated on p r i o r missions. �Mission O b j e c t i v e s and Experiments .The f o l l o w i n g summary of l u n a r EVA o b j e c t i v e s and experiments i s i n o r d e r of p r i o r i t y , w i t h t h e o b j e c t i v e o r experiment of h i g h e s t p r i o r i t y l i s t e d f i r s t . The o r d e r of p r i o r i t y i s based upon t h e r e l a t i v e importance t o t h e Apollo s p a c e c r a f t development program o r t o t h e advancement of l u n a r s c i e n c e . The D e t a i l e d O b j e c t i v e s and Experiments a r e i n c l u d e d i n t h e Appendix, S e c t i o n 5.2. The o b j e c t i v e s " T e l e v i s i o n Coverage" and "Photographic Coverage" w i l l b e performed i n c o n j u n c t i o n w i t h s e v e r a l of t h e o t h e r obj e c t i v e s o r experiments. The a s s o c i a t e d o p e r a t i o n s w i l l t a k e p l a c e a t v a r i o u s p o i n t s i n t h e t i m e l i n e . Hence, t h e s e two ' o b j e c t i v e s cannot b e a s s i g n e d any s p e c i f i c p r i o r i t y i n t h e l i s t below and a r e t h e r e f o r e i n c l u d e d a t t h e end. Priority O b j e c t i v e s and Experiments 1 A Contingency Sample C o l l e c t i o n B Lunar S u r f a c e EVA Operations 3 C EMU Lunar Surface Operations 4 D Landing E f f e c t s on LM 5 E Lunar S u r f a c e C h a r a c t e r i s t i c s 6 F Bulk Sample C o l l e c t i o n 7 G Landed LM Location 8 H Lunar Environment V i s i b i l i t y 9 I Assessment of Contamination by Lunar M a t e r i a l 10 S-031 Lunar P a s s i v e Seismology 11 S-078 Laser Ranging Retro-Reflector 12 S-080 S o l a r Wind Composition �J Documented Sample C o l l e c t i o n K (Included i n Photographic Coverage, Change A, May 1, 1969) L T e l e v i s i o n Coverage M Photographic Coverage �SECTION 3.0 NOMINAL LUNAR EVA �' . 3.0 NOMINAL LUNAR EVA 3.1 Timeline D e s c r i p t i o n and Rationale 3.1.1 Lunar Surface Stay The nominal plan i s f o r two crewmen, t h e Commander and t h e Lunar Module P i l o t , t o remain on t h e l u n a r s u r f a c e f o r approximately 22 hours. During t h i s period, the'crew w i l l accomplish postlanding and pre-ascent procedures and e x t r a v e h i c u l a r a c t i v i t y . There w i l l be two r e s t and s e v e r a l e a t periods. A timeline f o r t h e l u n a r s u r f a c e s t a y i s presented i n Figure 3-1. There a r e s e v e r a l c o n s i d e r a t i o n s which a r e t h e b a s i s f o r t h e sequence of a c t i v i t y f o r t h e l u n a r s u r f a c e s t a y . An e a r l y r e s t peiod i s planned which w i l l provide r e s t b e f o r e t h e strenuous pre-EVA, EVA, and post-EVA a c t i v i t i e s and i n s u r e t h e work day i s n o t p r o h i b i t i v e l y long i f l i f t o f f i s req u i r e d b e f o r e t h e o t h e r planned r e s t period. A second r e s t p e r i o d of f o u r hours and f o r t y minutes i s provided a f t e r t h e EVA b e f o r e t h e c r u c i a l l i f t o f f and rendezvous sequence. 3.1.2 - Extravehicular A c t i v i t y The f i r s t l u n a r EVA i s designed t o maximize t h e r e t u r n of s c i e n t i f i c and o p e r a t i o n a l data. However, t h e t i m e l i n e permits r e s t periods and a gradual i n c r e a s e i n t a s k complexity w i t h simple t a s k s i n i t i a l l y f o r crew acclimation and PLSS-EMU data analysis. There w i l l be two major a r e a s of e v a l u a t i o n during t h e l u n a r s u r f a c e EVA. The f i r s t concern i s with comprehensive crew f a m i l i a r i z a t i o n and e v a l u a t i o n of EVA c a p a b i l i t y and t h e l u n a r environment. The i n v e s t i g a t i o n w i l l b e a methodical approach which w i l l enhance t h e accomplishment of t h i s EVA a s w e l l a s demonstrate a s t r o n a u t and equipment c a p a b i l i t y f o r f u t u r e l u n a r s u r f a c e e x p l o r a t i o n . The second a r e a is t h e c o l l e c t i o n of o p e r a t i o n a l and s c i e n t i f i c data. The a n a l y s i s of t h i s d a t a w i l l a s s i s t i n t h e update of equipment designs a s ' w e l l a s i n c r e a s e our general understanding of t h e l u n a r s u r f a c e . The f i r s t few minutes of t h e EVA; t h e Lunar Module P i l o t (LMP) w i l l remain i n s i d e t h e LM a s c e n t s t a g e t o monitor t h e Commander's (CDR) s u r f a c e a c t i v i t y and t h e LM systems i n t h e �' depressurized state. The CDR will descend to the lunai surface to conduct several preliminary tasks. He will determine . his ability to operate in the lunar environment; collect a contingency lunar sample and take still color photographs (with an electric 70mm camera) as he checks the LM . and the lunar surface condition which affect the accomplishment of the EVA tasks. In addition to the TV coverage and still photographs, the LMP can visually observe and obtain sequence camera (data acquistiion) coverage to supplement the documentation of the CDR activity. With only one crewman on the surface during the first few minutes of the EVA, a more effective PLSS telemetry data analysis can be conducted. The real time use rate for the PLSS consumables will be compared with the predicted rate to determine the PLSS capability for'EVAcontinuation. After the CDR accomplishes the preliminary EVA tasks, the LMF' will descend to the surface and spend a few minutes in the familiarization and evaluation of his capability or limitations to conduct further operations in the lunar environment. After this short period of time he will deploy the Solar Wind Composition (SWC) experiment. The CDR, after photographing the LMPts egress and descent to the surface, will remove the TV camera and tripod from the descent for stage modularized equipment stowage assembly (MESA) and move them to a position for optimum coverage of the subsequent surface EVA operations. Then, while the CDR collects a bulk sample of lunar surface material, the LMP will continue to become more familiar with his ability to operate in the lunar environment as he conducts the EVA and Environment Evaluation. The LMP begins the LM inspection and is joined by the CDR after the bulk sample has been collected. When the crewmen reach the scientific equipment (SEQ) bay in Quad 11, the LMP removes the Early Apollo Scientific Experiments Package (EASEP) as the CDR completes the LM inspection and photographically documents the LMP's activity. After they deploy the EASEP, the crew will select, describe, photograph, and collect samples until they terminate the EVA. In summary, there is a general increase in task complexity for both crewmen. The conservative timeline permits the crew to follow a slow, methodical approach in accomplishing each task. Additionally, the frequent rest periods within �Figure 3 - 1 rum scrlr )r,Ono f:LY."ct KCM !LY Q -;I -2 IM MRS. -13 w fZccml UIPOSKIIC V . 4 UI COYWLMEU k PILOT ACTIVITY <> T I M SCAlr IYHRS.-3 -:z 'I 0 A TO~W W N OYISIDI lWlNEml .C*ICKWI ~CO C II~C IV 4 w wurcff n s m n C l U L C10lI C M l W U l D l H A M 1 OI?RESS O e t t P L t E E W I P U f I l PC4 J E I I I S O I Y Y P L C CDLLECllm OREIIYIUtVCMCCIS . S d l l D I ~ 1 t I M D C I L O V Y I ~ l U L l E * M l E ISYC LINE1 O L Y I I#IlUL CVAA.OEWIOYEIl4L CAY. 01" .I0 s 1 C OIPLWY.1 OW. E I V l t O l f I1W U W I I O I .-LI Y Y I L E COLLCCIDI U I IISP(ClIO# .EASE, OCPLOVYE*I *XXUYE#lCO Y Y P L E ICM U I SUT I 111EGtllV .Jf111SOm EWI* ~ S l A B L I S *c.11" I.1ICtllV �LUNAR SURFACE ACTIVITY TIMELINE FOR 22 HOUR STAY 1 tuaw ! t I i t srArus cmm 1I WRM U CLfll 8 ?~~CWnWllW I 1 061VE GO $01 RE51 �t h e timeline add t o t h i s conservatism and i n s u r e t h a t each crewman and h i s PLSS remain i n a nominal o p e r a t i n g condition. However, should t h e EVA b e terminated a t any p o i n t i n t h e t i m e l i n e , t h e maximum d a t a r e t u r n f o r t h e t i m e spent on t h e . s u r f a c e w i l l be assured. Task and Data Descriptions Although t h e d e t a i l e d procedures d e s c r i b e t h e s t e p s t o ac- ,complish each t a s k , f u r t h e r explanation of t h e d e s i r e d d a t a and d a t a c o l l e c t i o n processes is d e s i r a b l e . 3.2.1 Environmental F a m i l i a r i z a t i o n A s mentioned previously, t h e t i m e l i n e considerations f o r t h e l u n a r s u r f a c e e x t r a v e h i c u l a r a c t i v i t y w i l l permit a slow buildup of t a s k complexity t o i n s u r e thorough crew f a m i l i a r i z a t i o n with t h e l u n a r environment y e t optimize t h e d a t a r e t u r n . The approach with which t h e crewmen w i l l proceed w i l l permit them t o adapt t o t h e environment while determining t h e ease o r d i f f i c u l t y which they can expect through o u t t h e EVA. The f i r s t crewman t o e g r e s s , a f t e r determining h i s i n i t i a l EVA c a p a b i l i t y , can a d v i s e t h e second crewman on what t o expect and possibly suggest methods t o accomplish t h e a d d i t i o n a l t a s k s . Both crewmen's experiences w i l l b e invaluable f o r p r e d i c t i n g crew c a p a b i l i t y on f u t u r e l u n a r s u r f a c e explorations. Once on t h e s u r f a c e , t h e CDR w i l l move slowly from t h e footpad t o check h i s balance and determine h i s a b i l i t y t o cont i n u e with t h e EVA--the a b i l i t y t o move and t o s e e o r , s p e c i f i c a l l y , t o perform t h e s u r f a c e operations w i t h i n t h e c o n s t r a i n t s of t h e EMU and t h e l u n a r environment. Although a more thorough e v a l u a t i o n and documentation of a.crewmanls c a p a b i l i t i e s w i l l occur l a t e r i n t h e timeline, t h i s i n i t i a l f a m i l i a r i z a t i o n w i l l a s s u r e t h e CDR t h a t h e and t h e LMP a r e capable of accomplishing t h e assigned EVA t a s k s . Also, should i t be necessary t o unexpectedly terminate t h e EVA p r i o r t o f u r t h e r environment evaluation, t h i s e a r l y famili a r i z a t i o n w i l l i n s u r e some d a t a r e t u r n on EVA c a p a b i l i t y and t h e l u n a r s u r f a c e p r o p e r t i e s . �. 3.2.2 . P r e l i m i n a r y Checks For t h e P r e l i m i n a r y Checks t h e CDR w i l l t r a n s f e r t h e 70mm . EL Data.camera t o t h e s u r f a c e , conduct a b r i e f LM check and a p r e l i m i n a r y e v a l u a t i o n of t h e l u n a r environment. The Hasselblad camera w i l l e n a b l e t h e CDR t o t a k e s t i l l c o l o r photographs t o supplement t h e sequence ( d a t a a c q u i s i t i o n ) camera photography which t h e LMP w i l l a t t a i n through t h e LM a s c e n t s t a g e window t o document.the s u r f a c e a c t i v i t y . A b r i e f check of t h e LM s t a t u s i s a simple t a s k which can b e used t o extend t h e CDR's environment f a m i l i a r i z a t i o n . and, a t t h e same time, p r o v i d e an important c o n t r i b u t i o n ' t o t h e p o s t f l i g h t assessment of t h e LM l a n d i n g should a . f u l l o r nominal LM i n s p e c t i o n n o t b e accomplished l a t e r . The p r e l i m i n a r y e v a l u a t i o n of t h e c o n d i t i o n s which w i l l . i n f l u e n c e t h e crewmen's s u r f a c e o p e r a t i o n s , such a s t h e t e r r a i n s u r f a c e f e a t u r e s and l i g h t i n g o r v i s i b i l i t y , w i l l a l s o enhance t h e CDR's environmental f a m i l i a r i z a t i o n 'as w e l l a s h i s assessment of an a s t r o n a u t ' s c a p a b i l i t y t o accomplish EVA t a s k s . From a p o s i t i o n n e a r t h e l a d d e r t h e CDR w i l l make a g e n e r a l i n s p e c t i o n of t h e LM and s u r f a c e about t h e LM. For t h e LM and s u r f a c e v i s i b l e t o him, h e w i l l b r i e f l y examine t h e g e a r s t r u t s , f o o t p a d s , and major p a r t s of t h e s p a c e c r a f t t o a s s u r e t h a t t h e LM i s s t a b l e and w i l l provide a s a f e o p e r a t i o n s b a s e f o r t h e l u n a r s t a y . An i n s p e c t i o n of t h e s u r f a c e w i l l prov i d e p r e l i m i n a r y d a t a on t h e LM e f f e c t on t h e s u r f a c e d u r i n g t h e landing. 3.2.3 TV Coverage The primary purpose of t h e TV i s t o provide a supplemental r e a l time d a t a s o u r c e t o a s s u r e o r enhance t h e s c i e n t i f i c and o p e r a t i o n a l d a t a r e t u r n . It may b e a n a i d i n d e t e r mining t h e e x a c t LM l o c a t i o n on t h e l u n a r s u r f a c e , i n e v a l u a t i n g t h e EMU and man's c a p a b i l i t i e s i n t h e l u n a r environment and i n documenting t h e sample c o l l e c t i o n s . The TV w i l l b e u s e f u l i n p r o v i d i n g continuous o b s e r v a t i o n f o r time c o r r e l a t i o n of crew a c t i v i t y w i t h t e l e m e t e r e d d a t a , v o i c e comments, and photographic coverage. �TV r e c e p t i o n , w i t h o u t a d e g r a d a t i o n of b o t h v o i c e and t e l e metered i n f o r m a t i o n , may b e dependent on having t h e LM s t e e r a b l e S-band antenna r a d i a t e t o a 210-foot antenna, e i t h e r t h e Goldstone ( C a l i f o r n i a ) o r t h e Parkes ( A u s t r a l i a ) antenna, o r deploy t h e S-band e r e c t a b l e antenna on t h e l u n a r s u r f a c e . (A comparison of t h e performance expected w i t h t h e 210-foot/ s t e e r a b l e antennas o r 8 5 - f o o t / e r e c t a b l e antennas i s p r e s e n t e d i n T a b l e 3-1 on t h e f o l l o w i n g page.) The e r e c t a b l e antenna makes i t p o s s i b l e t o r e c e i v e TV t r a n s m i s s i o n s w i t h t h e 85-foot antenna d i s h e s a t e i t h e r Goldstone, Madrid, o r Canberra, which a r e e q u i v a l e n t t o t h e 2 1 0 - f o o t / s t e e r a b l e combination. I f a 210-foot antenna i s n o t i n view o r t h e e r e c t a b l e antenna has n o t been deployed, TV coverage may b e o b t a i n e d by a c c e p t i n g t h e l o s s ' o r d e g r a d a t i o n of v o i c e a n d t e l e m e t r y . The f i n a l d e c i s i o n f o r such coverage w i l l b e made i n r e a l t i m e and based on t h e q u a l i t y of t h e communications up t o . . that point. . . ' .:. - For t h e nominal mission, w i t h a J u l y 16 launch d a t e , t h e Goldstone and/or t h e Parkes antennas w i l l b e i n v i e w ' d u r i n g t h e EVA. The coverage provided by t h e 210-foot and 85-foot antennas d u r i n g t h e l u n a r s t a y i s shown i n ~ i g u r e . 3 - 2 . The TV camera w i l l have two primary p o s i t i o n s ' o r f i e l d s of view . f o r coverage of t h e s u r f a c e ' a c t i v i t y . The camera w i l l b e mounted i n ' t h e descent s t a g e Modularized Equipment Stowage Assembly (MESA) t o view ' t h e crewmen's d e s c e n t t o t h e s u r f a c e and t h e CDR's ' a c t i v i t y i n t h e immediate l a d d e r a r e a . (See Figure 3-3). A f t e r t h e LMP'S descent t o ' t h e s u r f a c e , t h e CDR removes t h e camera and t r i p o d from t h e MESA and p l a c e s t h e t r i p o d w i t h camera on t h e s u r f a c e i n an optimum p o s i t i o n ' f o r coverage of subsequent s u r f a c e a c t i v i t y . (See F i g u r e 3-4). �TABLE 3-1 (EM .Mode -~ i Power) ~ h 210 '. MARS STAT1ON 85' MSFN STATION NOMINAL WORST CASE NOMINAL WORST CASE +15.4 +25.4 +23.4 + 7.2 + 1.8 +17.2 +15.2 +11.8 + 9.8 + 7.7 +17.7. E r e c t a b l e Antenna + 8.8 + 9.2, 51.2 kbps Telemetry*" . . EVA Voice (dual) dB EVA EKG & PLSS Data (dual) +.3.8 . . + 9.7 . . T e l e v i s i o n (B&W) . 1.6 kbps Telemetry** +17.4 EVA Voice (dual) + 9.2 + 3.8 + 9.7 EVA EKG & PLSS Data . (dual) ~ e l e v ii so n (B&w) ' S t e e r a b l e Antenna . . . . 51.2 kbps Telemetry** .' EVA Voice (dual) EVA EKG & PLSS Data (dual) + 0.7 - + 1.1 - 4.3 - 1.1 - 6.5 - 0.6 +7.1 EVA Voice (dual) EVA EKG & PLSS Data (dual) - .4.3 - 6.5 T e l e v i s i o n (B&W) + 1.6 - 0.6 1.6 kbps' Telemetry** . . +17.3 + 3.7 + 9.6 +'6.5 + 6.9 . + 1.5 + 7.4 ' +15.1 + 1.5 + 7.4 ' . Based on measured LM-5 'data and MSC t e s t . d a t a on new. (1969) Motorola FM demodulator. The MSC t e s t s were conducted i n t h e ISD E l e c t r o n i c Systems T e s t F a c i l i t y (on one u n i t ) . ' ** + 8.7 + 9.1 + 3.7 + 9.6 1.5 + 1.6 + 9.3 + 1.1 T e l e v i s i o n . (B&W) * +15.7 . For a BER bf . . 16 ' �-16 . 0 .20 J U I 20 ~ 4 8 12 J U ~ Y21 16 20 Greenwich mean time, G a t .~ . . hr. : Figure 3-2.'- Radar coverage during lunar stay f o r launch date of July 16. 0 4 JU~Y 22 �"Z" - plane - / ~ i e wnormal cenl:er line Figure 3-3. - TV field of view from MESA. 18 �Figure 3-4 .-TV field of view from tripod (with Lunar day lens) 18a �3.2.4 S-Band E r e c t a b l e Antenna Deployment ( A l t e r n a t e Timeline) The S-band e r e c t a b l e antenna w i l l be deployed t o i n c r e a s e t h e communications c a p a b i l i t y . I t ' s major impact t o t h e EVA i s i n o b t a i n i n g an e q u i v a l e n t communications c a p a b i l i t y t h a t w i l l b e p o s s i b l e otherwise only i f a 210-foot antenna i s i n view. This communications c a p a b i l i t y may be r e q u i r e d f o r simultaneous TV, v o i c e , and t e l e m e t e r e d d a t a r e t u r n . (See t h e d i s c u s s i o n on t h i s s u b j e c t i n t h e previous s e c t i o n on TV coverage, S e c t i o n 3.2.3). ' . ,, . 3.2.5 The deployment of t h e e r e c t a b l e antenna i s a time-consuming task--deployment time i s expected t o be 19 minutes. However, t h e TV c o v e r a g e , ' w i t h o u t a d e g r a d a t i o n of v o i c e and t e l e m e t r y , gained through t h e use of t h e antenna may r e q u i r e i t t o be deployed. I n t h i s s i t u a t i o n , although i t i s d e s i r a b l e t o a t t a i n t h i s advantage provided by t h e antenna and t o p e r m i t t h e crewman i n s i d e t h e LM t o switch t o t h e e r e c t a b l e antenna e a r l i e r i n t h e t i m e l i n e , t h e crewman's f a m i l i a r i z a t i o n w i t h l u n a r o p e r a t i o n s b e f o r e t h i s p o i n t i s considered t o b e i n s u f f i c i e n t t o s a f e l y and e f f e c t i v e l y accomplish the' deployment task. Photography photography, s t i l l c o l o r photographs w i t h t h e 70mm EL d a t a camera, close-up s t e r e o photographs w i t h t h e Apollo Lunar S u r f a c e Close-up Camera (ALSCC), and motion p i c t u r e s w i t h t h e 16mm ( d a t a a c q u i s i t i o n ) camera, w i l l be a v i t a l p a r t of t h e d a t a c o l l e c t i o n p r o c e s s f o r t h e EVA. A 70mm camera, w i t h b l a c k and w h i t e f i l m , w i l l b e used f o r ' s u r f a c e photography from t h e LM and w i l l b e t r a n s f e r r e d t o ' t h e s u r f a c e . . i f a m a l f u c t i o n of t h e o t h e r camera occurs. . . The crewmen w i l l u s e t h e EL d a t a camera e x t e n s i v e l y on t h e s u r f a c e t o document each major t a s k which they accompl i s h . A d d i t i o n a l photography, such a s panoramas and s c i e n t i f i c documentation, w i l l supplement o t h e r d a t a i n t h e p o s t f l i g h t a n a l y s i s of t h e l u n a r environment and t h e a s t r o n a u t ' s c a p a b i l i t i e s o r l i m i t a t i o n s on conducting l u n a r s u r f a c e o p e r a t i o n s . With t h e ALSCC t h e crewmen may photograph a r e a s of , t h e l u n a r surface not disturbed during t h e landing o r surface a c t i v i t y , t h e i r f o o t p r i n t s , a r e a s a f f e c t e d by t h e LM footpads and t h e s c i e n t i f i c equipment, and o t h e r phenomena of o p e r a t i o n a l and' scientific interest. �The sequence camera, from t h e LM a s c e n t s t a g e window, w i l l p r o v i d e almost continuous coverage of t h e s u r f a c e a c t i v i t y . The Lunar Module P i l o t , who remains i n s i d e t h e a s c e n t s t a g e f o r t h e f i r s t few minutes of t h e EVA, w i l l u s e t h e seauence camera t o document t h e Commander's i n i t i a l s u r f a c e a c t i v i t i e s . Then, b e f o r e h e e g r e s s e s , t h e LMP w i l l p o s i t i o n t h e camera f o r optimum s u r f a c e coverage w h i l e b o t h crewmen a r e on t h e s u r f a c e . And, a f t e r t h e LMP i n g r e s s e s , h e can u s e t h e sequence camera t o p r o v i d e coverage of t h e remaining s u r f a c e activity. A complete d e s c r i p t i o n of t h e camera equipment and t h e i r operat i o n a l procedures, a s w e l l as t h e d e t a i l s of t h e documentation provided by t h e t h r e e cameras, a r e contained i n Reference 6 . 3.2.6 EVA and Environment Evaluation The primary purpose of t h e Environmental F a m i l i a r i z a t i o n p e r i o d , e a r l y i n t h e t i m e l i n e , i s t o allow t h e crew s u f f i c i e n t time t o adapt t o t h e new environment and o p e r a t i n g c o n d i t i o n s . The EVA and Environment E v a l u a t i o n , however, i n v o l v e s a d e t a i l e d i n v e s t i g a t i o n and documentation of a crewman's c a p a b i l i t y w i t h i n t h e c o n s t r a i n t s of t h e EMU, t h e PLSSIEMU performance under v a r y i n g c o n d i t i o n s of s u n l i g h t , shadow, crewman a c t i v i t y o r i n a c t i v i t y , and t h e c h a r a c t e r i s t i c s of t h e l u n a r environment which i n f l u e n c e o p e r a t i o n s on t h e s u r f a c e . The p r e l i m i n a r y f a m i l i a r i z a t i o n w i l l be of t h e most b e n e f i t i n r e a l time--to p r e p a r e t h e crewmen t o o p e r a t e d u r i n g t h i s EVA. On t h e o t h e r hand, t h e EVA and Environment E v a l u a t i o n p e r i o d should b e of s i g n i f i c a n t v a l u e f o r f u t u r e l u n a r s u r f a c e e x p l o r a t i o n . From t h e assessment of d a t a g a t h e r e d d u r i n g t h i s p e r i o d , s u f f i c i e n t knowledge should b e gained t o acc u r a t e l y p r e d i c t t h e c a p a b i l i t i e s and l i m i t a t i o n s of t h e a s t r o n a u t and h i s equipment f o r f u t u r e l u n a r s u r f a c e e x t r a vehicular activity. During t h e EVA and Environment E v a l u a t i o n t h e LMF w i l l determine, i n d e t a i l , t h e combined e f f e c t s of t h e EMU c o n s t r a i n t s and l u n a r g r a v i t y on h i s p h y s i c a l c a p a b i l i t i e s . H e w i l l compare h i s c a p a b i l i t i e s i n t h i s l u n a r environment w i t h s i m i l a r experiences d u r i n g e a r t h g r a v i t y and s i m u l a t e d l u n a r g r a v i t y e x e r c i s e s . He w i l l observe how t h e l u n a r s u r f a c e i s a f f e c t e d by t h e a c t i o n s he performs and c a r e f u l l y examine . t h e t e r r a i n t o determine t h e s u r f a c e c h a r a c t e r i s t i c s . Also, h e w i l l determine h i s v i s u a l p e r c e p t i o n of t h e s u r f a c e f e a t u r e s and h i s v i s u a l a c u i t y w i t h i n t h e c o n s t r a i n t s of t h e e x t r a v e h i c u l a r v i s o r assembly (EWA). �3.2.7 Sample Collections The nominal plan is to conduct three sample collections of lunar surface material. They are, in order of priority, the contingency, the bulk, and the documented sample collections. The contingency sample collection is a simple task which can be accomplished within a few minutes early in the EVA timeline. This will assure the'return of a small sample in a contingency situation where a crewman may remain on the surface for only a short period of time. One to two kilograms .of loose material will be collected near the LM ladder and the sample bag restowed in the suit pocket to be carried into the ascent stage when the crewman ingresses. In the bulk sample collection at least 10 kilograms of unsorted surface debris and selected rock chunks'willbe placed in a special container, an Apollo Lunar Sample Return Container (sRC), to provide a near vacuum environment for its Apollo return to the Lunar Receiving Laboratory (LRL). Lunar Handtools (ALHT), stowed in the MESA with the SRC, will be used to collect this large sample (30 to 60 pounds) of loose lunar material from the surface near the MESA in Quad IV of the LM. As each rock sample or scoop of loose material is collected it will be placed into a large sample bag. Placing the sealed bag, rather than the loose material directly into the SRC, also prevents contamination and possible damage to the container seals. The documented sample collection, like that of the bulk sample collection, will involve a large mass of lunar material placed into an SRC for return to earth: However, the documented sample will differ significantly in content and in its collection process. As the name implies the documented sample collection will involve the documentation of the individual samples and the area from which they are taken. It can be classified as a very limited lunar field geology investigation. �Within t h e documented sample c o l l e c t i o n a core t u b e sample i s f i r s t c o l l e c t e d t o p r o v i d e an a s e p t i c and s t r a t i f i e d sample n e a r t h e LM. A t a s i t e r e p r e s e n t a t i v e o f . t h e l a n d i n g a r e a , t h e crew w i l l examine, d e s c r i b e , photograph, and c o l l e c t rock fragments and l o o s e s u r f a c e m a t e r i a l samples and p l a c e them i n d i v i d u a l l y i n pre-numbered bags. ' T h e samples, i n t h e s m a l l bags numbered one through f o u r t e e n , a r e placed i n a l a r g e bag f o r t r a n s f e r t o and stowage i n t h e documented sample SRC. I f time p e r m i t s a f t e r c o l l e c t i n g t h e s m a l l bags of samples, t h e crew w i l l c o l l e c t two environment samples, r e p r e s e n t a t i v e of t h e b u l k sample, and a second c o r e t u b e sample. Additiona l l y , t h e l a r g e sample bag w i l l be f i l l e d , a s t h e b u l k sample bag, t o r e t u r n t h e maximum amount of s u r f a c e m a t e r i a l . The v a r i o u s samples w i t h i n t h e documented sample c o l l e c t i o n w i l l b e t a k e n from a r e a s n e a r t h e LM o u t t o p o s s i b l y 300 f e e t away. Although t h e l i m i t i n g d i s t a n c e from t h e LM f o r t h i s f i r s t s u r f a c e mission i s 300 f e e t , t h e r e a r e s e v e r a l reasons f o r t h e crew t o remain w i t h i n 100 f e e t . F i r s t , s i n c e t h e documented sample c o l l e c t i o n w i l l b e l a t e i n t h e EVA, t h e c a p a b i l i t y of t h e crew and t h e i r equipment w i l l b e l i m i t e d a t t h i s time. A d d i t i o n a l l y , on t h i s f i r s t l a n d i n g mission a r e l a t i v e l y cons e r v a t i v e approach i s necessary. Also, i t i s u n l i k e l y t h a t t h e t e r r a i n a t 300 f e e t w i l l be s i g n i f i c a n t l y d i f f e r e n t from t h e t e r r a i n w i t h i n 100 f e e t of t h e LM. 3.2.8 Lunar Module I n s p e c t i o n The purpose of t h e LM i n s p e c t i o n i s t o v i s u a l l y check and p h o t o g r a p h i c a l l y document t h e e x t e r n a l c o n d i t i o n of t h e LM a f t e r t h e f l i g h t t o t h e l u n a r s u r f a c e and t h e e f f e c t s of t h e LM l a n d i n g on t h e l u n a r s u r f a c e . The i n s p e c t i o n d a t a w i l l b e used t o v e r i f y t h e LM a s a s a f e and e f f e c t i v e v e h i c l e f o r l u n a r e x c u r s i o n s . The d a t a w i l l a l s o b e used t o g a i n more knowledge of t h e l u n a r s u r f a c e c h a r a c t e r i s t i c s . I n g e n e r a l ' t h e b e n e f i t of t h e . i n s p e c t i o n w i l l s e r v e t o advance t h e equipment d e s i g n and our understanding of t h e environment i n which i t operates. The crewmen w i l l methodically i n s p e c t and r e p o r t t h e s t a t u s of a l l e x t e r n a l p a r t s and s u r f a c e s of t h e LM which a r e v i s i b l e t o them. They w i l l examine t h e l u n a r s u r f a c e about t h e LM t o determine t h e i n t e r a c t i o n s of t h e LM footpads w i t h t h e l u n a r s o i l f o r s t u d y of t h e l u n a r s u r f a c e p r o p e r t i e s . The s t i l l c o l o r �photographs w i t h t h e Hasselblad and closeup cameras, w i l l supplement t h e i r v i s u a l documentation f o r p o s t f l i g h t engineeri n g a n a l y s i s and d e s i g n v e r i f i c a t i o n . They w i l l observe and photograph t h e Reaction C o n t r o l System (RCS) e f f e c t s on t h e LM, t h e l a n d i n g g e a r performance, t h e i n t e r a c t i o n s of t h e s u r f a c e and f o o t p a d s , and t h e Descent P r o p u l s i o n System (DPS) e f f e c t s on t h e s u r f a c e a s w e l l a s t h e g e n e r a l c o n d i t i o n of a l l . quadrants and l a n d i n g s t r u t s . (Refer t o F i g u r e s 3-5, 3 - 6 , 3-7, and 3-8 f o r t h e major LM i n s p e c t i o n p o i n t s .) 3.2.9 Experiment Deployments . . There a r e t h r e e s c i e n t i f i c experiments which w i l l ' b e deployed. The S o l a r Wind composition (SWC) experiment deployment, although of lowest p r i o r i t y , i s accomplished f i r s t a s i t is a s i m p l e t a s k and t h e r e s u l t s depend on t h e exposure time. A t l e a s t a n hour of exposure time i s d e s i r e d b e f o r e i t is p l a c e d i n a n SRC f o r r e t u r n t o e a r t h . The o t h e r two experiments, t h e P a s s i v e Seismic (PSE) and L a s e r Ranging R e t r o - r e f l e c t o r (LR3), a r e deployed l a t e r b u t w i l l c o n t i n u e t o r e t u r n d a t a a f t e r t h e mission. The SWC c o n s i s t s of a p a n e l of very t h i n aluminum f o i l r o l l e d and assembled i n t o a combination h a n d l i n g and deployment c o n t a i n e r . It i s stowed i n t h e MESA. Once t h e thermal b l a n k e t i s removed from around t h e ~ S equipment A i t is a s i m p l e t a s k t o remove t h e SWC, deploy t h e s t a f f and t h e f o i l "window shade", and p l a c e i t i n d i r e c t s u n l i g h t where t h e f o i l w i l l b e exposed t o t h e s u n ' s r a y s . The SWC i s designed t o e n t r a p n o b l e gas c o n s t i t u e n t s of t h e s o l a r wind, s u c h ' a s Helium, Neon, Argon, Krypton and Xenon. The f o i l is . l a t e r r o l l e d up, removed from t h e s t a f f , and placed i n an SRC. I f i t i s known a t t h e time t h e b u l k sample SRC i s packed t h a t a documented sample w i l l n o t b e c o l l e c t e d , t h e SWC w i l l b e p l a c e d i n t h e b u l k sample SRC. I f t h e b u l k sample SRC h a s been s e a l e d b e f o r e d e c i d i n g n o t t o c o l l e c t t h e documented sample t h e SWC may b e p u t i n t o t h e LMP's s u i t pocket f o r t r a n s f e r t o t h e a s c e n t s t a g e . A t t h e same t i m e t h e f o i l i s recovered, t h e a s t o n a u t w i l l push t h e s t a f f i n t o t h e l u n a r s u r f a c e t o determine, f o r p o s t f l i g h t s o i l mechanics a n a l y s i s , t h e depth of p e n e t r a t i o n . �Pad and surface descent stage Figure 3-5. - Quad I inspection points. Figure 3-6. - Quad II inspection points. 24 �S-band steerable antenna :ation Oxidizer pressurization Figure 3-7. - Quad III inspection points. S-band DPS effects on surface Figure 3-8. . - Quad I37 inspection points. �The PSE, o r t h e PSE package (PSEP), is one of two packages of t h e E a r l y Apollo S c i e n t i f i c Experiments Package (EASEP). It w i l l b e p l a c e d on t h e l u n a r s u r f a c e t o monitor l u n a r seismic a c t i v i t y and d e t e c t meteriod impacts, f r e e o s c i l l a t i o n s of t h e moon, and l u n a r i n t e r n a l a c t i v i t y . It may a l s o d e t e c t s u r f a c e deformations and v a r i a t i o n s of e x t e r n a l g r a v i t a t i o n a l f i e l d s a c t i n g on t h e moon. Data from t h i s s e l f c o n t a i n e d , solar-powered experiment package s h o u l d r e v e a l t h e p r o p e r t i e s of t h e s e i s m i c e v e n t s , t h e p h y s i c a l p r o p e r t i e s of t h e s u b s u r f a c e m a t e r i a l s , and t h e g e n e r a l s t r u c t u r e of t h e lunar interior. The LR3 i s a l s o one of t h e two EASEP packages. The package p r o v i d e s a c o r n e r r e f l e c t o r ( a c t u a l l y a n a r r a y of 100 r e f l e c t o r s ) f o r l a s e r ranging from e a r t h . From t h i s experiment t h e n a t u r e of t h e e a r t h ' s i r r e g u l a r r o t a t i o n may b e determined. Also, t h e d a t a w i l l h e l p r e f i n e t h e l u n a r motions and t h e r e l a t i v e motion of t h e e a r t h and moon. The PSEP and LR3 a r e on s e p a r a t e p a l l e t s which a r e stowed i n ' t h e S c i e n t i f i c Experiment (SEQ) bay of t h e d e s c e n t s t a g e Quad 11. I n t h e nominal deployment t h e LMP removes b o t h packages and c a r r i e s them t o t h e deployment s i t e simultaneously. 15 degrees The,crewmen w i l l s e l e c t a l e v e l s i t e , nominally w i t h i n of t h e LM -Y a x i s and 70 t o 110 f e e t from t h e LM. The s e l e c t i o n of t h e s i t e i s based on a compromise between a s i t e which minimizes t h e e f f e c t s of t h e LM a s c e n t e n g i n e d u r i n g l i f t o f f h e a t and contamination by d u s t and i n s u l a t i o n d e b r i s (kapton) from t h e LM d e s c e n t s t a g e , and a convenient s i t e n e a r t h e SEQ bay. + 3.2.10 U s e of t h e Lunar Equipment Conveyor The Lunar Equipment Conveyor (LEC) i s a d e v i c e which t h e a s t r o n a u t s w i l l u s e d u r i n g t h e EVA t o t r a n s f e r equipment t o o r from t h e a s c e n t s t a g e . It may a l s o b e used by t h e crewmen a s a s a f e t y t e t h e r when moving down t h e l a d d e r o r as a n a i d i n ascending t o t h e a s c e n t s t a g e . The LEC is a t h i n 60 fo-ot continuous loop of one i n c h wide s t r a p , which loops through a s u p p o r t p o i n t i n t h e a s c e n t s t a g e and back t o t h e crewman on t h e s u r f a c e . The end of t h e loop i s c l o s e d by two hooks, a t t a c h e d t o g e t h e r , which �p r o v i d e a means of s e c u r i n g equipment t o t h e LEC f o r t r a n s f e r . The crewman on t h e s u r f a c e can e f f e c t a t r a n s f e r t o t h e a s c e n t s t a g e by p u l l i n g t h e top s t r a p which causes equipment hooked t o t h e lower s t r a p t o move i n t o t h e a s c e n t stage. Although t h e t r a n s f e r of equipment with t h e LEC i s simple i n p r i n c i p l e , t h e a c t u a l t r a n s f e r o p e r a t i o n can r e q u i r e a s i g n i f i more i f c a u t i o n i s . n o t obc a n t amount of time and e f f o r t s e r v e d i n keeping t h e s t r a p s untangled o r i f t h e p r o p e r o p e r a t i o n a l procedures a r e n o t used. Because of t h e time involved (up t o f i v e minutes p l u s a r e s t p e r i o d ) , t h e number of equipment t r a n s f e r s i s k e p t t o a minimum. I n t h e nominal t i m e l i n e t h r e e t r a n s f e r s a r e planned, one t o t r a n s f e r t h e Hasselblad camera t o t h e s u r f a c e and one t r a n s f e r f o r each of t h e two SRC's. - EVA Termination For EVA t e r m i n a t i o n t h e r e a r e s e v e r a l advantages gained by one crewman i n g r e s s i n g b e f o r e an SRC i s t r a n s f e r r e d . ~ l t h o u g h i t i s p o s s i b l e t o t r a n s f e r an SRC i n t o t h e a s c e n t s t a g e b e f o r e t h e f i r s t crewman i n g r e s s e s , t h e crewman i n s i d e w i l l p r o v i d e some a s s i s t a n c e d u r i n g t h e t r a n s f e r . A d d i t i o n a l l y , h e w i l l remove t h e SRC and p l a c e i t where i t does n o t i n t e r f e r e w i t h i n g r e s s . The f i r s t crewman t o i n g r e s s w i l l a l s o make a LM system check, change t h e sequence camera f i l m magazine, and r e p o s i t i o n t h e camera t o cover t h e SRC t r a n s f e r and o t h e r crewman's l a d d e r a s c e n t . A s each man b e g i n s h i s EVA t e r m i n a t i o n h e w i l l c l e a n t h e EMU. Although t h e crew w i l l have a very l i m i t e d c a p a b i l i t y t o remove l u n a r m a t e r i a l from t h e i r EMU'S, they w i l l a t t e m p t t o brush o f f any d u s t o r p a r t i c l e s from t h e p o r t i o n s of t h e s u i t which they can reach and from t h e b o o t s on t h e footpad and l a d d e r . I n t h e EVA t e r m i n a t i o n t h e r e a r e two t a s k s which w i l l r e q u i r e some i n c r e a s e d e f f o r t . The f i r s t i s t h e a s c e n t from t h e . footpad t o t h e lowest l a d d e r rung. I n t h e unstroked p o s i t i o n t h e v e r t i c a l d i s t a n c e from t h e top of t h e footpad t o t h e lowest l a d d e r rung i s 31 i n c h e s . I n a nominal l e v e l l a n d i n g t h i s d i s t a n c e w i l l be decreased only about f o u r i n c h e s . Thus, u n l e s s t h e s t r u t i s s t r o k e d s i g n i f i c a n t l y t h e crewmen a r e r e q u i r e d t o s p r i n g up u s i n g t h e i r l e g s and arms t o b e s t advantage t o r e a c h t h e bottom rung of t h e l a d d e r from t h e footpad. �The second t a s k w i l l be t h e i n g r e s s o r t h e crewmen's movement through t h e h a t c h opening t o a s t a n d i n g p o s i t i o n i n s i d e t h e LM. The h a t c h opening and t h e space i n s i d e t h e LM a r e small. T h e r e f o r e , t h e crewmen must move slowly t o p r e v e n t p o s s i b l e damage t o t h e i r EMU'S o r t o t h e exposed LM equipment. Before t h e crew c l o s e s t h e h a t c h and b e g i n s t h e c a b i n r e p r e s s u r i z a t i o n , they w i l l j e t t i s o n t h e equipment they no l o n g e r need. The i t e m s t o j e t t i s o n a r e t h e used ECS c a n n i s t e r and b r a c k e t , OPS b r a c k e t s ( a d a p t e r s ) , and 3 a r m r e s t s . Numerous p i e c e s of l o o s e equipment w i l l b e l e f t on t h e l u n a r s u r f a c e a f t e r they have been deployed o r used d u r i n g t h e EVA. A complete l i s t of t h i s equipment except f o r a few pip-pins, b r a c k e t s , and o t h e r s m a l l p i e c e s of t h e l a r g e r p i e c e s of equipment l i s t e d , i s p r e s e n t e d a s Table 3-2 on t h e f o l l o w i n g page �TABLE 3-2 Loose Equipment L e f t on Lunar S u r f a c e During EVA . TV Equipment . . .. .. camera tripod h a n d l e l c a b l e assembly MESA b r a c k e t . S o l a r Wind Composition s t a f f Apollo Lunar Handtools scoop tongs e x t e n s i o n handle hammer gnomon Equipment stowed i n sample r e t u r n c o n t a i n e r s (outbound ) e x t r a York mesh packing m a t e r i a l SWC bag ( e x t r a ) spring scale unused s m a l l sample bags two c o r e tube b i t s two SRC s e a l p r o t e c t o r s environmental sample c o n t a i n e r s 0 r i n g s and s m a l l r o d s i n l i d s .. . .. . . . . .. - - . . . Apollo Lunar S u r f a c e Close-up Camera . EL Data Camera (magazine r e t u r n e d ) (film c a s s e t t e returned) EVA t e r m i n a t i o n Lunar Equipment Conveyor ECS c a n n i s t e r and b r a c k e t OPS b r a c k e t s Three a r m r e s t s Bag of used u r i n e bags . . . . . Post-EVA equipment j e t t i s o n Two P o r t a b l e L i f e Support Systems L e f t Hand S i d e Stowage Compartment (with equipment i n s i d e ) One a r m r e s t . . . �3.3 SUMMARY TIMELINE NOMINAL LUNAR SURFACE EVA n LEGEND I HCC.H ~YL:LRV." :: i.. I I ACIlVIIV ...'..., .. .~C.OV..l b0t~.0. 1.10 1:20 1439 \Irnt\<I it: is 1.40 *.:....z... .................................................... o u t COUY 5 m m . ru ~ m w t c r d o ~ p s s c c r ol.0 ~v OO(,YCITCO MCST/PMO~O IAYPLC :JUIC:,~S ius .Tact C L O I ~ . C DD . C I O I I < .OIDLO' L*' .Rat0 b C10SC.u. m .on* - .(a JcsLo."c:. 8.r ."CYWC I I ,.W.l"l*'S lOrYI [.,I> I 1XMIIVI.l am ! 0. T o o 1 C"M.l"I.lS 4- DO(.YI.113 ( A Y 4 1 C*L.L-"M .u~wt I);%* sw T O \ v 4 . ' v. ... c-*I .C,OSC S I P 6." I ~IILCCI < OWI OC.LO~YC.I .C.*.v 1.20 1.30 k ... $811 m s s * v c $cn\unr KC CL0SC.C. 1.10 I ..r I S ~ C t I P 1J 0 1 4 0 ' .OCPIO, I ur ~aeaa*~.. hi'\'\ -. --. -- -- 1:10.-. ��3.4 NOMINAL TIMELINE. LUNAR SURFACE EVA LMP - CD R - o+oo mm m a C r m ,m z m 0 mm z 00 D - oz x m - + I == C NOTE : DETAILED PROCEDURES ARE PRESENTED I N " F I N A L EVA PROCEDURES APOLLO 11" SUBMITTED BY EVA BRANCH, FC -zs 7JC <3 m - -I= W-I -I- TURN TV ON START SEQUENCE CAMERA (SC) I ' .I IPLAY UliT LEC I DESCEND TO FOOTPAD CHECK ASCENT PROCEDURES I z 3 r u I H O Z Z CHANGE SC FR TO 24/SEC STEP TO SURFACt RESTICHECK E14U I I I - .-ISTOW LEC - ~ - 0+10 - MONITOR CDR A C T I V I T Y PLAY OUT LEC MOVE TO'POSITION AND RELEASE MESA w cnD -m LMP - DEPRESS CABIN FROM 3.5 P S I OPEN HATCH INSURE SUBLIMATOR ICED PERFORM F I N A L SYSTEMS CHECKS CONFIRM "GO" FOR EVA - Wcn 0 CDR - II M O V E 1'HROUGH HATCH CHECK INGRFSS PROCEDURE I 11 1 APOLLO EDITION FINAL t 1 CHECK AND DISCUSS BALANCEISTABILITY I I 1 TO 121SEC VISUALLY MONIT~R CDR ACTIVITY PROVIDE CHECKLIST ASSISTANCE I + ASSIS CDR PLAY OUT LEC CHANGE SC F I L M MAG CHANGE FR TO 61SEC /-L MISSION CHANGE SC% - DATE JUNE 27, 1 9 6 9 rC/ I MISSION TIME I DAY1am I PAGE 1 �NOMINAL TIMELINE CDR - LMP - LMP - CDR - II I- REST/CHECK EMU CHECK LM AND EMU STA* sc 1 t UNSTOW CSC AllD DEPLOY HANDLE MONITOR AN; EXTEND BAG COLLECT SAMPLE + PHOTO EGRESS I DETACH BAG AND DISCARD HANDLE -I- I STOW SAMPLE I MONITOR TRANSFER STILL CAMERA TO SURFACE PREPARE FOR CAMERA TRANSFER ASSIST CDR PERFORM COMM CHECK AND PHOTO LMP C I REMOVE TRIPOD I PERF OR^ FI~AL LM AND EMU CHECK CONFIRM "GO" FOR EVA PLACE SPARE CAMERA ON LM FLOOR I MISSION APOLLO 1 1 I I FINAL I 1 JUNE t tI t DET'ERMI NE WALKING CAPABILITY REMOVE TV CABLE 1 I -I- REMOVE CAMERA CARRY TV TO DEPLOY S I T E L 1 EDITION f' \D LENS WA TO I t CHECK ERWIN AND LIGHTING STEP TO SURFACE REST/CHECK EMU + CHANGE FROM I CHECK AND REPORT LM STATUS DESCEND TO PAD CHECK ASCENT PROCEDURE C ECK BALANCE/STABILITY REACH CAPABILITY TETHER' CAMERA t I- I t PREPARE MESA FOR TV DEPLOYMENT REST/CHECK EMU MOVE TH'RU HATCH CHECK INGRESS PROCEDURE DATE 27. 1 9 6 9 MISSION TIME 112+54 - 113+18 I 1 DAY/ REV 5/20 I PAG€ 2 of 7 1 �NOMiNAL TIMELINE CDR - LMP - . II CDR - LMP - �NOMINAL TIMELINE LMP - CDR - ?' + CARRY ALSCC REPORT STATUS QUAD I V REPORT STATUS AND PHOTO -Y GEAR REMOVE PACKAGE 1 (PSE) PHOTO QUAD I V TAKE PHOTO PANORAMA + REMOVE PACKAGE 2 ( L R ~ ) I I PHOTO >Y GEAR 1 , PHOTO EASEP OFFLOAD TAKE CLOSE-UP PHOTOS TAKE CLOSE-UP PHOTOS QUAD. I11 + t 4- TRANSFER CAMERA TO CDR 1 OPEN SEQ BAY DOOR C I , PHOTO E A S E OFF LOAD MISSION APOLLO 11 I 1 EDITION FHVAL I 1 i t T RESTICHECK EMU C DEPLOY PSE $- DEPLOY L R ~ -IREPORT STATUS AND PHOTO QUAD I 1 t CLOSE SEQ BAY DOOR RESTISELECT DEPLOY S I T E CARRY CAMERAS TO CARRY EASEP DEPLOY S I T E PACKAGES REPORT POSITION TO DEPLOY S I T E FROM LM PHOTO -Z GEAR TETHER S T I L L CAMERA t T_L PHOTO qUAD I11 REPORT STATUS -Z GEAR 7' -1- REMOVE ALSCC FROM MESA AND DEPLOY 1 REPORT STATUS +Y GEAR 1 LMP - CDR - II I PHOTO L R ~ MOVE DATE JUNE 13, 1969 MISSION TIME 113+42 - 114+06 I % PSE T I 1 TAKE CLOSE-UP PHOTOS DAY/ REV 5/20 I PAGE 4 of 7 ��NOMINAL TIMELIN E CDR - LMP - CDR - LMP - T PLATFORM t RESTIPHOTO LMP 1 t REMOVE ALSCC F I L M STOW I N CSC POCKET STOW ALSCC F I L M I -L- t MOVE TO MESA PLACE SCOOP BY MESA MOVE TO MESA PLACE SAMPLE BAG ON SCALE t OPEN L A ~ G EENVIR. SAMPLE CONTAINER. COLLECT LOPSE MATERIAL -L + RETRIEVE SWC t HOLD CONTAINER SEAL AND STOW t SCOOP LOOSE + PACK SRC I F T I M E AVAILABLE COLLECT CORE SAMPLE CLOSE AND SEAL SRC MOVE TO LADDER CLEAN EMU t 1, APOLLO ASSIST CDR, + + HOLD S ~ CBAG 1. 11 1 T TRANSFER BULK SAMPLE SRC AND CAMERA MAG. MATERIAL INTO SAMPLE BAG PLACE SWC I N BAG MISSION CHANGE sc F I L M REORIENT CAMERA CHANGE FR TO 6/SEC I I PUSH STAFF INTO SURFACE. ASSESS FORCE PHOTO r REMOVE CAMERA MAGAZINE AND CONNECT TO LEC OPEN SMALL CONTAINER COLLECT ROCK SAMPLE HOLD CONTAINER SEAL AND STOW + INGRESS DISCONNECT AND STOW SRC AND CAMERA MAG. I I EDIVION. FINAL I DATE IJUNE 1 9 6~9 ~ , . MISSION TIME 114+30 - 114+54 1 DAY/ REV 5/20-21 I t PAW 6 of 7 I �NOMINAL TIMELINE CDR - LMP - - T - t1 -. JETTISON EQUIPMENT CLOSE HATCH - Ct STOP SC ' 2+40 LMP - CDR - CABIN REPRESS 1 - - DISCONNECT LEC AND - M I S S I O N TIME FINAL I JUNE 27, 1969 114+54 - 115+f8 I DAY/ REV 5/21 I PAaE 7 of 7 I �SUN I -z 100 FEET OF - FIGURE 3-9. - SCALE 0' PROBABLE AREAS FOR LUNAR SURFACE ACTIVITY 5' 10' �3.5 Detailed Procedures 3.5.1 Nominal Activities Sequence Section Event Final Pre-EVA Operations Page 40 CDR Initial EVA CDR Environmental Familarization Contingency Sample Collection Preliminary Checks LMP Initial EVA . VIII . VII TV Deployment LME' Environmental Familiarization SWC Deployment EVA and Environment Evaluation XI. Bulk Sample Collection LM Inspection* EASEP Deployment XIV . XV. XVI . XVII. * Documented Sample Collection LMP EVA Termination SRC Transfer CDR EVA Termination Nominally, the Apollo Lunar Surface Close-up . . Camera (ALSCC) will be deployed during the LM inspection. �3.5.2 Procedures LMP - CDR I. FINAL PRE-EVA OPEUTIONS NOTE: For t h e d e t a i l e d procedures of t h i s s e c t i o n , r e f e r t o t h e " F i n a l EVA Procedures Apollo ll", which is submitted by t h e EVA Branch, FCSD D e p r e s s u r i z e c a b i n from 3.5 p s i Open h a t c h I n s u r e s u b l i m a t o r iced Perform f i n a l systems checks Confirm "go" f o r EVA CDR INITIAL EVA 11. Move through h a t c h (with LEC t e t h e r e d ) Check i n g r e s s procedure A s s is t CDR ' . Perform communications . check w i t h MSFN - Compare l e v e l , c l a r i t y and r e l a y c a p a b i l i t y w i t h t h a t experienced i n s i d e t h e LM. NOTE: F u r t h e r mention of communications checks w i l l b e made only when communication c o n d i t i o n s change, however, t h e y w i l l b e conducted a s r e q u i r e d f o r system o r crewmen monitoring. Move t o p o s i t i o n on l a d d e r t o r e l e a s e MESA Play o u t LEC and u s e a s s a f e t y t e t h e r .. �CDR - Release MESA(1f MESA does n o t deploy, p u l l manual deployment lanyard l o c a t e d on l e f t s i d e of MESA) NOTE: I f t h e MESA w i l l n o t deploy a f t e r p u l l i n g t h e manual deployment lanyard, t h e following EVA t a s k s cannot b e accomplished: 1) 2) 3) 4) 5) 6) Turn TV on and v e r i f y TV reception . . . S t a r t sequence camera. Check o r i e n t a t i o n and frame r a t e a t 12 frameslsec TV Deployment (no TV coverage) SWC Deployment Bulk Sample C o l l e c t i o n Documented Sample C o l l e c t i o n SRC T r a n s f e r Close-up Photography Descend l a d d e r t o footpad. Checkpad-to-1adder.ascent procedures Play o u t LEC Change sequence camera (SC) frame r a t e (FR) t o 2 4 l s e c Step t o s u r f a c e R e s t b e s i d e ladderlcheck EMU. Check RCU. Report 02 and s u i t p r e s s u r e Change SC FR t o 12Isec. Check LM and EMU. Check RCU and r e p o r t 0 2 and s u i t p r e s s u r e Assess e g r e s s / i n g r e s s c a p a b i l i t y 111. CDR ENVIRONMENTAL FAMILIARIZATION Detach and temporarily stow LEC on gear s t r u t o r ladder I n t h e v i c i n i t y of t h e l a d d e r , check i n d i v i d u a l s t a b i l i t y and perform preliminary m o b i l i t y evaluation Check and r e p o r t b a l a n c e l s t a b i l i t y : a. b. c. - l e a n forward, E f f e c t of CG s h i f t backward, and t o each s i d e Downward reach A m motion e f f e c t s Visually monitor CDR a c t i v i t y . Provide c h e c k l i s t a s s is t a n c e �E v a l u a t e and r e p o r t walking capability: Change SC f i l m magazine when necessary. Change FR t o 61sec a. . B a l a n c e b. B e s t pace c. Boot p e n e t r a t i o n d. T r a c t i o n e. S o i l s c a t t e r i n g (cohesion) f . S o i l adhesion g. General comments . . . . . . ~ e s t l c h e c kEMU. Check RCU. Report 02 and s u i t p r e s s u r e . Report p h y s i c a l comfort. Assess EVA capsbility Check LM and EMU. Check RCU Report 02 and s u i t p r e s s u r e . . IV. . CONTINGENCY SAMPLE COLLECTION Remain w i t h i n a few f e e t of l a d d e r Remove t h e CSC from s u i t pocket Deploy t h e CSC h a n d l e and p u l l s t r a p a t b a s e of bag t o open C o l l e c t sample ( i n undisturbed area) P u l l l o c k i n g p i n on . h a n d l e r e l e a s e lever P r e s s r e l e a s e l e v e r and s e p a r a t e h a n d l e from l i p l b a g assembly Discard handle under o r away from LM Detach bag from l i p assembly Discard l i p assembly under o r away from LM S e a l sample bag Restow and s e c u r e bag i n s u i t pocket S t a r t SC. .Check FR a t 6 / s e c V i s u a l l y monitor CDR a c t i v i t y Reorient SC i f necessary �CDR - LMP V. PRELIMINARY CHECKS T r a n s f e r Hasselblad EL Data camera (with c o l o r f i l m and 60mm l e n s ) t o s u r f a c e : a. Remove LEC from temporary stowage l o c a t i o n Prepare t o t r a n s f e r t h e E l e c t r i c Hasselblad camera t o s u r f a c e b. Walk o u t +Z w i t h LEC P l a y o u t LEC. Remove LEC stowage bag and stow i n LHSSC c. T r a n s f e r camera t o s u r f a c e by p u l l i n g on lower s t r a p of LEC A s s i s t CDR, i f necessary d. Detach camera from LEC and t e t h e r t o s u i t . Mount camera on RCU b r a c k e t when d e s i r e d Change sequence camera FR t o llsec NOTE: Only t h e one Hasselblad camera is t r a n s f e r r e d t o t h e surface. I f a f a i l u r e o c c u r s , manual f i l m advancemand and a f u s e change a r e t h e only a c t i o n s p o s s i b l e t o c o r r e c t t h e malfunction. I f malfunction is not c o r r e c t e d , t h e 70mm Hasselblad, w i t h b l a c k and w h i t e f i l m and 80mm l e n s , can be transferred. e. P l a c e LEC back a t stowage location Check and r e p o r t LM s t a t u s . From immediate v i c i n i t y of t h e l a d d e r , check and r e p o r t : a. S t a b i l i t y of LM ( a l l pads contacting surface, t e r r a i n slope, boulders, c r a t e r s ) R e o r i e n t c'amera t o view CDR activity . (The LMP p r e p a r e s t o e g r e s s ) �CDR - b. Gear s t a t u s ( t a k e two photos, one each of +Y and -Y, and one of +Z p a d l s u r f a c e ) (1) Contact (2) P e n e t r a t i o n , s l i p , b u r i a l (3) S t r o k e . . (4) S o i l adhesion c . ? DPS s k i r t s t a t u s ( 1 photo) d. DPS e f f e c t on s u r f a c e : (1) Crater ' (2) R a d i a l e r o s i o n Perform f i n a l LM and EMU check. Confirm "GO" f o r two-man EVA P l a c e s p a r e Hasselblad camera on f l o o r a t 1 e f t . s i d e of +Z hatch. Check EVA t e t h e r attached (Refer t o t h e n e x t s e c t i o n f o r LMP e g r e s s p r o c e d u r e s ) . Check t e r r a i n s t a t u s f o r crew operations : . . a. Check s l o p e , o b s t r u c t i o n s and roughness i n (1) MESA a r e a (2) TV deployment a r e a (3) S-band antenna deployment area (4) Quad I a r e a b. Check l i g h t i n g l v i s i b i l i t y s t a t u s : (1) B r i g h t and d a r k a r e a s (2) TV deployment (3) MESA (4) S-band antenna a r e a (5) General sampling a r e a s ( t a k e two ( s t e r e o ) photos of b u l k sample and one photo, c l o s e up, of contingency sample a r e a ) (6) Up sun (7) Cross sun (two photos, one each d i r e c t i o n ) (8) Down sun LMP INITIAL EVA Res t/Monitor and photograph LMP e g r e s s and d e s c e n t t o R e o r i e n t SC . . . surface Photo (3) LMP Move through hatch. Check i n g r e s s procedure ( P u l l +Z hatch closed) �CDR - LMP Perform communications check (Include r e l a y check with CSM, i f p o s s i b l e ) Photo (3) LMP Descend l a d d e r t o footpad Check pad-to-ladder procedures Photo (3) LMP ascent Step t o s u r f a c e (Deploy TV, see procedures below) Rest b e s i d e ladderlcheck Assess e g r e s s l i n g r e s s capabilities EMU. VII. TV DEPLOYMENT Walk t o MESA Adjust MESA h e i g h t , i f necessary, by p u l l i n g upward on adjustment strap P u l l s t r a p (velcroed) t o remove MESA thermal b l a n k e t from around TV l e n s Complete removal of thermal blanket Remove t r i p o d from MESA: a. P u l l two s t r a p s t o unsnap b. c. d. e. tripod L i f t t r i p o d from MESA Extend t e l e s c o p i n g s e c t i o n Deploy l e g s P l a c e on s u r f a c e near r i g h t s i d e of MESA Walk t o r i g h t s i d e of MESA Remove wide angle l e n s from TV camera and stow on MESA holder Remove LD l e n s from holder and a t t a c h t o camera P u l l s e v e r a l f e e t of TV cable from MESA . (After completion of a r e s t period t h e LMP conducts environmental f a m i l i a r i z a t i o n , see S e c t i o n VIII) �CDR Remove camera from MESA: a. Pull the two pins at the forward edge of mounting frame b. Grasp TV handle and rotate TV toward rear of MESA to free from frame c. Lift camera from frame d. Check camera temperature and report (cold, normal, hot) Place camera on tripod. camera secure Check Carry camera with tripod to site to view subsequent EVA operations (See figure 3-4) Take a step-wise, fast-scan (10 frameslsec) panorama or, if time not available, select several points of interest. Do not point camera within 20" to sun. Start panorama at approximates 22" from an upsun view, move through down sun, continue to other view 22" from up sun. Place camera on surface for a few seconds at approximately 22 112" increments. (15 increments are required for the panorama) Recheck camera temp. and report. Place TV on surface for optimum coverage of surface activity (See Figure 3-4) Move near LMP. Restlcheck EMU. Check RCU. Report 02 and suit pressure. Photo SWC (stereo pair) after LMP deploys it. Return to MESA As required, pull more TV cable from MESA �LMP - CDR - VIII. LMP ENVIRONMENTAL FAMILIARIZATION (At t h i s p o i n t t h e CDR i s deploying t h e TV, s e e S e c t i o n VII) I n t h e v i c i n i t y of. l a d d e r and i n view of TV (and sequence camera, i f pract i c a l ) , check and r e p o r t balance/s t a b i l i t y : a. E f f e c t of CG s h i f t - l e a n forward, backward, and t o each s i d e b. Downward r e a c h c. A r m motion e f f e c t s E v a l u a t e and r e p o r t r e a c h c a p a b i l i t y (with and without support): a . Right up b Right down c. Both up and down . NOTE: Perform f o l l o w i n g e v a l u a t i o n s w i t h i n a few yards of SIC and i n view of sequence camera, i f practical E v a l u a t e and r e p o r t walking capability: a. b. c. d. Pace Stability Traction General e v a l u a t i o n ~ e s t / c h e c kEMU. Check RCU. Report oxygen and s u i t p r e s s u r e . Report p h y s i c a l comfort. Assess EVA capability �CDR - LMF' SWC DEPLOYMENT (At t h i s time t h e CDR is dep l o y i n g t h e TV, s e e S e c t i o n VII) a E r e c t SRC t a b l e : . . a. P u l l Velcro t a b s t o free table b. P u l l t a b l e forward from stowed p o s i t i o n and r o t a t e i n t o horizontal position c. Attach Velcro t a p e t o hold t a b l e i n correct position ( l e v e l , f o r e and a f t ) P u l l t h e two s t r a p s h o l d i n g SWC and remove SWC from MESA Walk t o s u n l i t a r e a Deploy SWC: a. Extend each s e c t i o n of s t a f f u n t i l i t l o c k s . ( r e d band should b e v i s i b l e ) Apply a compressing f o r c e t o each s e c t i o n t o check s e c t i o n s locked b. Extend shade c y l i n d e r and r o t a t e toward r e d s i d e of p i v o t p o i n t , i.e., r e d t o red c. Extend f o i l shade and hook t o lower p o r t i o n of s t a f f d. P r e s s s t a f f i n t o surf a c e w i t h f o i l normal t o sun ( s i d e marked SUN t o Sun) �CDR - LMP X. EVA AND ENVIRONMENT EVALUATION Remove camera from MESA and t e t h e r when r e q u i r e d i n t h e following evaluation NOTE: The f o l l o w i n g l i s t of t a s k s i s p r e s e n t e d a s a guide. The a c t i v i t i e s w i t h i n t h i s p e r i o d are n o t l i m i t e d t o t h e items l i s t e d o r t h e o r d e r i n which they appear. I f necessary f u r t h e r e v a l u a t e: a. E f f e c t of CG s h i f t b (leaning, reach, e t c . Walking capability .) I n u n d i s t u r b e d a r e a and i n view of TV a n d . SC, i f p r a c t i c a l , observe and report : a. Best pace b. Technique f o r s t a r t i n g and s t o p p i n g c. Balance a t i n c r e a s e d pace and l e n g t h of s t e p d. T r a c t i o n e. Dust f . Boot p e n e t r a t i o n ( t a k e stereo pair) g. S c u f f i n g h. Cohesion i. Adhesion (photo boots) 3 . General e v a l u a t i o n of EVA capability �CDR - I n each d i r e c t i o n , up sun, down sun and c r o s s sun, observe and r e p o r t s u r f a c e : a. b. c. d. e. f. Brightness/reflections Color p e r c e p t i o n Contrast v a r i a t i o n Texture determination R e f l e c t i o n i n shadow Rock and c r a t e r distribution g. General t e r r a i n evaluation h. Visual and t e r r a i n phenomena d i f f e r e n t from t h a t expected Check EMU s t a t u s w i t h MSFN af t e r stay i n sunlight. Report comfort /problems Move t o shadow edge and repeat l i g h t i n g / v i s i b i l i t y and t e r r a i n e v a l u a t i o n a s above. A d d i t i o n a l l y , observe shadow edge sharpness (look down sun) Check EMU s t a t u s w i t h MSFN a f t e r stay. Take 12 photo panorama (from p o s i t i o n 20 f e e t i n f r o n t of +Z pad). A s panorama is taken, e s t i m a t e d i s tance t o s e v e r a l prominent terrrain features. Repeat e v a l u a t i o n , a s above, i n shadow Check EMU af t e r s t a y i n shadow �CDR - LMP XI. BULK SAMPLE COLLECTION (The LMP i s conducting t h e EVA and Environment E v a l u a t i o n , S e c t i o n X) Remove camera and p l a c e on MESA P r e p a r e MESA: a. Proceed t o MESA b. I n s u r e a r e a about MESA is s u i t a b l e f o r operations c. Adjust h e i g h t of MESA, i f required d. I n s u r e a l l equipment i s accessible Deploy ETB: a. Unfold and p o s i t i o n bag on r i g h t s i d e of MESA (Check bag t o p f o l d e d i n s i d e bag) . P r e p a r e SRC and ALHT: a. Unstow scoop and hammer. P l a c e i n ETB b. Check s e c u r i t y of SRC t a b l e c. Release b u l k sample SRC c a r r y h a n d l e from d e t e n t p o s i t i o n d. R o t a t e h a n d l e 90' clockwise t o r e l e a s e SRC from MESA e. P u l l p e r p e n d i c u l a r t o MESA t o p w i t h c a r r y handle t o remove from stowage p o s i t i o n f . P l a c e SRC on t a b l e w i t h T-handle up and SRC a l i g n e d with t h e t a b l e g. R o t a t e and p l a c e t h e SRC on t a b l e w i t h SRC h a n d l e pointing away from t h e s p a c e c r a f t h. Release t h e two s t r a p l a t c h e s by p r e s s i n g t h e l a t c h l o c k i n g mechanism, w i t h t h e hand on t h e r e l e a s e handle, i n a sideways motion toward t h e c e n t e r of t h e SRC and r o t a t i n g t h e handle forward and upward . �i. Continuing t o grasp second . s t r a p l a t c h r e l e a s e handle, a f t e r relase, rotate the SRC top to' a n open s t a b l e ' p o s i t i o n . NOTE: I f necessary r e s t r a i n SRC with o t h e r hand on c a r r y handle i n order t o break seal j. Check t h e seal s p a c e r is s t i l l i n p l a c e over t h e s e a l k. Unpack SRC. P l a c e packing m a t e r i a l , and s m a l l sample bags i n SRC l i d , i n t r a n s f e r bag o r on MESA 1.. Remove s p r i n g s c a l e m. Hook s c a l e t o l e f t f r o n t of MESA n. Attach l a r g e sample bag t o s c a l e o. P l a c e SWC stowage bag i n SRC l i d o r on MESA NOTE: I f p r a c t i c a l c o l l e c t samples i n view of TV and sequence camera (NOTE: I f p r a c t i c a l use t h e scoop t o c o l l e c t rocks and loose m a t e r i a l simultaneously. Attempt t o c o l l e c t same volume of rocks a s loose m a t e r i a l ) C o l l e c t rock fragments: a. P u l l s t r a p t o f r e e v i b r a t i o n a t t e n u a t o r from tongs b. Remove t h e tongs from t h e MESA, p u l l t h e two lanyards t o r e l e a s e snaps c. Move w i t h i n s e v e r a l yards of t h e MESA t o c o l l e c t rock fragments placing each fragment i n t o t h e sample bag a t t h e t i m e of collection d. A t t h e completion of fragment sampling, place t h e tongs i n temporary stowage i n t h e MESA o r ETB �CDR R e s t l c h e c k EMU systems Collect loose material: a. Remove e x t e n s i o n h a n d l e from stowed p o s i t i o n on MESA. P u l l two snap l a n y a r d s on e x t e n s i o n h a n d l e t o r e l e a s e . Remove v i b r a t i o n a t t e n u a t o r from s m a l l handle. b. Remove scoop from ETB and connect t o e x t e n s i o n handle c . U s e scoop t o f i l l sample bag w i t h l o o s e m a t e r i a l . Comment on c o l l e c t i o n p r o c e s s , s o i l adhesion and cohesion, d i f f i c u l t y of ..scooping, volume of m a t e r i a l , general evaluation . d. Disconnect e x t e n s i o n handle . from scoop. P l a c e scoop 'and e x t e n s i o n h a n d l e i n temporary stowage on MESA o r i n ETB Res t l c h e c k EMU systems Pack and s e a l SRC: a. Remove sample bag from s p r i n g scale b. P l a c e sample bag i n SRC c. Close bag and p l a c e bag i n c e n t e r of SRC s o t h a t bag ends a r e toward SRC ends. d. P l a c e packing m a t e r i a l i n SRC t o minimize v o i d space U s e c a u t i o n t o keep SRC s e a l clean. e. Remove s e a l p r o t e c t o r . If a n O-ring s e a l is l o o s e , remove from SRC and d i s c a r d �CDR - LMP - f . Rotate t h e top closed with a s t r a p l a t c h handle g. S e a l t h e SRC by r o t a t i n g t h e two s t r a p l a t c h e s downward t o t h e locked p o s i t i o n ' P r e p a r e f o r SRC t r a n s f e r : a. R e t r i e v e LEC from stowed position b. Walk t o SRC c. A t t a c h LEC lower hook (marked w i t h "L") t o SRC t o p - l e f t f r o n t bracket d. Attach LEC upper hook (marked w i t h "R") t o t h e SRC t o p - r i g h t r e a r b r a c k e t and l o c k hook R e s t l c h e c k EMU XII. (At t h i s ' p o i n t t h e CDR i s comp l e t i n g t h e Bulk Sample Collect i o n , S e c t i o n XI) LM INSPECTION During i n s p e c t i o n e v a l u a t e v i s u a l perception Report s t a t u s of Quad I: a. Both LM s t a g e s (1) Coating (2) Dust (3) S h i e l d i n g b. Ascent s t a g e (one photo) (1) RCS (2) Rendezvous r a d a r c. Descent s t a g e (one photo) (1) Engine s k i r t , Report s t a t u s of +Z gear: a. Main s t r u t ( t a k e one photo) b. Secondary s t r u t s (two photos, one on each side) c. Take s t e r e o p a i r of padlsurf ace �Photo a r e a where b u l k sample was c o l l e c t e d Deploy ALSCC : (Deployment of t h e ALSCC w i l l b e delayed u n t i l t h e documented sample c o l l e c t i o n i f behind i n the timeline) . a. Remove i s o l a t o r l a t c h p i n and p i v o t cover b. P u l l camera from MESA c. P l a c e camera on secondary g e a r s t r u t and e x e r t . p r e s s u r e on camera cover. P u l l t h e two s k i r t l a n y a r d s d. R o t a t e handle r e t a i n i n g latch e. Swing handle clockwise 150° and p u l l u n t i l f u l l y extended f . P l a c e camera on s u r f a c e ALSCC OPERATION Close-up photographs w i l l b e t a k e n by e i t h e r crewman when time i s a v a i l a b l e between or during other tasks. Several times w i t h i n t h e EVA a r e sugg e s t e d when i t may b e convenient f o r t h e crew t o t a k e photos. T h i s i s n o t a requirement t o t a k e photos nor does i t p r o h i b i t . them from o b t a i n i n g photographs a t o t h e r times which may b e feasible. I n g e n e r a l t h e camera o p e r a t i o n is : a. Estimate p o s i t i o n of o b j e c t p l a n e r e l a t i v e t o camera bearing surface b. P o s i t i o n camera over o b j e c t (Describe o b j e c t and l o c a t i o n ) , �CDR - c. I f o b j e c t is below ALSCC bearing surface depress s k i r t u n t i l o b j e c t i s w i t h i n focus plane d. I f o b j e c t is above b e a r i n g s u r f a c e t i l t camera back u n t i l o b j e c t i s w i t h i n focus p l a n e e. A c t i v a t e t r i g g e r l o c a t e d on handle g r i p f . Read and r e p o r t frame c o u n t e r g. Observe c y c l e completion by l i g h t on handle Carry t h e ALSCC around t h e LM d u r i n g t h e i n s p e c t i o n and t a k e photos a s p r a c t i c a l Report s t a t u s of Quad IV: a. Both LM s t a g e s (1) Coating (2) Dust (3) S h i e l d i n g b. Ascent s t a g e (1) RCS (2) St e e r a b l e antenna (3) Rendezvous r a d a r c. Descent s t a g e (1) Descent engine s k i r t (2) MESA Report s t a t u s of +Y g e a r assembly: a. Main s t r u t b. Secondary s t r u t s . Take one photo of A/S Take one photo of s k i r t Take one photo of MESA ( I n c l u d e a l l Quad I V , i f practical) Take one photo of main s t r u t Take two photos, one on each s i d e of secondary s t r u t s Take s t e r e o p a i r of pad/ surface �CDR R e s t l e v a l u a t e and r e p o r t l i g h t i n g / v i s i b i l i t y i n a l l directions, p a r t i c u l a r l y SIC r e f l e c t i o n s . Observe and r e p o r t t e r r a i n c h a r a c t e r i s t i c s . Estimate dist a n c e t o s e v e r a l prominent t e r r a i n f e a t u r e s . Take close-up photos i f p o s s i b l e - .LMP Take panorama (12 photos) from p o s i t i o n approx 20 f t o u t from +Y pad and 30 deg CW from +Y a x i s o r 120 deg from l a s t panorama Report s t a t u s of Quad 111: a. Both LM s t a g e s (same a s Quad IV) b. Ascent s t a g e (1) RCS (2) St e e r a b l e antenna (3) VHF antenna c. Descent s t a g e (1) P r o p e l l a n t v e n t s (2) F u e l v e n t (3) Tanks (Oxygen, Helium (2)) (4) Descent engine s k i r t (5) Note i f s u r f a c e d i s c o l o r e d Report s t a t u s of -Z g e a r assembly (same items a s +Y and: Take one photo of A/S , Take one photo of s k i r t (Photo i f s u r f a c e d i s c o l o r e d ) Take same photos a s +Y a. Landing t r a c k b. O x i d i z e r v e n t c EVA antenna) . . Receive camera and t e t h e r t o s u i t Hand Hasselb l a d camera t o CDR Report s t a t u s of Quad 11: (The LMP b e g i n s t h e . EASEP deployment. See t h e following s e c t i o n ) a. Both IN s t a g e s (same a s Quad IV) b. Descent s t a g e (one photo) (1) Landing r a d a r (2) SEQ bay ' T a k e 12 photo panorama (from 20 f t o u t from -Y pad and 30' CCW from -Y a x i s o r 120' from l a s t panorama position) �CDR - LMP Report s t a t u s of -Y g e a r assembly: a. Main s t r u t ( t a k e one photo) b. Secondary s t r u t s (one photo from each s i d e ) c. P a d l s u r f a c e ( t a k e s t e r e o pair) XIII. (At t h i s p o i n t t h e CDR i s completing t h e LM i n s p e c t i o n . See t h e precedi.ng s e c t i o n ) NOTE: I f LMP cannot r a i s e door, s t a n d c l e a r of d o o r , a n d manually' a s s i s t ' EASEP DEPLOYMENT Open SEQ bay door: a. Remove thermal cover from door lanyard b. R e t r i e v e l a n y a r d from r i g h t s i d e of SEQ bay (remove lower v e l c r o strap) c. Move t o p o s i t i o n c l e a r of door d. p u l l w h i t e of lanyard t o r a i s e door e. Temporarily stow lanyard on s t r u t f . I f Quad I1 is i n a low a t t i t u d e connect f o l d e d doors w i t h v e l c r o s t r a p PACKAGES REMOVED BY BOOMS Photograph package removal Remove Package 1 (PSE): a. R e t r i v e boom l a n y a r d from package, (handle) . ' . b. Move t o p o s i t o n c l e a r of package (approximately . . 10 f e e t ) c. P u l l w h i t e p o r t i o n of lanyard t o unlock and move package from SEQ bay t o f u l l y extended boom position �CDR - LMP d. P u l l b l a c k and w h i t e s t r i p e d p o r t i o n of lanyard t o lower package t o s u r f a c e e. R e l e a s e w h i t e p o r t i o n of lanyard from b a s e of package f . P u l l s m a l l lanyard ( v e l c r o e d t o handle) on package t o r e l e a s e boom c a b l e and l a n y a r d s . Reattach lanyard t o v e l c r o g. Move package c l e a r h. P u l l b l a c k and w h i t e s t r i p e d lanyard t o r e t r a c t boom ( o r push boom back w i t h hand) Remove Package 2 (LR') : a. Repeat Package 1 procedure ( s e t package c l e a r of SEQ bay MANUAL PACKAGE REMOVAL Remove Package 1: . a. P u l l s m a l l l a n y a r d , a t t o p o r bottom of package, t o r e l e a s e hockey s t i c k from boom b. Remove deployment l a n y a r d from package and p u l l w h i t e p o r t i o n t o unlock package from bay c. Release w h i t e p o r t i o n of lanyard from b a s e of package d. Move deployment l a n y a r d t o s i d e c l e a r of package e. Manually p u l l package c l e a r of SEQ bay f . S e t package on s u r f a c e c l e a r of bay a r e a �LMP - CDR - Remove Package 2: a. Repeat Package 1 procedure NOTE: Simultaneous accomplishment, although i n d i c a t e d of t h e following tasks, is not required. Photo LMP and t a k e close-up photos a s p r a c t i c a l Close SEQ bay door: a. R e t r i e v e door l a n y a r d b. Move t o p o s i t i o n c l e a r of door c. P u l l b l a c k and w h i t e s t r i p e p o r t i o n of l a n y a r d u n t i l door is c l o s e d d. Discard l a n y a r d . 3 S e l e c t s i t e f o r PSE and LR deployments, nominally 70 f t s o u t h of t h e SIC . Move to'deployment s i t e w i t h cameras. E s t i m a t e d i s t a n c e and p o s i t i o n w i t h r e s p e c t t o t h e LM P l a c e LR3 w i t h b a s e toward Earth. (Astronaut f a c e s e a s t f o r S i t e s 1 and 2 and west f o r S i t e s 3,4, and 5). R e s t / prepare a r e a ( c l e a r rocks, smooth s u r f a c e as r e q u i r e d ) 3 Carry PSE and LR t o deployment s i t e (Nominally 70 f e e t out t h e LM-Y a x i s . Report s i t e 10cat i o n i f i t is n o t nominal) 3 P l a c e LR package on s u r f a c e (on end) i n a c l e a r , l e v e l l o c a t i o n , i f p r a c t i c a l . Move PSE approximately 1 0 f e e t f u r t h e r from T.,M and p l a c e on s u r f a c e w i t h b a s e toward n o r t h (Arrow on handle p o i n t s t o south) 3 Deploy LR : a. Simultaneously g r a s p deployment boom ("hockey s t i c k " ) and p u l l p i n ' i n s i d e c a r r y handle. Remove and d i s c a r h "hockey s t i c k " a* Res t / c h e c k EMU �CDR b . ment Simultaneously g r a s p deployh a n d l e and r e l e a s e r i n g c. d. e. f. . * ( L e f t s i d e of package) t o release deployment handle p u l l pin O P u l l deployment handle t o extend handle s i x inches, t o the f i r s t d e t e n t p o s i t i o n , and t o p a r t i a l l y r e l e a s e a r r a y . Discard handle release ring Grasp p u l l r i n g on a r r a y t i l t i n g handle, p u l l t o remove p r o t e c t i v e cover. Discard cover @ Grasp deployment handle t o s t e a d y package. @ Grasp a r r a y t i l t i n g handle, push down r o t a t e handle 45'. P u l l outward t o extend t o d e t e n t p o s i t i o n (9.5 i n c h e s ) and complete a r r a y r e l e a s e @ Use deployment handle t o s t e a d y package. Use a r r a y t i l t i n g handle t o t i l t a r r a y ( t o d e t e n t f o r landing s i t e ) Deploy PSE: a. P r e p a r e a r e a (move r o c k s , . etc.) i f required b. From b a s e of package p u l l l a n y a r d t o r e l e a s e gnomon @ c. Grasp c a r r y h a n d l e w i t h one hand and u s e t h e o t h e r t o remove and d i s c a r d t h e r i g h t s o l a r panel-restraini n g p u l l p i n @ and p a n e l support bracket p u l l p i n @ d. Grasp f i r s t s o l a r p a n e l support bracket, r o t a t e b r a c k e t forward l i f t b r a c k e t upward t o r e l e a s e and remove f i r s t r e a r support bracket-p u l l pin. @ Discard b r a c k e t / l a n y a r d / p u l l p i n The c i r c l e d numbers and symbols correspond t o d e c a l s on t h e packages. g. R e l e a s e t i l t i n g handle (should s p r i n g back i n t o stowed position) h. Depress t r i g g e r on deployment handle, p u l l handle t o extend t o f u l l @ e x t e n t (an a d d i t i o n a l 27 inches) and r o t a t e package t o lunar surface i. Check and r e p o r t experiment a l i g n e d and l e v e l t o w i t h i n Use gnomon +5O. - @1-1 shadow c a s t on p a r t i a l compass r o s e f o r alignment. Use bubble f o r l e v e l i n d i c a t i o n . Use deployment h a n d l e t o a l i g n and l e v e l as r e q u i r e d e. Repeat procedures c. and d. f o r t h e l e f t s o l a r panel bracket @ @ @ f . From s i d e of PSE p u l l deployment h a n d l e ("worki n g height") p i p p i n @ and remove "hockey s t i c k " @ g. Grasp deployment h a n d l e , r o t a t e and p u l l t o extend t o 30 i n c h working h e i g h t and l o c k i n p l a c e @ h. Use deployment handle t o r o t a t e package t o s u r f a c e i. With deployment h a n d l e , embed package mounting t a b s i n l u n a r s u r f a c e (smooth s u r f a c e and a l i g n package) 0 ~nm-1 �CDR - Photograph s c i e n t i f i c packages: CAUTION : Do n o t walk up-sun of t h e PSE. Shadows on t h e s o l a r p a n e l s affect internal electronics a. Take c l o s e u p photo of LR3 b. Take s t e r e o p a i r of LR3 c. Take one photo from about same distance a s stereo p a i r but a t e n t i r e l y d i f f e r e n t angle d.. Move t o PSE e. Repeat photos as i n a , b , and c j. Check and r e p o r t experiment a l i g n e d and l e v e l t o withi n i-5' a s i n d i c a t e d by gnoKon shadow c a s t on part i a l compass r o s e and bubble l e v e l , r e s p e c t i v e l y . Use deployment h a n d l e t o a l i g n and l e v e l as r e q u i r e d . k. P u l l antenna r e l e a s e lanyard from deployment handle ( v e l c r o e d t o handle) 1. P u l l l a n y a r d t o deploy s o l a r p a n e l s and antenna NOTE: . I f p a n e l s do n o t deploy, s t a n d c l e a r of deployment a r e a and check r e a r s u p p o r t b r a c k e t s c l e a r of s o l a r p a n e l s and r e l e a s e l e v e r s (underneath forward edge of p a n e l s ) p u l l e d m. R o t a t e antenna t o designated landin o f f s e t ( s i t e dependent) n. Recheck package l e v e l and a l i g n e d . Report shadow on compass r o s e &) Move t o t h e Quad IV a r e a Move t o MESA w i t h ALSCC.: Take photos a s p r a c t i c a l . Photo f o o t p r i n t made w h i l e c a r r y i n g EASEP R e s t l c h e c k EMU Restlcheck EMU XIV. ~ e s t / p h o t oLMP. close-up photos Take ' - DOCUMENTED SAMPLE COLLECTION T r a n s f e r b u l k sample SRC t o footpad o r g e a r s t r u t s : . . a. Extend loop end of LEC u n t i l s e c t i o n of s t r a p going t o A/S i s t a u t .b. L i f t SRC from t a b l e by l e f t (lower) hook @ �CDR c. Carry SRC and p l a c e on footpad o r secondary struts d. Temporarily stow LEC on gear s t r u t e. Return t o MESA P r e p a r e documented sample SRC f o r sample c o l l e c t i o n : a. Check s e c u r i t y of t a b l e b. P u l l t h e lanyard on l e f t s i d e of TV mounting b r a c k e t t o r e l e a s e t h e two p u l l pins. c. Remove and d i s c a r d b r a c k e t under LM d. Release DS SRC c a r r y h a n d l e from d e t e n t p o s i t i o n e. R o t a t e handle 90' clockwise t o r e l e a s e SRC from MESA f . P u l l perpendicular t o MESA top w i t h c a r r y h a n d l e t o remove from stowage position g. P l a c e SRC on t a b l e w i t h T-handle up and SRC a l i g n e d with the t a b l e h. R o t a t e and p l a c e . t h e SRC on t a b l e w i t h SRC handle p o i n t i n g away from t h e spacecraft i. Release t h e two s t r a p l a t c h e s by p r e s s i n g t h e l a t c h l o c k i n g mechanism w i t h t h e hand on t h e r e l e a s e handle i n a sideways motion toward t h e c e n t e r of t h e SRC and r o t a t i n g t h e handle forward and upward �CDR j. Continuing t o g r a s p second strap latch release handle, a f t e r r e l e a s e , r o t a t e t h e SRC t o p t o an open s t a b l e p o s i t i o n . NOTE: I f necessary res t r a i n SRC w i t h o t h e r hand on c a r r y h a n d l e i n o r d e r t o break s e a l k. Check t h e s e a l s p a c e r i s s t i l l i n p l a c e over t h e bottom s e a l 1. Remove and stow packing m a t e r i a l on SRC l i d , o r i n MESA o r ETB Remove one c o r e t u b e from SRC and p l a c e i n SRC l i d o r ETB . n. Remove t u b e caps and p l a c e i n SRC l i d (two caps . . . wrapped i n packing m a t e r i a l ) 0. Remove small sample bag c o n t a i n i n g York mesh. S e a l bag and p l a c e i n SRC l i d Walk t o LMP ', C o l l e c t c o r e t u b e sample: Take s t e r e o p a i r a f t e r t u b e i s pushed i n t o s u r f a c e ' a. Remove c o r e t u b e from SRC (check b i t a t t a c h e d ) and connect t o t h e e x t e n s i o n handle b. Remove hammer from ETB c. Move t o an u n d i s t u r b e d p o i n t n e a r t h e MESA ( i n view of TV, i f p r a c t i c a l ) d. P l a c e t h e c o r e t u b e a t t h e sampling l o c a t i o n . Push tube i n t o surface t h e l e n g t h of t h e tube. Drive w i t h t h e hammer i f n e c e s s a r y e. R e t r i e v e t u b e by p u l l i n g a l o n g its vertical axis, rotating i f necessary �CDR - I f procedure above i s n o t p r a c t i c a l o r i f t i m e perm i t s , p l a c e gnomon n e a r p r o s p e c t i v e fragment and/or s o i l sample ( n e a r s e v e r a l samples i f p o s s i b l e ) and t a k e two photos of sample s i t e . From approximately f i v e f e e t away, t a k e two photos ( s t e r e o p a i r ) from n e a r 90' t o sun l i n e NOTE: The types of samples and t h e o r d e r i n which they a r e coll e c t e d w i l l b e dependent on t h e t e r r a i n features investigated and crew judgement on t h e b e s t i n v e s t i g a t i v e approach w i t h i n operational limitations. . . Remove a s m a l l b a g ( s ) from l a r g e bag. Report number on bag. (Bags a r e numbered 1 through 14) Open s m a l l bag and hold f o r LMP S e a l small bag and p l a c e i n i n l a r g e c o l l e c t i o n bag Photograph a r e a ( s ) where sample(s) was taken C o l l e c t sample(s) w i t h scoop o r tongs. P l a c e i n bag ( c o l l e c t s e v e r a l samples i f possible) NOTE: The scoop can be used t o simultaneously.collect a small fragment and a s m a l l q u a n t i t y of l o o s e m a t e r i a l S e l e c t a n o t h e r sample and d e s c r i b e o r s e l e c t a new sample a r e a Pick up gnomon ( i f gnomon cannot be conveniently included i n photographs of n e x t sample) �CDR - I f procedure above i s n o t p r a c t i c a l o r i f t i m e perm i t s , p l a c e gnomon n e a r p r o s p e c t i v e fragment and/or s o i l sample ( n e a r s e v e r a l samples i f p o s s i b l e ) and t a k e two photos of sample s i t e . From approximately f i v e f e e t away, t a k e two photos ( s t e r e o p a i r ) from n e a r 90' t o sun l i n e NOTE: The types of samples and t h e o r d e r i n which they a r e coll e c t e d w i l l be dependent on t h e t e r r a i n features investigated and crew judgement on t h e b e s t i n v e s t i g a t i v e approach w i t h i n operational limitations. . . Remove a s m a l l bag(s) from l a r g e bag. Report number on bag. (Bags a r e numbered 1 through 14) Open s m a l l bag and hold f o r LMP S e a l s m a l l bag and p l a c e i n i n l a r g e c o l l e c t i o n bag Photograph a r e a ( s ) where sample(s) was taken C o l l e c t sample(s) w i t h scoop o r tongs. P l a c e i n bag ( c o l l e c t s e v e r a l samples i f possible) NOTE: The scoop can be used t o simultaneously.collect a small fragment and a s m a l l q u a n t i t y of l o o s e m a t e r i a l S e l e c t a n o t h e r sample and d e s c r i b e o r s e l e c t a new sample a r e a Pick up gnomon ( i f gnomon cannot be conveniently included i n photographs of next sample) �CDR Move t o a new sampling a r e a Repeat sampling procedure a t new s i t e ( s ) - u n t i l t h e c o l l e c t i o n bag is f i l l e d o r t h e a l l o t t e d time h a s elapsed. ~ e s t l c h e c kEMU as a p p r o p r i a t e . Take s u r f a c e close-up photographs i f feasible Move t o MESA w i t h s t i l l and close-up cameras Move t o MESA w i t h tongs, scoop, and samples Remove ALSCC f i l m c a s s e t t e and stow: a . P u l l t h e two cover l a n y a r d s and remove cover b. R o t a t e c a s s e t t e f i l m cutter lever c. L i f t c a s s e t t e r e t a i n i n g arm d. Remove c a s s e t t e a n d . p l a c e i n CSC pocket on CDR's s u i t . Close CSC pocket Remove l a r g e sample bag from LMP and a t t a c h t o s p r i n g s c a l e on MESA P l a c e scoop by o r on MESA Hold c o n t a i n e r f o r LMP Hand c o n t a i n e r t o CDR Remove sample of t h e i n the Remove t h e environmental container, the l a r g e r two s m a l l c o n t a i n e r s SRC, and open. o-ring from s e a l �CDR Use scoop to collect loose material from an undisturbed area where bulk sample was taken. Place sample in container. Place scoop by MESA Seal container and place in SRC Remove the gas analysis container from SRC and open. Remove o-ring seal Hand container to CDR Hold container for LMP Use tongs to collect a small rock fragment from bulk sample area and place in container. Seal container and place in SRC Detach tongs and place in ETB Recover SWC: Use scoop to collect rocks and loose material. Fill large sample bag to designated weight or volume Move to SWC Withdraw staff from surface Roll up foil Rotate foil roller to detach position and remove from staff Let staff rest on surface, vertically and with only its weight acting on surface, report depth of penetration Push staff into surface as deep as possible Assess amount of force applied and staff depth If time permits photograph staff and repeat e and f several times. Check staff rigidity in surface Carry SWC foil to MESA Place bag in SRC. Seal bag Remove SWC bag from temporary stowage on MESA and open Hold bag for CDR Insert foil into bag Seal SWC bag and place in SRC Collect second core tube sample if time available (See procedures on page 55) If time not available assist CDR Place York mesh sample (in SRC lid) in SRC. Place packing material in SRC to minimize void space 68 �CDR - T r a n s f e r b u l k sample SRC and magazine: ( I f t h e r e i s time f o r t h e t r a n s f e r of only one SRC, t h e b u l k sample SRC w i l l be t r a n s f e r r e d ) a . Extend loop end of LEC u n t i l s e c t i o n of s t r a p going t o A/S i s t a u t b. Grasp loop g r i p on t h e LEC top l i n e c. L i f t SRC from s t r u t d. Walk t o t h e f r o n t of t h e . l a d d e r w i t h SRC suspended on LEC e. Walk away from l a d d e r ( i n +Z d i r e c t i o n ) w h i l e h o l d i n g LEC t o p . s t r a p (loop) t o t r a n s f e r magaz i n e and SRC t o A/S Assist CDR, i f r e q u i r e d Disconnect and t e m p o r a r i l y stow SRC and camera magazine P r e p a r e f o r t r a n s f e r of documented sample SRC: a. P u l l LEC lower l i n e t o t r a n s f e r LEC hooks t o surface b. With LEC hooks i n hand, walk t o SRC on MESA c. Attach LEC lower hook t o SRC t o p - l e f t f r o n t b r a c k e t and l o c k hook d. A t t a c h upper ( r i g h t ) hook t o SRC t o p - r i g h t r e a r b r a c k e t and l o c k hook T r a n s f e r SRC: a. Extend loop end of LEC u n t i l s e c t i o n of s t r a p going t o A/S i s t a u t b. Grasp LEC t o p l i n e by loop g r i p �CDR - c. L i f t SRC from t a b l e d. Walk t o t h e f r o n t of t h e l a d d e r w i t h SRC suspended on LEC e. Walk away from l a d d e r ( i n +Z d i r e c t i o n ) w h i l e h o l d i n g LEC top s t r a p loop t o t r a n s f e r SRC t o A/S A s s i s t CDR, i f r e q u i r e d ~ e s t l c h e c kEMU Disconnect and t e m p o r a r i l y stow SRC XVII. CDR EVA TERMINATION Clean EMU by d u s t i n g w i t h hands and wiping o r k i c k i n g b o o t s a g a i n s t footpad Change SC FR t o 1 2 / s e c Ascend t o p l a t f o r m Disconnect LEC from ascent stage Receive and d i s c a r d end of LEC away from LM Hand end of LEC through h a t c h t o CDR Ingress A s s i s t CDR, i f r e q u i r e d J e t t i s o n ECS c a n i s t e r and b r a c k e t , OPS b r a c k e t s (adapt e r s ) , 3 a r m r e s t s , bag of used u r i n e bags Close h a t c h Repressurize cabin �SECTION 4.0 ALTERNATE AND CONTINGENT PLANS �4.0 ALTERNATE AND CONTINGENT PLANS 4.1 Alternate EVA (With S-band Erectable Antenna ~eployment) An alternate timeline is presented for the situation in which deployment of the S-band erectable antenna is required. Such a situation will occur if the Goldstone or Parkes (~ustralia) 210-foot antennas are not in view and the communications capability with the LM steerablel85-foot antenna combination is not sufficient to simultaneously obtain acceptable W coverage and voice-biomedical and telemetry data. Thus, due to the present uncertainty of the communications capability - possible unsatisfactory equipment performance and/or contingencies which may cause mission event times to vary so that a 210-foot antenna is not in view, the erectable antenna will be carried on the mission and a real time decision made to deploy or not deploy it, i.e., follow the alternate or the nominal timeline. With the addition of the erectable antenna deployment, the major impact to the timeline is the reduction of time available for the documented sample collection. Also, for the alternate timeline, the LMP must delay his egress to switch to the erectable antenna after the CDR has deployed it. �4.1.2 WITH DEPLOYMENT OF S-BAND ERECTABLE ANTENNA SUMMARY TIMELINE ALTERNATE LUNAR SURFACE EVA b t r r ~ v ~ corm r a rvr I I �1.50 2 a00 2r10 2.20 2.40 1.30 ...t..,..r*............... ...................................................... ................................................. z; I P ~ CSI o o c u r r r r r o s ~ u r r rc o r r c c r ~ o r LY* *.ESTPMOIO ng .OVU6MT 1 S11C *l..I C L O I I . " I .OCPLW LI'EXP. .IOIO I I I ElKlUL.IS ursrm 0 r o* . . j 1c. TO rue 0 5 Ale& o"0,r SlYPLI I c ~ ~ t c r ~ o r *lclalCVE sru L ,L". , " I . , Slit ' 11~. t o OZPLOI .KROl 01 .. 1.50 snrr ICLOSIY. .cL~." I E Y 1 ICRYIWIIO~ CYU YYPLE ."*I101 L ~ r c a c s sc r s l m ! 0C"rcl IOOLS ru .OUK.TC b c o r ~ e r SIYOLES .PAC" YYeLIs Rwros 2.00 CWIPYIII marc* U141SS Cllll I I I I I I I 7U.C PASSNC S C l S W U P . 1 C.011 *JElItSOll .SCCUIC j SCI ,IIST.RIOlO .nr.uc 0s C S. e n n s r c a o r sac I Am0 S f O l 5% LADDIm *t.Cacss I *CLOSC EYY *A%tW I CWUO. o o c v v c n l t o wrrrr c m r r c r ~ o m * m v c l V L l SIC 1 0 .CLCA# AMD SIOLL I * S T 0 1 LLSCC r l l Y Y O T O S.r.LImG *rcr*re wuprc (1YEl.S t~.hvra f::rt;it*m8&L;M~C PDros 2.10 . I I . i I sra crvenr lltCCIYt u.cul"c 8 SIW V C . jI bI ltCElVE sac 2 rJ0 2.30 2.40 �4.1.3 ALTERNATE TIMELINE LUNAR SURFACE EVA CDR HRtMIN LMP - LMP - CDR - II + %R MONITOR ACTIVITY PLAY OUT LEC MOVE TO POSITION AND RELEASE MESA 1 I I t + TV ON FOR CHECK* START SEQUENCE CAMERA (SC) + DESCEND TO FOOTPAD CHECK ASCENT PROCEDURES PLAY O ~ LEC T I TURN TV ON '(AND OFF)* CHANGE SC FR TO 24/SEC I CHANGE SC FR TO 121SEC STOW LEC T STEP TO SURFACE RESTICHECK EMU 4- + I T VISUALLY MONITOR CDR A C T I V I T Y PROVIDE CHECKLIST ASSISTANCE CHECK AND DISCUSS BALANCElSTABIL I T Y WALKING CAPABILITY *TV LEFT ON I F SATISFACTORY 1 , TELEMETRY AND CHANGE SC F I L M MAG VOICE-BIOMED CHANGE FR, TO 6/SEC 1- DATA RECEIVED A II I CDR LEC ' MISSION I APOLLO 11 I EDITION FINAL I 1 DATE 1 JUNE 27, 1 9 6 9 MISSION TIME 112+30 - 112+54 I DAY/ REV 5/19 I W6E 1 of 7 I �ALTERNATE TIMELINE CDR HRtMIN LMP T + RESTICHECK EMU I I 6 T DEPLOY HANDLE I EXTEND BAG COLLECT SAMPLE 4DETACH BAG AND LMP - REMOVE S-BAND ERECTABLE AIITEliNA FROM S/C CHECK LM-L AND EMU $TART sc t UNSTOW CSC AND - CDR II CtiECK LM AND EMU I t CHANGE CARRY ANTENNA TO DEPLOYMEiVT S I T E SC% TO B/SEC I MONITOR CDR ACTIVITY t ORIENT ANTEIIIjA REMOVE TOP CAP DISCARD HANDLE -L I I STOW SAMPLE t I TRANSFER S T I L L CAMERA TO SURFACE PROVIDE CHECKLIST ASSISTANCt EXTEND MAST AND LEGS PREPARE FOR CAMERA TRANSFER ASSIST CDR C I + REMOVE THERMAL COVER AND L I F T ANT. ONTO LEGS CHANGE SC FR TO 11SEC + REMOVE DEPLOY BAR AND R I B T I P PROTECTOR t CHECK AND REPORT LM STATUS 3- I CHAijGE SC FR TO l / S k C OPEN ANTENNA D I S H I t MONITOR CDR ACTIVITY PROVIDE CHECKLIST ASSISTANCE t CHECK TERRAIii ANij LIGHTING t REMOVE CABLE FROM MESA MONITOR CDR A C T I V I T Y I 1, MISSION AF'OLLO 11 I I EDITION FINAL I I I DATE JUNE27,1969 MISSION TIME 112+54-113+18 I DAY/ IW 5/20 I PAOE 2 of 7 �ALTERNATE TIMELINE CDR - LMP - LMP CDR - II T t T ATTACH CABLE TO ANTENNA STEP TO SURFACE REST/CHECK EMU CHANGE SC F I L M MAG. t 1 ROUGH ALIGN ANTENNA I PREPARE MESA FOR TV DEPLOYMENT I MONITOR CDR A C T I V I T Y CHECK BALANCE/STABIL I T Y I REMOVE TRIPOD -1 I CHANGE FROM WA TO L D LENS S-BAND T ~ I L U N A RSTAY TURN ~ T VON CHECK COMM, LM, AND EMU DETERMINE "GO" FOR EVA PLACE SPARE CAMERA ON L L F L O O R REORIENT SC REST/CHECK COMM AND EMU I T + REMOVE CAMERA AND PLACE ON TRIPOD + CARRY TV TO DEPLOY S I T E MISSWN 1 EDITION FINAL I I JUNE 4 + MOVE NEAR LMP REST/CHECK EMU 27, 1969 REMOVE SWC' FROM MESADEPLOY I N SUNLIGHT + P H O T L SWC I DATE ERECT SRC TABLE PLACE TV FOR SUB. EVA CHECK ASCENT PROCEDURE rC, rC, t TAKE FAST SCAN PANORAMA OR SEVERAL POINTS OF, INTEREST t PERFORM COMM CHECK I I + + MONITOR AND DESCEND TO PAD PHOTO LMP PULL TV CABLE FROM MESA t MOVE THRU HATCH CHECK INGRESS PROCEDURE MONITOR AND PHOTO EGRESS APOLLO 11 I DETERMINE WALKING C A P A B I L I T Y MISSION TIME 113+18 - 113+42 I DAY1RN 5 /20 1 1 PAGE 3 of 7 i �ALTERNATE TIMELINE LMP PLACE CAME$ ON MESA PREPARE 'MESA FOR BULK SAMPLE COLLECTION t t PREPARE ALHT AND SRC LIGHTING/VISIBILITY AND TERRAIN I N SHADOW EVALUATE AND REPORT EVA CAPABILITY AND EFFECTS ON SURFACE (TETHER CAMERA WHEN REQUIRED) REST/CHECK EMU PHOTO QUAD I t I PACK SRC EVALUATE AND REPORT LIGHTING/VISIBILITY AND TERRAIN I N SUNLIGHT REPORT STATUS AND PHOTO +Z GEAR PHOTO BULK SAMPLE AREA I t REMOVE ALSCC FROM MESA AND DEPLOY CONNECT LEC I MISSION APOLLO 11 I I CARRY ' ALSCC REPORT STATUS QUADI I V EVALUATE AND REPORT LIGHTING/VISIBILITY AND TERRAIN AT SHADOW EDGE COLLECT ROCKS AND LOOSE MATERIAL 1. I I REPORT' STATUS +Y GEAR I I EDITION FINAL I PHOTO + EVALUATE T E R R A I N / V I S I B I L . I T Y TAKE PHOTO PANORAMA TAKE CLOSE-UP PHOTOS k I DATE ( JUNE 27, 1969 M I S S I O N TIME 113+42 - 114+06 I t I t PHOTO QUAD I V DAY/ REV 5/20 + Y GEAR I t TAKE PHOTO PANORAMA /I. I PAGE 4 of 7 1 �A L T E R N A TTIMELINE E LMP - CDR - I, PHOTO QUAD I11 CARRY C A ~ E R A STO DEPLOY S I T E REPORT POSITION FROM LM CDR LMP - 2: REPORT STATUS QUAD I11 I I t t 1 REPORT STATUS -Z GEAR PHOTO -Z GEAR + I CARRY PSE TO DEPLOY S I T E I t TRANSFER CAMERA TO CDR t I REPORT STATUS DEPLOY PSE PHOTO L R ~ OPEN SEQ BAY DOOR I I AND PHOTO QUAD 11- I' T PHOTO EASEP OFFLOAD MOVE TO PSE t t REPORT STATUS AND PHOTO -Y GEAR + PHOTO PSE + MOVE BULK SRC TO STRUTS OR FOOTPAD RESTIPH'OTO LMP TAKE CLOSE-UP PHOTOS REMOVE ALSCC F I L M AND STOW I N S U I T I DEPLOY S I T E APOLLO 11 1 MOVE MESA RESTICHECK EMU MOVE TO QUAD I V . I PHOTO EASEP OFFLOAD TAKE CLOSE-UP PHOTOS I TAKE CLOSE-UP PHOTOS REMOVE PACKAGE 2 ( L R ~ ) TAKE PHOTO PANORAMA MISSION t T REMOVE PACKAGE 1 (PSE) EDITION FINAL I 1 PREPARE DS SRC AND SAMPLING EQUIPMENT L I DATE JUNE 27, 1 9 6 9 MISSION TIME 114+06 - 114+30 I DAY/R€V 5/20 I PAG€ 5 of 7 I �r ALTERNATE TIMELINE LMP &C -L TETHER SA%E LMP - II ASCEND TO PLATFORM t BAG TO LMP COLLECT CORE TUBE SAMPLE UNSTOW GNOMON SELECT DS AREA MOVE TO DS AREA PHOTO DS AREA + LI t INGRESS I CHECK LM A N D EMU REMOVE S T I L L CAMERA MAGAZINE AND CONNECT TO LEC 1 T I REORIENT CAMERA DESCRIBE AND COLLECT SAMPLES . PHOTO SAMPLES AND SAMPLE AREA ASSIST LMP I t. 4- MOVE TO MESA PLACE SAMPLES I N SRC RETRIEVE AND STOQW C MOVE TO MESA PLACE TOOLS I N ETB PACK SRC CLOSE AND SEA; SRC MOVE TO' LADDER CLEAN EMU MISSION I APOLLO 11 1 I TRANSFER BULK SAMPLE SRC AND CAMERA MAG. I- 1 EDITION FINAL - I DATE C t DISCONNECT AND STOW SRC AND CAMERA MAG. REST/CHECK EMU I LOWER LEC I I JUNE 27, 1969 ASSIST 'CDR, I F REQUIRED 1 MISSION 114+30 - 114+54 DAY! REV 5/20-21 I PAOL 6 of 7 I �LMP CDR I JETTISON EQUIPMENT CLOSE HATCH 1 '"f CABIN REPRESS �4.1.4 Detailed Procedures Refer t o t h e Nominal Lunar EVA Detailed Procedures Section 3.5, f o r t h e procedures which precede t h e S-band Erectable Antenna Deployment. LMP - CDR - S-BAND ERECTABLE ANTENNA DEPLOYMENT Transfer antenna t o deployment s i t e : . a. Walk t o antenna stowage p o s i t i o n ( ~ u a dI ) . . b . Remove thermal s h i e l d c . Remove Velcro s t r a p s and p u l l t o r e l e a s e p i n s a t base of antenna d. Grasp antenna- by deployment . "shimmy" b a r and folded l i f t handle ' e . P u l l antenna o u t and down by l i f t handle t o c l e a r LM s t r u c ture f . Hold antenna by deployment b a r and deploy f o l d e d l i f t handle by p u l l i n g handle o u t of stowage d e t e n t and down t o ' l o c k e d position g. Rotate antenna t o h o r i z o n t a l p o s i t i o n and c a r r y t h e antenna t o t h e deployment s i t e by t h e . shimmy b a r (NOTE: The s i t e t o be used should provide a c l e a r view of Earth and b e approximately 20 f e e t from t h e MESA). h. Place - t h e antenna down with t h e bottom antenna handle r e s t i n g . . on t h e s u r f a c e and t h e orientat i o n arrow on top cap pointing , t o Earth. , When CDR moves i n t o SC f i e l d of view, change SC frame r a t e t o 6/sec �CDR - Remove t o p cap: a. b. c. Release each of t h e t h r e e l e g clamps by r o t a t i n g them out and down Depress t h e t h r e e l e g t i p s and push them r a d i a l l y outward t o f r e e t h e antenna t o p cap Discard metal t o p cap and foam piece i n a r e a away from t h e LM Raise antenna mast : While holding t h e antenna vert i c a l , grasp antenna horn t o p p l a t e and r a i s e t h e first s e c t i o n of t h e antenna feed support. (insure t h e f i r s t s e c t i o n only i s deploying by applying a 2-finger pressure on o u t e r mast section. The outer s e c t i o n has orange stripes. ) Do not touch h e l i x eleCAUTION: ----ment when extending feed assembly .b. Check f i r s t s e c t i o n f u l l y deployed and locked i n detent c. Extend t h e second antenna feed s u p p o r t , s e c t i o n i n t h e same manner a s t h e f i r s t . Check t h e second s e c t i o n f u l l y extended and locked i n detent. a. Deploy t r i p o d : a. b. Extend antenna l e g s by placing 2 f i n g e r s about t h e l e g s e c t i o n and applying f o r c e against loops on e i t h e r s i d e of l e g . Continue t o extend each l e g s e c t i o n t o t h e proper' l e n g t h , i .e., t h e proper p a i n t r i n g and lock with clamps. Check adequacy of each l e g lock Check antenna point toward e a r t h by arrow on r i b programmer IMP - �IMP - CDR - Move around t o t h e r i g h t i n t o t h e antenna l i f t i n g position by t h e shimmy bar P u l l each of t h r e e Velcro l e g retension s t r a p s and l e t the l e g s f a l l outward t o a horizontal position on t h e surface Remove thermal covering from antenna and discard away from LM L i f t t h e antenna from t h e surface using both hands on t h e shi,pmy bar u n t i l t h e antenna i s high enough t o permit t h e crewmember t o . g r a s p the lift handle While holding t h e antenna a l o f t with one hand, grasp l i f t handle with other hand L i f t t h e antenna t o t h e high detent position Check each l e g locked securely i n detent by holding the antenna a l o f t with one hand,and pushing outboard on the l e g s individually Set antenna on surface Release p u l l pin fastener a t base of shimmy bar. P u l l deployment bar down and away from antenna Discard bar i n t h e area away from the Firmly implant each l e g i n t o surface ' Open antenna r e f l e c t o r : a, b. c. d. e. Remove r i b t i p protector and allow it t o s l i d e down antenna l e g t o surface Uncoil antenna r e f l e c t o r r e l e a s e cable from around antenna. Hold cable t a u t and i n s t r a i g h t l i n e t o plunger Remove release t r i g g e r guard pin and discard i n area away from IM Graps an antenna l e g with f r e e hand and position s e l f a t arms length from l e g With head down, squeeze release t r i g g e r t o deploy antenna dish. �CDR - IMF - Attach antenna cable: Walk t o f r o n t of MESA, a d j u s t MESA i f necessary P u l l Velcro s t r a p s t o f r e e l e f t s i d e of thermal blanket Unfold lef't s i d e of blanket t o permit easy access t o cable Release antenna cable connector by p u l l i n g Velcro t a b and snap f r e e Grasp cable connector and pass t h e connector under t h e MESA support s t r a p With cable connector i n hand, walk t o t h e lef't of t h e antenna Walk p a s t t h e antenna and deploy t h e cable completely ( u n t i l black and white s t r i p e d section visible ) Walk t o antenna ,Connect antenna cable by mating t h e two connector p a r t s t u r n i n g t h e outer p a r t clockwise a s viewed from cable end Change SC FR t o l / s e c - Rough a l i g n antenna: a. b. c. d. e. Move around antenna l e g t o rough antenna alignment p o s i t i o n Unstow alignment crank by pushing down and away on crank handle Uncoil crank cable by passing crank wound and behind t h e ant enna base Rough a l i g n antenna i n p i t c h (CCW r o t a t i o n of t h e handle p i t c h e s t h e antenna down) Rough align'antenna i n azimuth. Pull antenna crank out from housing then r o t a t e handcrank t o change antenna azimuth Change SC f i l m magazine when necessary �Fine a l i g n antenna: a. b. c . Press each l e g i n t o surface Check antenna alignment by s i g h t i n g along antenna mast and using o p t i c a l alignment s i g h t Fine a l i g n antenna, a s required, by using remote c o n t r o l crankhandle "in" f o r p i t c h and "out" f o r azimuth Rest-check communications and EMU systems. Take one photo of antenna Switch t o e r e c t a b l e antennaS-band s e l e c t o r t o "Lunar stay" (FM, Mode 10) Perform communications check. Check s i g n a l s t r e n g t h indication > 1.0. Verify voice and telemetry with MSFN. Check LM and EMU systems. Determine "GO" f o r EVA Refer t o t h e Nominal EVA procedures, Section 3 . 5 , f o r t h e LMP I n i t i a l EVA procedures. �4.2 Contingent EVA 1 - Minimum Time, One Man 4.2.1 Description and Rationale For various reasons, on the first lunar landing mission only a very limited time may be available to accomplish the,EVA.* For such a situation the choice of objectives are, first, those with the highest priority and, secondly, those which can be accomplished in a Short period of time and do not require the accomplishment of a previous task. The timeline presented here, referred to as the Contingent EVA 1 or Minimum-Time, One-Man EVA, is to optimize the accomplishment of the choice of objectives by providing the maximum data return for the minimum amount of time expended. ( ~ M n A timeline of approximately 49 minutes). There are several other considerations which enter into the selection of the tasks and the procedural detail of the activities for a minimum time EVA. As this will be an unplanned or contingent EVA, it is desirable to have the procedures and sequence of events closely related to the nominal. Either crewman should be equally capable of conducting the desired tasks and contributing to the data returned. And in general, to achieve the maximum diversified data collection, the crewman on the surface will not go into the procedural detail, particularly with verbal descriptions, as he is expected to in the nominal timeline. In this contingent EVA, for the environmental familiarization, the crewman will spend only enough time to assure himself that he can safely proceed with the EVA. After the contingency sample collection he will continue to become more adapted to the new environment as he conducts a limited EVA evaluation. PrimariLy, this EVA evaluation will involve a brief investigation to determine an astronaut's general capabilities or limitations for conducting EVA tasks within the lunar environment. Photographs taken during this evaluation will be a postflight aid to the crewman's recall and the documentation of this activity. A limited LM inspection, with very brief comments and several documentary photographs, can be conducted for the forward half of the spacecraft within a few minutes. To conclude the surface activity the crewman will take a photographic panorama and possibly a few additional photographs of documentary value. In conclusion it should be mentioned that the crewman's surface activity will be confined to an area where he can be constantly monitored by and in communications with the crewman inside the LM. Practically all of the activity can be documented with the sequence camera, and, if the communications capability exists, with the TV. Also, there should be sufficient time and activity for a thorough PLSS analysis. The final Flight Mission Rules for Apollo 11 wil1,govern the selection of the crewman to egress and the EVA he will accomplish. . . ' 86 �4.2.2 T I M E SCALE q C O W N011nr D HODUU ( . .-. E H I LllL SUMMARY TIMELINE CONTINGENT EVA I I0 . ACTIVITY C S M l l M COMM I MCC-H ACTIVlTV I P A R A T C S YUOM UOCKS W S T N l T V t CWRDIMTED TASKS I I. F I ~ LVRE-LVA OI(MTIDUS #DEPRESS FROM 3.) PSI b SEQlENX CALTRA C M R A Q ~ C W E M A C E b FRAME W ~ c w r n ~ c r C . INITIAL N A tcouu T V COVERAGE 1FRAYVYC I1 MINIMUM TIME, ONE MAN COMMANDER ACllVlTY cnrcr ORELEASE Y Y I 0.LRFORU C l U L SYSlLYS CHECKS I 12 F R A U E ~ C . ~DETERUIML GO FOI EVA 24 F R A Y E V I f C 0 1CcoveACE BXgl Y U I C M ~ E OfCTIVATE SEQUENCE CAULMA LM PILOT ACTIVITY IDEPLOV LEE AS SAFETY UOUITOR I l M E SCALE OASCEND LADDER OCOLLECT SAMPLE ODETACH B I C L GISCUD MMDLE OIYCRESS U B I N .+z ORESIXMECI: EMU . OP(IWIDE CHECKLIST ASSISTA*CE I I OP((OT0CRAPWI DA , @ . I +.Y CLU OJETTISOM EPUINENT .SECURE MTCH 1" OREPRESSURIZE CABIN 1-1 GEAR f REV. YLRCH I ITRAMSFER STILL CAYERA 1 0 SURFACE 4.2.2 OR: HENORICKS CH SUMMARY 1IMELINE c o m r l m c r n EVA I (US% Y M . 1969 � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000072 Title A name given to the resource Final Apollo 11 Lunar Surface Operations Plan. Description An account of the resource Prepared by the Lunar Surface Operations Office, Mission Operations Branch, Flight Crew Support Division. Creator An entity primarily responsible for making the resource Wood, William H., Jr. Manned Spacecraft Center (U.S.) Date A point or period of time associated with an event in the lifecycle of the resource 1969-06-27 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Apollo 11 (Spacecraft) Lunar surface vehicles Project Apollo (U.S.) Saturn Project (U.S.) Saturn launch vehicles Space flight to the moon Space vehicles--Moon--Landing Type The nature or genre of the resource Reports Text Source A related resource from which the described resource is derived Saturn V Collection Box 32, Folder 10 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000051_000074 https://digitalprojects.uah.edu/files/original/20/1155/spc_stnv_000071.pdf b1640a68a7f1bcbf1b664bdfa25ace14 PDF Text Text . J I k @ NATIONALAERONAUTICS AND SPACE ADM*lSTRATlON TELS WASHINGTON,D .C. 20546 WO 2-4155 W 0 3-6925 FOR RELEASE: ~ D I A T E m y 7, 1969 RELEASE NO: 69-68 PROJECT:&pow 19 SATURN !-llSTORY DOCUMENT University of Alabama Research lnstitcrk History of Science G. Technology G ~ w ------- - - - DOC.NO. Date S *S ------a- GB#ERALWSE--------------------------------------------1-7 WSSIOM oBJgc~s-----------------------------------------~-lo A ~ U X ) 10 ~~~~~---------------------------------------11-1 HISSIOBi CPWAJECTORY AND MHBWER DESCRImION----------------14 Launch Evenes-------------------------------------------15 m r s l o n E;vants---------------------------------------------l6-18 m t h ]Pa** Opblt-------------------------------------19 Wan8l-r Injection-------------------------------------19 Tranarposition, Daoklng and $;leetion---------------------- 19 'pransl-r Coaet-----------------------------------------2Q L m r Orbst Im%erti~n------------------------------------20 Lunar Parking Orbit L W-Autive Rendezvous---------------20-22 K I Transearth Injecti~n------------------------------~-------22 wasearth Caa~t----------------------------------------22 mtrg mding--------------------------------------------22 O~~TIQ~S--------------------------------------APOLLO 10 A L ~ A T MIISJSIOH~--------------------------------~~-~~ E ABORT MoDES------------------------------------------------29 Deep Smae Abort@---------------------------------------- 29-31 APOLLO 10 a0/#0-80 DBCISIOM POImS------------------------ 32 O m R D mf;EfISIOM----------------;.----c-------------------APOLm 10 PBQmQRAPHIC TASKS------------------------------3 MHAR DESCRIPTION------------------------------------------35 pol lo Lunar mdiw ~ites-------------------------------36-37 COMMAND M D SBFtVICE MODULE STIPFICTURE, SYS'PElrtS---------------38-39 Y CSH Systees---------------------------------------.----.39-41 S~UCSTTL;ZES, UEIG~----------------------------~~ Ascent St;age-------------------------------------------- L W HOW ~ I)escent Stwe-------------------------------------.----. m w Module System------------------------------------A448 �Conteats Continued SAmRH W U W C R VEHICLE DESCRIPTIOM & OPERATIO&----------- 4 9 pipst Stage--------------------------------------------49 Second Stage--------------------------------------..----49-50 Stags---------------------------------------------50-51 nt Unit-----------------------------------------Ina 51-52 on----------------------------------------------Pro 52-53 Munch Vehicle Instrumentation and Communication---------53 Restapt-------------------------------------------S54 -55 APOEW 10 CRW-----------------------------------------------56 L i f e Support Equipment Space Suits--------------------56-57 - Heala---------------------------------------------------2;-62 Personal mgiene----------------------------------------$upviva& aeap--------------------------------------------63-64 Biomedical Lnflight lulsnitoring---------------------------a Regt-Wopk Cgcles------------------------------------------& waAnbg--.-----------------------------------------------65-66 Crew B&~gratphres-----~------------------------~---------67-72 &BI.uNcHQPEWONS-r,---------------------------73 Prelamch Preparakions----------------------------------73-75 u u H c R @omem39------------------------------------------76 a h i e l e Assembly m%ld$ng-------------------------------77-78 h m e h Control Center-----------------------------------78-79 Mob$le Launchep-------------------------------------------79-80 ABOLLX) T~~nsporker------------..---------------------------------80-81 Cpawlemaye-----------------------------------------------8l Mobile Service Stmewre---------------------------------81-82 Water mbwe System--------------------------------------82 m n e k and Deflector--------------------------------82-83 Pad areas------------------------------------------------83-w Mfasfsn control Centep---------------------------.--------84-85 ~~1aw" WC~WORK---------------------------------~~-~$ p ations ~etwork------------------------------8$-89 teps---------------------------------------- 89-90 Ships-----------------------------------------90-91 Xnrstrumentrttion Aircraft (ARIA)-------------91 0110 lo-----------------------------92 ye----------------------------------93 Is---------------------------------9 -95 luraJor Apollo/Saturn V Cont~actors-----------------------2-97 98 102 APOLLO GLOS ----,-,i,---------------------AI? ACRO A m mBRNmTxONS---------------------------103-l& CO SIOW ~s----------------------------.------------105 106 - - �LI Y N A T I O N A L AERONAUTICS AND WASHINGTON,D SPACE ADMINISTRATION .C. 20546 TELS' W O 2-4 155 W 0 3-6925, FOR' RE1 R E ~ S ENO: 69-68 APOLU) 10: MANt S NEAREST LUNAR APPROACH Two Apollo 10 astronauts w i l l descend to within eight nautical miles of the Moonls surface, the closest man has ever been to another c e l e s t i a l body. A dress rehearsal for the first manned lunar landing, Apallo 10 is scheduled for launch Mag 18 at 12:49 p.m. EMP f r o m the National Aeranautfca and Space Adlainistration's Kennedy Space Center, Fla. !?he eight-day, lunar orbit mission will mark the first time the complete Apollo spacecraft has operated around the Moon and the second manned flight for the lunar module. Pollowlng c l o s e l y the time line and traJectory t o be flown on Apollo 11, Apollo 10 w i l l Include an eight;-houp eequence o f lunar module (W)undocked a c t i v i t i e s during which the c o m d e r and Ijl p i l o t w i l l descend t o within eight nautical milea o f the lunar surface and later rejoin the colllmajld/aervice module (CSM) I n a 60-nautioal-mlle circular orbit. �MOON AT EARTH LANDING TRANSEARTH INJECTION ENTRY & LANDING TRANSPOSITION LUNAR ORBIT INSERTION MOON AT EARTH LAUNCH APOLLO LUNAR MISSION �A l l a s p e c t s of Apollo 10 w i l l d u p l i c a t e conditions of t h e l u n a r landing mission as c l o s e l y as p o ~ ~ i b l e - - S u angles n a t Apollo S i t e 2, t h e out-and-back flight path t o t h e Moon, and the time l i n e of mission events, Apollo 10 d i f f e r s from Apollo 11 i n t h a t no landing w i l l be m d e on t h e Moon's surf ace, Apollo 10 is designed t o provide a d d i t i o n a l operational experience f o r t h e crew; space vehicle; and mission-support f a c i l i t i e s during a simulated lunar landing mission. Among d e s i r e d data p o i n t s t o be gained by Apollo 10 a r e 3.44 systems operations a t lunar d i s t a n c e s a s well as o v e r a l l mission o p e r a t i o n a l experience. The was s u c c e s s f u l l y checked - out i n Earth o r b i t i n Apollo go i n c l u d i w a rendezvous sequence simulating l u n a r o r b i t rendezvous. Space navigation experience around t h e Moon is another b e n e f i t t o be gained from f l y l n g a r e h e a r s a l mission before making a l u n a r landing, More knowledge of t h e l u n a r p o t e n t i a l , o r g r a v i t a t i o n a l e f f e c t will provide a d d i t i o n a l refinement of Manned Space F l i g h t Metwork tracking techniques, and broad landmark t r a c k i n g w i l l b o l s t e r t h l s knowledge, �- Analysis of l a s t Becemberls Apollo 8 l u n a r o r b i t mission t r a c k i n g has aided refinement of t r a c k i n g and navigation techniques and Apollo 10 should reduce e r r o r margins s t i l l f u r t h e r . Apollo 10 crewmen a r e Commander Thomas P. S t a f f o r d , Command Moudle P i l o t John W e Young and Lunar Module P i l o t Eugene A. Cernan. The mission w i l l be t h e t h i r d apace f l i g h t f o r S t a f f o r d (Gemini 6 and 9 ) and Young ( ~ e m i n i3 and l o ) , and t h e second f o r Cernan ( ~ e m i n i9 ) . t h e Apollo 7 backup crew. The three were recycled from The Apollo 10 backup crew i a Com- mander L. Gordon Cooper, Command Moudle P i l o t Donn F. E i s e l e and Lunar Module P i l o t Edgar D, Mitchell. S t a f f o r d i s an A i r Force Colonel; Young and Cernan are Navy Commanders. If necessary, t h e backup crew can be s u b s t i t u t e d f o r t h e prime crew up t o about two weeks p r i o r t o a n Apollo launch. During t h i s period, t h e f l i g h t hardware and software, ground hardware and software, f l i g h t crew and ground crews work as an i n t e g r a t e d team t o perform ground simulations and o t h e r tests It i s necessary t h a t t h e f l i g h t crew of t h e upcoming mission. t h a t w i l l conduct t h e mission t a k e p a r t i n t h e s e a c t i v i t i e s , which a r e not repeated f o r t h e b e n e f i t of t h e backup crew. To v do s o would add an a d d i t i o n a l c o s t l y two-week perlod t o t h e prelaunch schedule, which, f o r a l u n a r mission, would r e q u i r e rescheduling f o r t h e next l u n a r window. �-4- The Apollo 10 rendezvous w i l l be t h e f i f t h space rendezvous i n which S t a f f o r d has taken part--Gemini 7/6 and t h e w o r l d ' s first rendezvous, and t h r e e t y p e s of rendezvous with t h e augmented t a r g e t docking a d a p t e r i n Gemini 9 , The Apollo 10 mission time l i n e can be d e s c r i b e d as a combination of Apollo 8 and Apollo 9 i n t h a t i t w i l l be a l u n a r o r b i t mission w i t h a CSM-LM rendezvous, Apollo 8 was a l u n a r o r b i t mission with t h e command/service module only, while Apollo 9 w a s an E a r t h o r b i t a l mission w i t h the complete Apollo s p a c e c r a f t and included a LW-active rendezvous w i t h t h e CSM. Apollo 10, a f t e r l i f t o f f from Launch Complex 39B, w i l l begin t h e three-day voyage t o t h e Moon about two and a h a l f hours a f t e r t h e s p a c e c r a f t is i n s e r t e d i n t o a 100-nautical mile c i r c u l a r E a r t h parking o r b i t . The Saturn V launch v e h i c l e t h i r d s t a g e w i l l r e s t a r t t o i n j e c t Apollo LO i n t o a t r a n s l u n a r t r a j e c t o r y as t h e v e h i c l e p a s s e s over A u s t r a l i a mid-way through t h e second r e v o l u t i o n of t h e Earth. The "go" f o r t r a n s l u n a r i n j e c t i o n w i l l f o l l o w a complete checkout of t h e s p a c e c r a f t ' s r e a d i n e s s t o be committed f o r i n jection. About a n hour a f t e r t r a n s l u n a r i n 3 e c t i o n (TLI), t h e command/service module w i l l s e p a r a t e from t h e Saturn t h i r d stage, t u r n around qnd dock with t h e l u n a r module n e s t e d i n t h e s p a c e c r a f t IlvI a d a p t e r . Spring-loaded l u n a r module holddowns w i l l be r e l e a s e d t o e j e c t t h e docked s p a c e c r a f t from t h e a d a p t e r . �-5- Later, l e f t o v e r liquid p r o p e l l a n t i n t h e Saturn t h i r d s t a g e w i l l be vented through the engine b e l l t o p l a c e t h e s t a g e i n t o a " s l i n g s h o t " t r a j e c t o r y t o miss t h e Moon and go i n t o solar orbit, During the t r a n s l u n a r c o a s t , Apollo 10 w i l l be i n t h e so-called passive thermal c o n t r o l made i n whlch t h e spacec r a f t r o t a t e s slowly about one of i t s axes t o s t a b i l i z e thermal response t o s o l a r h e a t i n g , Four midcourse c o r r e c t i o n maneuvers a r e p o s s i b l e during t r a n s l u n a r c o a s t and w i l l be planned i n real time t o a d J u s t t h e t r a j e c t o r y , Apallo 10 w i l l first be I n s e r t e d i n t o a 60-by-170-nautical mile e l l i p t i c a l l u n a r o r b i t , which two r e v o l u t i o n s later w i l l be circularized t o 60 n a u t i c a l miles, Both l u n a r o r b i t I n s e r - t i o n burns (MI) w i l l be made when Apollo 10 Is behind t h e Moon out of " s i g h t " of Manned Space F l i g h t Network s t a t i o n s , S t a f f o r d and Cernan w i l l man t h e U4 f o r systems checkout and p r e p a r a t i o n s f o r a n eight-and-a-half hour sequence t h a t duplicates--except f o r an a c t u a l landing--the maneuvers planned f o r Apollo 11. The LM twice w i l l sweep within 50,000 f e e t of Apollo Landing S i t e 2, one of t h e prime t a r g e t s f o r t h e Apollo 11 landing. �-6Maximum s e p a r a t i o n between t h e IM and the CSM during the rendezvous sequence w i l l be about 350 miles and w i l l provide an extensive checkout of t h e LPlI rendezvous r a d a r as well as of t h e backup VHF ranging device aboard t h e CSM, flown f o r t h e first t i n e on Apollo LO. When the LM ascent stage has docked w i t h t h e CSW and the two crewmen have t r a n s f e r r e d back t o t h e CSM, t h e LM w i l l be j e t t i s o n e d f o r a ground command ascent engine burn t o prop e l l a n t depletion which w i l l place the IN ascent s t a g e i n t o solar oribt. The crew of Apollo 10 w i l l spend t h e remainder of t h e time i n lunar o r i b t conducting lunar navigational t a s k s and photographing Apollo landing sites t h a t a r e within camera range of Apollo 10's ground track. The t r a n s e a r t h i n j e c t i o n burn w i l l be made behind the Moon after 61.5 hours i n l u n a r o r b i t . During t h e %-hour t r a n s e a r t h coast, Apollo 10 again w i l l c o n t r o l s o l a r heat loads by using t h e passive thermal c o n t r o l "barbecue" technique. Three t r a n s e a r t h midcourse c o r r e c t i o n s are possible and w i l l be planned i n r e a l time t o a d j u s t the Earth e n t r y corridor. �-7- Apollo 10 w i l l e n t e r the E a r t h ' s atmosphere (400,000 f e e t ) a t 191 hours 51 minutes a f t e r launch a t 36,310 feet-per-second, Command module touchdown w i l l be 1,285 n a u t i c a l miles down- range from e n t r y a t 15 degrees 7 minutes South l a t i t u d e by 165 degrees West longitude a t a n elapsed time of 192 hours 5 minutes. The touchdown point i s about 345 n a u t i c a l a i l e s e a s t of Pago Pago, Tutuila, i n American Samoa. (END OF GENERAL RELEASE; BACKGROUND IPIFORMATION FOLLOWS) �APOLLO 10 lunch aB/dTrans Lunar njection Astronauts Board' Apollo Trans Lunar Injection S a t u r n Staging Papollo S a t u r n Separation �P O L L O 10 Trans L u ~ . a rF Apollo Midcourse Maneuver Astronauts a t Command Module S t a r b n s �APOLLO 10 Trans Lundr F Final Course Adjustment Navigational Check �APOLFO 10 Lunar Oroita Lunar Orbit Insertion Television Braadcast 9 I Lunw Landmark Tracking Transfer to Lunar Module �APOLLO 10 Descent Orbit Insertion Lunar LBscent and Ren-dezvous Lunar Mceduie! %tag"sng LM Ascent Engine Firing to Depletion Lunar Landmark Tracking �APOLLO 10 Trans - ~ a r t h njection and F Trans Earth Injection ApsBlas Midcourse Maneu ler Navigational Check Final Reentry Preparations �Earth Reentry and Recovery - Command-Service Module Separation Command Module R e e n t r y Splashdown Recovery �MISSION Ol3JECTIVES Although Apollo 10 w i l l pass no c l o a e r than e i g h t n a u t i c a l miles from t h e l u n a r ~ u r f a c e , a l l o t h e r a s p e c t s of t h e mission w i l l be similar t o the f k r s t l u n a r landing mission, Apollo 11, now scheduled f o r July. The t r a j e c t o r y , time l i n e and maneuvers follow t h e l u n a r landing p r o f l l e . After rendezvous i s completed, t h e Apollo 1 0 t i m e l i n e w i l l d e v i a t e from Apollo 11 i n t h a t Apollo 1 0 w i l l spend a n e x t r a day i n l u n a r o r b i t , Additional LP4 o p e r a t i o n i n e i t h e r E a r t h o r b i t o r l u n a r o r b i t w i l l provide a d d i t i o n a l experience and confidence with t h e IM systems, i n c l u d i n g v a r i o u s c o n t r o l modes of t h e Ul primary/abort guidance systems, as w e l l as further assessment of crew time l i n e s . The mission w i l l a l s o t e s t t h e Apollo rendezvous radar a t maximum range (approximately 350 miles vs. 100 miles during Apollo 9). Apollo 10 w i l l mark t h e first space f l i g h t t e s t of t h e s t e e r a b l e S-band antenna and of t h e landing radar, The LM landing radar has undergone numeroue t e s t s i n Earth environment, but t h i s mission w i l l provide a n opportunity t o check t h e l u n a r s u r f a c e r e f l e c t i v i t y c h a r a c t e r i s t i c s with t h e landing r a d a r , Some 800 seconds of landing r a d a r a l t i t u d e a e a s u r i n g data w i l l be gathered as the IIvI makes two sweeps eight nautical miles above Apollo Landing S i t e 2. !Ehis mission w i l l a l s o provide t h e first opportunity t o check t h e very high frequency (VHP) ranging device aboard t h e CSM which s e r v e s as a backup t o t h e LM rendezvous r a d a r , The Apollo 10 mission p r o f i l e provides f u e l and o t h e r consumable reserves i n t h e rsrl. t h a t are g r e a t e r t h a n those planned f o r t h e first LM t o land on t h e Moon. The l u n a r landing mission i s t h e "design mission" f o r t h e Apollo s p a c e c r a f t , and such a mission has smaller although adequate margins of r e s e r v e consumable~. From l i f t o f f through descent o r b i t i n s e r t i o n , Apollo 10 f o l l o w s c l o s e l y t h e t r a j e c t o r y and time l i n e t h a t w i l l be flown i n t h e landing miss4on. Following t h e eight-mile pericynthion, t h e p r o f i l e c l o s e l y simulates t h e c o n d i t i o n s o f l u n a r o r b i t rendezvous af t a r a landing. �The May 18 launch d a t e w i l l produce l i g h t i n g conditions on Apollo S i t e 2 similar t o those t h a t w i l l be present f o r t h e landing mission. A t t h e low i n c l i n a t i o n t o be flown on Apollos 10 and 11 about 1,2 degrees r e l a t i v e t o the lunar equator-Apollo landing S i t e 3 can be photographed and o p t i c a l l y tracked by t h e crew of Agollo 10 i n addition t o t h e p ~ i m eS i t e 2. -- S i t e 1 waa photographed by Apollo 8 i n last December's lunar o r b i t mission and, together with t h e two s i t e s t o be covered i n Apollo 10, photographic, tracking and s i t e a l t i t u d e data on three s i t e s w i l l be in hand. Among the Apollo 10 obJectlves i s the gathering of a d d i t i o n a l Manned Space F l i g h t Network (MSFN) tracking data on vehicles i n lunslr alpbit. While MSFN experience i n tracking Apollo 8 w i l l benefit Apollo 10, t h e r e a r e s t i l l some uncert a i n t i e s , For example, t h e r e is s t i l l some lack of knowledge as t o what t h e exact lunar p o t e n t i a l o r g r a v i t y f i e l d i s and how it a f f e o t s an orbiting, spacecraft. I n tracking Apollo 8, downtrack, o r o r b i t a l timing e r r o r s projected ahead two revolutions were 30,000 f e e t , and o r b i t a l radtus measurements r e l a t i v e t o t h e center of t h e Moon were off 5,500 f e e t . MSFN tracking can produce accurate position and velocity information i n r e a l time while a spacecraft i s " i n view" from t h e Earth and not occulGed by the Moon, but landing and rendezvous operations w i l l require accurate pred i c t i o n s of p e s i t i o n and velocity several revolutions i n advance of t h e e v m t , The lunar p o t e n t i a l apparently a f f e c t s an o r b i t i n g spacecraft d i f f e r e n t l y depending upon o r b i t a l i n c l i n a t i o n and a l t i t u d e . Apollo 10 w i l l be flown on t h e same i n c l i n a t i o n t o the lunar equator a s the landing mission and w i l l provide iflormation f o r refining prediction techniques. Apollo 8 p o s t f l i g h t a n a l y s i s has produced modifications t o tracking a& position prediction techniques which should reduce downtrack e r r o r s t o 3,000 feet and a l t i t u d e e r r o r s t o l,lC00 f e e t . Apollo 10 w i l l allow mission planners t o p e r f e c t techniques developed as a r e s u l t of Apollo 8 tracking a n a l y s i s , Other space navigation benefits from Apollo 10 w i l l ha gained from combinin$ onboard spacecraft lunar landmark tracking data with ISSFN tracking and from evaluating present lunar landing site maps a t close v i s u a l and camera ranges. �Additionally, LEI descent and ascent engine burns will be monitored by HSFN stations for developing useful techniques for tracking powered Pllgbt in future miaslons. �APOLLO 10 COUNTDOWN The clock for t h e Apollo 10 countdown w i l l start a t T-28 hours, with a six--hour built-in-hold planned a t T-9 hours, p r i o r t o launch v e h i c l e p r o p e l l a n t loading. The countdown i s preceded by a pre-count operation t h a t begins some 4 days before launch. During t h i s e r i o d t h e t a s k s include mechanical buildup of both t h e comandAervice module and Uvl, f u e l c e l l a c t i v a t i o n and s e r v i c i n g and loading of t h e super c r i t i c a l helium aboard t h e LM descent stage. A 5% hour built-in-hold i s scheduled between t h e end of t h e pre-count and start of t h e f i n a l countdown. Pollowing are same of t h e h i g h l i g h t s of t h e f i n a l count: T-28 h r s . O f f l c i a l countdown starts T-27 h r s . 30 mins. I n s t a l l launch v e h i c l e f l i g h t b a t t e r i e s ( t o 23 h r s . 30 mins.) LM stowage and cabin closeout ( t o 15 firs.) T-21 hrs. Top off LM super c r i t i c a l helium ( t o 19 hrs ) . Launch v e h i c l e range s a f e t y checks 15 hrs .) (to T-11 hrs. 30 mlns. I n s t a l l launch v e h i c l e d e s t r u c t devices ( t o 10 hrs. 45 mins,) ~ommand/service module pre-ingress operations T-10 h r s . S t a r t mobile s e r v i c e s t r u c t u r e move t o park s i t e T-9 hrs . S t a r t s i x hour built-in-hold T-9 h r s . counting Clear b l a s t a r e a f o r p r o p e l l a n t loading T-8 hrs. 30 mins. Astronaut backup crew t o s p a c e c r a f t f o r prelaunch checks T-8 ~ P S *15 mins. Launch Vehicle p r o p e l l a n t loading, t h r e e s t a g e s ( l i q u i d oxygen i n first stage) l i q u i d oxygen and l i q u i d hydrogen i n second, t h i r d stages. Continues t h r u T-3 hrs. 38 mins. �T-5 h r s , F l i g h t crew alerted T-4 hrs. 45 mins , Medical examination T-4 hrs, 15 mins. Breakfast T-3 hrs, 45 mins. Don space s u i t s T-3 h r s , 30 mins* Depart Manned Spacecraft Operations Buildi n g for LC-39 v i a crew transfer van T-3 hrs. 14 m i n s . Arrive a t LC-39 T-3 hrs. 10 a n s . Enter Elevator t o spacecraft l e v e l T-2 hrs. b mins. Start f l l g h t crew ingress T-1 h r . 55 mins. Mission Control Center-Houston/spacecraft cornmad checks T-1 hr. 50 mins, Abort advisory system checks T-1hr, 46 mins. Space vehicle Ebergency Detection System T-43 mins. Retrack Apollo access arm t o standby p o s i t i o n (12 degrees) T-42 mins, Ann launch escape system T-40 mins, Final launch v e h i c l e range safety checks (to 35 mins, ) T-30 mins, Launch v e h l c l e power t r a n s f e r test ( ~ m tiest ) LM switch over t o internal power T-20 mins. Shutdown U l o p e r a t i o n a l instrumentation T-15 mins, Spacecraft t o i n t e r n a l power T-6 rnins. Space v e h i c l e f i n a l s t a t u s checks to T-10 rnlns. T-5 mins. 30 set, Am d e s t r u c t system T-5 mins. Apollo access arm fully retracted T-3 mins. 10 sec, I n i t i a t e f i r i n g command (automatic sequencer) T-50 see. Launch v e h i c l e t r a n a f e r to i n t e r n a l power �T-8.9 see. Ignition sequence start A l l engines running Liftoff *Note: Some ckianges i n the above countdown are possible as a r e s u l t of experience gained i n the Countdown Demonstration T e s t (C9M') which occurs about 10 days before launch. �lUCSSION TRAJECPORY AND BUUEWER DESCRIPTION Q Note; Information presented herein is based upon a May 1 launch and is subject t o change p r i o r ta the mission or i n real time during the mission t o meet changing conditions,) Iaunch Apollo 10 vdll be launched fran Kennedy Space Center Launch Complex 39B on a launch azimuth that can vary from 7 2 degrees to 108 degrees, depending upon the t3me of day of launch, The azimuth changes with time of day t o perfnit a fuel-optimum injection frm Earth paI?king o r b i t i n t o a free-return circumlunar trajectory, O t h e r factors influencing thelaunch windows are a daylight launch and proper Sun angles on lunar landing sites. The planned Apollo 10 launch date of Hay 18 w i l l c a l l f o r l i f t o f f a t 12:49 p.m. Efi on a launch azimuth of 72 degrees, Insertion i n t o a 100-nautical-=mile circular Earth parking o r b i t w i l l occur at 11 mlrmtes 53 seconds ground elapsed frun launch (GET), and t h e resultant o r b i t will be,inclZnd 32.5 degrees to the Earth's equator. �FLIGHT PROFILE TRANSEARTH lNJECTlON BURN CSM/LM SEPARATION LM PI-IASING BURN EARTH PARKING ORBIT CSM60N.MI. S-IVB RESTART CSM 60 DURING 2ND OR 3RD ORBIT CM SPLASHDOWN & RECOVERY S-IVB 2ND BURN CUTOFF TRANSLUNAR INJECTiON -IVB RESIDUAL / S/C SEPAR~TION', TRANSPOSITION, DOCKING & EJECTION (SLINGSHOT) 60 N.M. LUNAR OF . LUNAR ORBlT ClRCUlARIZATION �SPACE VEHICLE LAUNCH EVENTS/WEIGH!?'S Hrs. 00 00 00 00 00 00 00 00 00 00 00 00 00 i! 0 3 CC I 00 00 00 00 Time Min. 00 (-)08.9 00 00 12 00 21 01 92 32 02 02 . Altitude Sec. 15 40 41 42 11 03 03 03 07 09 09 09 16 21 39 14 15 18 11 11 43 53 : Event : Ignition F i r s t Motion T i l t Initiation Maximum Dynamic Pressure Center Engine Cutoff Outboard Engines Cutoff S-IC/S-II Separation S-I1 I g n i t i o n S-11 A f t I n t e r s t a g e J e t t i s o n LES J e t t i s o n I n i t i a t e IGM S-I1 Center Engine Cutoff S-I1 Outboard Engines Cutoff S-II/S-IVB Separation S-IVB I g n i t i o n S-IVB F i r s t Cutoff Parking O r b i t I n s e r t i o n Naut ~ e l o c l t y 'deight : Pounds M i . : Knots 0 .OO 0 .033 0.12 7 24 35 36 37 49 51 53 97 102 102 102 103 103 0 "0 *3 1554 3888 5324 5343 5335 5581 5642 5701 10977 13427 13434 13434 15135 15139 6,499,016 6,412,918 . I ) 985 2,43;, 1,842,997 1,465,702 1,465,123 -.. . I , 644,128 471,494 364,429 364,343 295,153 295,008 *First two v e l o c i t i e s are space f i x e d , Others are inertial v e l o c i t i e s . Vehicle on launch pad has i n e r t i a l v e l o c i t y of 408.5 meters p e r second (793.7 knots). The above figures a r e based on a launch azimuth of 72 degrees. a l l g h t l y f o r o t h e r azimuths. Figures w i l l vary �Apollo 10 l i e s i a n Events Event - Qmund Elapsed Time hr8:rIn: 8eC Date 6c lima v Purpose and (Resultant Orbit) Insertion into 100 nm c i r o u l a r EM. Insertion Injection i n t o free-return translunar traJectory with 60 arn pericynthion. CSH separatio?:, docking ?Iard-mating Ejection from SLA Separates CSM-LbI Prom S-IVB/ SLA. SPS evasive maneuver Frovides separation p r i o r t o f-IVE propellant dump and slingshotn mBnBuver. 6 lidcourse 2 correction No. 1 ' ,Midcourse correction No. 2 TJd +9 hrs. % +24 I &a. Ridcourse cormction No. 3 LC1 -22 h r s , Mldcour~ecorrection No. 4 LO1 -5 hre. Of CSM and LSI. * These midcourse corrections have a nomlnal velocity change of 0 fps, but w i l l be c a l culated in r e a l time t o eorr e c t 'PLIT: dispersions. LQCC-3 w i l l have a plane change component t o achieve desired lunar o r b i t Inclination. Lunar Orbit Insertion No. 1 I n s e r t s Apollo 10 i n t o 60x170 nm e l l i p t i c a l lunar o r b i t . huuw Orbit InsertSon No. 2 Circularizes lunar parking o r b i t t o 60 nm. CSlrI-IX undoaklng; separation Establishes equiperiod o r b i t f o r 2 nm separation (mini~ootball). Descent o r b i t insertion (DPB) Lower LH pericynthion t o eight nm (8x60). (SM RCS) , g I �Xvent - Date & The Purpose and (Resultant Orbit1 7Enr) DPS phasing bum Raises JN apocynthlon to 194 nm, allows OSM t o ass a d overt* (8x197. AP8 Insertion gum Siaulates I . ascent I n t o lunar o r b i t a f t e r landing (8~43.6). LH RCS concentria sequenae ini:late (CSI) burit Raises M pericynthion t o 46.2 nm, adjusts o r b i t a l shape f o r rendeevms sequence (42. w46.2) Radially dowmard bum adJusts IA t o constant 15 nm below CSH. 1l1 RCS conatant d e l t a height (om)burn 6 L1I RCS terminal phase 7 (WI) h r n Initiate . I1I thTYLsts along l i a a - O f - s&ht t o w a r d CSM, mldoourse and braking manepvors, a s neoessam. m0-W ~ b s f e back r to E)SM (about 107 om). APS burn ta depletion Poaigrade APS depletion bum near I# perloynthion i g j e c t s X.#l asoent s t q e into heliooentrla orbit. Transearth injection (%I) SP8 bum ~ n j e a t sCSM into Slf-hour transearth t r a j e a t a q . I 5 �Ground Elapsed Tiae hmr:mlm: see Bate h Tirw, (EBT) Midcourse correction Ilo. 5 !fSI +15 hrs. 5/24 5: 09 gas Midoaur~ecorrrrution XQ. 6 m e -~15 ~hrs. 5/25 5: 39 pas Xidcourse oorreotion Ha. 7 &try 5/26 5: 39 w WS?! reparation Entry Interface (400,680 feet) - 3 ~lrs. Parpose and (lle~)ulbntOrbit) -- * Tmwearth mLdoourse earrootloma w i l l be omin real tlma for entry oomidor contwl and for adjusting landing poiat to avoid recover~r area foul weather. Reentry condition. got4 Command module enters BartR(a aenaible ataosphere a t 36,310 fps. an ding: 1,285 na domrsly. iFo1p entry, 15 degree8 seven airmtas South latitude x 165 degrees West longitude. �The crew f o r t h e first t i m e w i l l have a backup t o launch v e h i c l e guidance d u r i n g powered f l i g h t , If t h e S a t u r n i n s t r u ment u n i t i n e r t i a l platform f a i l s , t h e crew can switch guidance t o the command module computer f o r f i r s t - s t a g e powered f l i g h t automatic c o n t r o l . Second and t h i r d stage backup guidance i s through manual takeover i n which command module hand c o n t r o l l e r i n p u t s a r e f e d through t h e command module computer t o t h e Saturn instrument u n i t , Apollo 10 w i l l remain i n E a r t h parking o r b i t f o r one-andone-half r e v o l u t i o n s a f t e r i n s e r t i o n and w i l l hold a l o c a l h o r i z o n t a l a t t i t u d e d u r i n g t h e e n t i r e period. The crew w i l l p e r f o m s p a c e c r a f t s stems checks i n p r e p a r a t i o n f o r t h e t r a n s l u n a r i n j e c t i o n (TLI burn. The f i n a l "go" f o r the TLI burn w i l l be given t o t h e crew through t h e Carnarvon, A u s t r a l i a , Manned Space F l i g h t Network s t a t i o n , 3 Midway through t h e second r e v o l u t i o n i n Earth parking o r b i t , t h e S-IVB t h i r d - s t a g e engine w i l l r e i g n i t e a t two hours 33 minuees 26 seconds Ground Elapsed Time (GET) over f i u s t r a l i a t o i n j e c t Apollo 1 0 toward t h e Moon, The v e l o c i t y w i l l i n c r e a s e f p s ) t o 35,651 f p s a t TLI c u t o f f from 25,593 feet-per-second a v e l o c i t y i n c r e a s e of 1O,O5 f p s , The TLI burn w i l l p l a c e t h e s p a c e c r a f t on a f r e e - r e t u r n circumlunar t r a j e c t o r y f rorn which midcourse c o r r e c t i o n s could be made with t h e SM r e a c t i o n c o n t r o l system t h r u s t e r . Splashdown f o r a f r e e - r e t u r n t r a j e c t o r y would be a t 6:37 porn4 EDT May 24 a t 24.9 degrees South l a t i t u d e by 84,3 degrees E a s t l o n g i t u d e a f t e r a f l i g h t time of 149 hours and 49 minutes, -- Q Transposition, Docking and E j e c t i o n (TM) A t about t h r e e hours a f t e r l i f t o f f and 25 minutes a f t e r t h e TLI burn, t h e Apollo 1 0 crew w i l l s e p a r a t e t h e command/ s e r v i c e module from t h e s p a c e c r a f t l u n a r module a d a p t e r (SLA), thmst o u t away from t h e S-IVB, t u r n around and move back i n f o r docking w i t h t h e l u n a r module. Docking should t a k e place a t about t h r e e hours and t e n minutes GET, and a f t e r t h e crew c o n f i m s a l l docking l a t c h e s s o l i d l y engaged, they w i l l connect t h e CSM-to-W u m b i l i c a l s and p r e s s u r i z e t h e LM with t h e command module surge tank. A t about 4:09 GET, docked s p a c e c r a f t w i l l be e j e c t e d from t h e s p a c e c r a f t LM a d a p t e r by s p r i n g d e v i c e s a t the four landing g e a r " k n e e H a t t a c h p o i n t s , The e j e c t i o n springs w i l l i m p a r t abput one fps v e l o c i t t o t h e s p a c e c r a f t . A 19.7 f p s s e r v i c e propulsion system (SPS e v a s i v e maneuver i n plane a t 4:29 GET w i l l s e p a r a t e t h e s p a c e c r a f t t o a s a f e d i s t a n c e f o r t h e S-IVB " s l i n g s h o t " maneuver i n which r e s i d u a l l i q u i d p r o p e l l a n t s w i l l be dumped through t h e 3-2 engine b e l l t o propel t h e s t a g e i n t o a t r a j e c t o r y passing behind t h e Moon's t r a i l i n g edge and on i n t o s o l a r o r b i t . T �SPACE VEHICLE EARTH PARKING ORBIT CONFIGURATION (SATURN V THIRD STAGE AND INSTRUMENT UNIT, APOLLO SPACECRAFT) �0 10 LUNAR ORB I T INSERTION LUNAR ORB I T 20 80 30 40 50 60 70 90 100 TRANSEARTH 'INJECTION 110 120 130 140 150 LAUNCH 160 170 180 193 200 SPLASHDOWN GROUND ELAPSED TlME (HOURS) SPACECRAFT ALTITUDE VS. T l M E �': 25 VELOCITY3 (MPH x 10 10 36 24 VELOC ITY (FTISEC) (lo3, , 5 0 0 0 40 80 120 160 200 TRANSLUNAR VELOCITY PROFILE 240 �POST TLI TIMELINE T L I + 2 0 SEC -:ORBIT RATE T L I + 2 5 MlN SC INITIAL SEPARATION (1 F P S ) T L I t 2 7 MIN NULL SEPARATION RATE AND PITCH TO DOCKING ATTITUDE LM WITHDRAWAL -20 FPS �T r a n s l u n a r Csast Up t o f o u r midcourse c o r r e c t i o n burns a r e planned d u r i n g t h e t r a n s l u n a r c o a s t phase, depending upon the accuracy of t h e t r a j e c t o r y r e s u l t i n g from the TLI maneuver. If required; the midcourse c o r r e c f i o n burns are planned a t TLI +g hours, TLI +24 hours, l u n a r o r b i t i n s e r t i o n (LOI) -22 hours and LOX -5 hours. During c o a s t p e r i o d s between midcourse c o r r e c t i o n s , t h e s p a c e c r a f t w i l l be i n t h e p a s s i v e thermal c o n t r o l (PTC) o r "barbecue" mode i n which t h e s p a c e c r a f t w i l l r o t a t e s l o w l y about one a x i s t o s t a b i l i z e s p a c e c r a f t thermal r e s p o n s e s p a c s t o t h e continuous s o l a r exposure. Midcourse c o r r e c t i o n s 1 and 2 w l l l n o t normally be made u n l e s s the p r e d i c t e d Mission Control Center 3 v e l o c i t y change i s g r e a t e r t h a n 25 feet-per-second. Lunar O r b i t I n s e r t i o n (WI) The f i r s t of two l u n a r o r b i t i n s e r t i o n burns w i l l be made a t 75:45:43 GET a t a n a l t i t u d e of 89 lllg above t h e Moon, LOI-1 w i l l have a nominal r e t r o g r a d e v e l o c i t y change of 2,974 f p s and w i l l i n s e r t Apollo 10 i n t o a 60x170-nm e l l i p t i c a l l u n a r o r b i t . LOI-2 two o r b i t s l a t e r a t 80:10:45 GET w i l l c3.r- c u l a r i z e t h e o r b i t t o 60 nm. The burn w i l l be 138.5 f p s r e t r o grade. Both LO1 maneuvers w i l l be w i t h t h e SPS engine n e a r p e r i c y n t h i o n when t h e s p a c e c r a f t i s behind t h e Moon and o u t of c o n t a c t w i t h MSPN s t a t i o n s . Lunar Parking O r b i t (LPO) and IN-Active Rendezvous Apollo 1 0 w i l l remain i n l u n a r o r b i t about 61.5 hours, and I n a d d i t i o n t o t h e LEP d e s c e n t t o eight n a u t i c a l m i l e s above t h e l u n a r s u r f a c e and subsequent rendezvous w i t h t h e CSM, e x t e n s i v e l u n a r landnark tracking t a s k s w i l l be performed by t h e crew, Following a r e s t period a f t e r t h e l u n a r o r b i t c i r c u l a r i z a t i o n , t h e LH w i l l be manned by t h e command and l u n a r module p i l o t and p r e p a r a t i o n s begun f o r undocking a t 98:10 GET. Some 25 minutes of s t a t i o n keeping and CSM i n s p e c t i o n of the IM will be followed by a 2.5 f p s r a d i a l l y downward SM RCS maneuver, plati n g t h e I24 and CSM i n e q u i e r i o d o r b i t s w i t h a maximum s e p a r a t i o n A t t h e midpoint of t h e m i n i f o o t b a l l , of two m i l e s ( m i n i f o p t b a l l the descent propulsion system (DPs) w i l l be f i r e d r e t r o g r a d e 71 f p s a t 99:34 GET f o r t h e descent o r b i t i n s e r t i o n (DOI) t o lower LM p e r i c y n t h i o n t o e i g h t miles. The DPS engine w i l l be f i r e d a t 10 p e r c e n t t h r o t t l e s e t t i n g f o r 1 5 seconds and a t 40 p e r c e n t f o r 13 seconds, 7. �LUNAR ORBIT INSERTION 101- 1 LO1 - 2 I EARTH EARTH �LUNAR ORBIT ACTIVITIES LM A C T I V E RENDEZVOUS LM C ; O AND LANDMARK S RN 31 I SEP PHAS STRl P PHOTO 1 AND 2 T g . 0. 33 I h) 0 d 4 LANDMARK TRACKING I I TEI STRIP PHOTO 3 �24.5 DEG PlTCH DOWN FROM LOCAL HORIZONTAL OVER LANDMARK 2 DEG PITCH DOWN FROM LOCAL HORIZONTAL BEGIN 0.3 DEGPEC PITCH DOWN AT A05 'a PITCH DOWN 47 DEG FROM AT, = 296 SEC - a T 2 40 SEC AT3 = 25 SEC A Tq = 25 SEC AOS TO LOS = 3 MIN TOTAL I C S M / L M TYPICAL L A N D M A R K T R A C K I N G PROFILE �APOLLO 10 RENDEZVOUS SEQUENCE �COMPARISON OF F A N D G LM OPERATIONS PHASE RENDEZVOUS MANEUVERS UNDOCKING ilNG I I \ SEPARATION F UNDOCKING G RENDEZVOUS DOCKING INSER LM LIFTOFF RENDEZVOUS MANEUVERS k 8 �@lLM (DO1 DESCENT ORB IT INSERTION MANEUVER I MSFN AOS MSFN LOS SURFACE DARKNESS SC DARKNESS Ib 0 '? T + k/ -, \ (DO11 ' ~ ~ ~ ~ FAND + ~BEHIND '. :TSEPARATION ~ I R E C T I Ok+ N OF MOTION I\ I MOTION OF ~ o ~ "PL1.8 N. MI. / t EARTH LM RELATIVE TO CSM MOON CSM/LM SEPARATION MANEUVER �LUNAR MODULE DESCENT ORBIT INSERTION @ LM DESCENT ORB I T INSERTION (DO1 MANUEVER, RETROGRADE, DP,~S TO d C1 0 I 200 N. MI. I -a LM BELOW A N D AHEAD 1 - 1- LM BELOW -a (PHASING) LANDING SITE 54 000 FT. \ ABOVE LANDING SITE RAD IUS MOON �ORBIT RATE (0.05 DEG/sEC PITCH DOWN) FROM -400 to 200 FROM PERlCYTHlON O€iSERW CANDING SITE (PHOTOGRAPIO CHECKOUT LANDING O8SERVE LUNAR YAW RIGHT180 DEG AND plrcn up NEAR LUNAR SURFACE ACTIVITY MANEUVER 10 RIASlNG BURNATTITUDE �A s t h e W passes over Apollo landing S i t e 2, t h e IN landing radar w i l l be t e s t e d i n t h e a l t i t u d e mode but not i n descent r a t e , About 10 minutes a f t e r t h e pass over S i t e 2, t h e 195 f p s DPS phasing burn a t 100:46 GET w i l l boost t h e IM i n t o an 8x194-nm o r b i t t o allow the CSM t o overtake and pass t h e M , The phasing burn i s posigrade and t h e DPS engine is f i r e d a t 10 per cent t h r o t t l e f o r 26 seconds and f u l l t h r o t t l e f o r 17 seconds, The phasing burn places t h e LM i n a l'dwellll o r b i t which allows t h e CSN t o overtake and pass t h e LPI s o that a t t h e second LM passes over S i t e 2, t h e I24 w i l l t r a i l t h e CSM by 27 nm and w i l l be i n a proper p o s i t i o n f o r t h e i n s e r t i o n maneuver simulating ascent from t h e l u n a r surface a f t e r a landing mission, P r i o r t o t h e 207-fps M ascent engine retrograde i n s e r t i o n burn, the Ilvl descent s t a g e w i l l be j e t t i s o n e d and an evasive maneuver perfo~medby t h e ascent stage t o prevent recontact. The i n s e r t i o n burn w i l l be made a t 102:43 CIET and w i l l lower LM apocynthion t o 44.9 nra s o t h a t t h e LM i s 14.7 nin below and 148 rn behind t h e CSM a t t h e time of t h e concentric sequence i n i t i a t e (CSI) burn. Following IM radar tracking of t h e CSM and onboard computation of t h e CSI maneuver, a 50.5 f p s IM RCS posigrade burn w i l l be made a t a nominal time of 103:33 GET a t apocynthion and all l ~ g s u l ti n a 44.9~44.3-nm fM o r b i t , The IEI RCS w i l l draw from t h e LM ascent propulsion system (BPS) propellant tanks through t h e interconnect valves. A 3.4 f p s r a d i a l l y downward U l RCS constant d e l t a height (cDH) maneuver a t 104:31 GET w i l l place t h e W on a c o e l l i p t i c o r b i t 15 nm below that of t h e CSM and w i l l set up conditions f o r t h e terminal phase i n i t i a t e (TPI) burn 38 minutes l a t e r , The T P I maneuver w i l l be made when t h e CSM i s a t a 26,6degree e l e v a t i o n angle above t h e M a s l o c a l h o r i z o n t a l following continuing r a d a r tracking of t h e CSM and onboard computations for t h e maneuver. Nominally, t h e T P I burn w i l l be a 24.6-fps LM RCS burn along t h e l i n e of s i g h t toward t h e CSM a t 105:09 GET. Midcourse c o r r e c t i o n and braking maneuvers w i l l place the XM and CSM i n a rendezvous and station-keeping p o s i t i o n , and docking should take place a t 106:20 GET t o complete a eight-and-a-half hour sequence of undocked a c t i v i t i e s . After t h e commander and lunar. module p i l o t have t r a n s f e r r e d i n t o t h e CSM, the IM.w i l l be j e t t i s o n e d and t h e CSM w i l l maneuver 2 fps r a d i a l l y upward t o move above and behind the IN a t the t i m e of the W a s c e n t propulsion system burn t o propellant d e p l e t i o n a t 108:39 GET. �LUNAR MODULE PHASING MANEUVER I N. MI. I MOON U\A PHAS ING MANEUVER DPS- FULL THROTTLE LANDING S ITE �LUNAR MODULE INSERTION MANEUVER MSFN I 147 270 N.MI. N. MI. I n I \ 15 N. MI.--/ I (CSI) I MSFN AOS I I (RETROGRADE, APS) \ \ .-4 I --I 51 . I MOON N. ;O *L MI. / @ LM INSERTION MANEUVER INSERTION �LUNAR MODULE CONCENTRIC SEQUENCE INITIATION MANEUVER @cs I MANEUVER ,/-0>. .. / \ 4 ; . - 4 15 - N. MI. '\ MSFN LOS / I / 1 I 147 N. MI. \ (CSI) \\ '15 N.MI~,&, ( T P(CDH) I) AOSt MOON I / ,/ �LUNAR MODULE CONSTANT DIFFERENTIAL HEIGHT AND TERMINAL PHASE MANEUVERS RENDEZVOUS AND @ T P I MANEUVER (MIDPOINT OF DARKNESS) LM RCS 8 cj (0 I BRAKING I -45 75 N. MI. 30 N. M I . 1 I I MINI \ 1\\, 15 N MI \26.b0 TPI LOOK ANGLE TO CSM 36 MIN CDH I-@ CDH MANEUVER �The burn w i l l be ground-coamanded, An estiwated 3,837-Pps posigrade v e l o c i t y w i l l be imparted by t h e APS d e p l e t i o n burn near Uf pericynthion t o place t h e IN a s c e n t s t a g e i n a h e l l o centric orbit, h a d d i t i o n a l 29 hours w i l l be spent i n l u n a r o r b i t before t r a n s e a r t h i n j e c t i o n while t h e crew conducts l u n a r landmark t r a c k i n g t a s k s and makes photographs of Apollo landing sites. TransearBh I n j e c t i o n (TEI) The 54-hour r e t u r n t r i p t o Earth begins a t 137:20 GET when the SPS engine i s f i r e d 3622.5 fps posigrade f o r the TEI burn, L i k e LOI-1 and LOI-2, t h e T E I burn w i l l be made when t h e s p a c e c r a f t i s behind the Moon and out of touch w i t h MSFN s t a t i o n s . Transearth Coast Three c o r r i d o r - c o n t r o l t r a n s e a r t h midcourse c o r r e c t i o n b u m s w i l l be made i f needed: MCC-5 a t TEI +35 hours, MCC-6 a t entry interface (EI=400,000 f e e t ) -15 hours and a t E I -3 hours, Entry, Laodine Apollo 10 w i l l encounter t h e E a r t h ' s atmosphere (400,000 f e e t ) a t 191:50 GET a t a v e l o c i t y of 36,310 f p s and w i l l land some 1,285 nm downrange from t h e e n t r y - i n t e r f a c e p o i n t using the s p a c e c r a f t ' s l i f t i n g c h a r a c t e r i s t i c s t o reach t h e landing p o i n t . Touchdown w i l l be a t l92:O5 GET a t 15 degrees 7 minutes South l a t i t u d e by 165 degrees West longitude. �EARTH ENTRY ENTRY RANGE CAPABILITY * NOMINAL ENTRY RANGE - 1200 TO 2500 N. MI. - 1 2 8 5 N. MI. SHORT RANGE SELECTED FOR NOMINAL MISSION BECAUSE: e RANGE FROM ENTRY TO lANDlNG CAN B E SAME FOR PRIMARY AND BACKUP CONTROL MOPES PRIMARY MODE EASIER TO MONITOR WITH SHORT RANGE WEATHER AVOIDANCE, WITHIN ONE DAY PRIOR TO ENTRY, I S ACHIEVED USING ENTRY RANGING CAPABILITY TO 2500 N. MI. UP TO ONE DAY PRIOR TO ENTRY USE PROPULSION SYSTEM TO CHANGE LANDING POINT r: E' t �VELOCITY AT ENTRY INTERFACE 36.5 x l o 3 LAUNCH W INDOW CLOSED VELOC l TY 4 2I LAUNCH WI NDOW OPEN (FPS 18 20 24 L A U N C H D A T E (MAY) 23 25 �GEODETIC ALTITUDE VERSUS RANGE TO GO 400 NOTE: T I M E T I C K E D E V E R Y 1/2 MLN FROM E N T R Y INTERFACE ENTER S-BAND BLACKOUT 320 240 A3 8 88 h) 0 8 ALTITUDE (1000 FT) 160 E*XIT S-BAND BLACKOUT DROGUE PARACHUTE DEPLOYMENT 80 MAIN PARACHUTE DEPLOYMEN TOUCHDOWN. 0 1400 1200 1000 800 600 400 200 R A N G E TO SPLASHDOWN, (Nautical Miles) 0 �DROGUE CHUTES PILOT CHUTES CHUTE SPLASH DOWN VELOCITIES: 3 CHUTES 2 CHUTES - 31 FT/SEC - 36 FT/ SEC - _ - - -- AFTER TOUCHDOWM -- -- - - -- - - - E A R T H RE-ENTRY AND LANDING �ACTIVITY D A Y 1 REST PERIODS DATE/DAY' ED7 LUNAR REVOLUTION N O . 1 GET 0 1 8 12 12 6 16 20 24 28 6 24 32 36 40 12 44 - I Q 18 52 56 60 I MAY 21 -WEDNESDAY 24 6 64 12:so 68 1 4 LO1 D A Y I MAY 20 -TUESDAY I8 I 3 2 MAY I 9 MONDAY 24 IS 4 - - - MAY SUNDAY I8 12 48 APOLLO 10 SUMMARY FLIGHT PLAN n 18-50 74 I 2 76 78 6 - THURSDAY I I 1MO 18 6 3 4 5 6 7 8 9 10 11 12 13 14 IS 16 17 18 80 82 84 86 88 w 92 94 96 $0 IW 102 IM 106 la, 110 19 112 20 I14 12254 21 116 :8 i 22 23 24 118 ~ z o 122 a? 26 I 4 1% M A Y 24 24 v 28 128 130 29 132 I 7 TEl D A Y I MAY 23 -FRIDAY 24 - - I I MAY 22 24 - :6 5 DO1 DAY - M 134 31 136 I SATURDAY 1250 b 1 8 I8 MAY 25 24 6 - SUNDAY 12 I 9 18 10 MAY 26 -MONDAY 24 6 12.52 32 138 YO I42 144 148 152 156 160 164 168 172 176 180 I84 I@ 192 LM MANEUVER DATA 81. 15.6 SEC AV: 24.6 FPS NO ULLAGE LM (SNOOPY) (CHARLIE BROWN) C S M MANEUVER D A T A 1-5 �RECOVERY OPERATIONS The primary recovery l i n e f o r Apollo 10 i s i n t h e mtdP a c i f i c a l o n g t h e 175th West meridian of longitude above 15 degrees North l a t i t u d e , and jogging t o 165 degrees West l o n g i t u d e below t h e Equator. The h e l i c o p t e r c a r r i e r USS P r i n c e t o n , Apollo 10 prime recovery v e s s e l , w3 11 be s t a t i o n e d n e a r t h e end-of-mission aiming p o i n t . Splashdown f o r a f u l l - d u r a t i o n l u n a r o r b i t mission launched on time May 18 w i l l be a t 5 d e g r e e s 8 minutes South by 165 degrees West a t a ground e l a p s e d time o f 192 hours 5 minutes. The l a t i t u d e o f splashdown depends upon t h e time of t h e t r a n s e a r t h i n j e c t i o n burn and t h e d e c l i n a t i o n o f t h e Moon a t t h e t i m e o f t h e burn. A s p a c e c r a f t r e t u r n i n g from a l u n a r f l i g h t w i l l e n t e r E a r t h ' s atmosphere and s p l a s h down a t a p o i n t on E a r t h d i r e c t l y o p p o s i t e t h e Moon. T h i s p o i n t , c a l l e d t h e a n t i p o d e , i s a p r o j e c t i o n of a l i n e from t h e c e n t e r o f t h e Moon through t h e c e n t e r o f t h e Earth t o t h e s u r f a c e o p p o s i t e t h e Moon. The mid-Pacific recovery l i n e r o t a t e s through t h e a n t i p o d e once each 24 hours, and t h e t r a n s E a r t h i n j e c t i o n burn w i l l be t a r g e t e d f o r splashdown along t h e p r i m s y recovery l i n e . Other planned recovery l i n e s f o r a deep-space mission a r e t h e E a s t P a c i f i c l i n e extending roughly p a r a l l e l t o t h e c o a s t l i n e s o f North and South America; t h e A t l a n t i c Ocean l i n e running a l o n g t h e 3 0 t h West meridian i n t h e n o r t h e r n hemisphere and a l o n g t h e 2 5 t h West meridian I n t h e s o u t h e r n hemisphere; t h e I n d i a n Ocean l i n e a l o n g t h e 6 5 t h E a s t meridian; and t h e West P a c i f i c l i n e along t h e 150th East meridian i n t h e n o r t h e r n hemisphere and jogglng t o t h e 170th E a s t meridian i n t h e s o u t h e r n hemisphere. Secondary landing areas f o r a p o s s i b l e Earth o r b i t a l a l t e r n a t e mission have been e s t a b l i s h e d i n two zones--one i n t h e P a c i f i c and one i n t h e A t l a n t i c . Launch a b o r t landing areas extend downrange 3,400 n a u t i c a l m i l e s from Kennedy Space C e n t e r , fanwise 50 n a u t i c a l m i l e s above and below t h e l i m i t s o f t h e v a s i a b l e launch azimuth ( 7 2 degrees 107 d e g r e e s ) . Ships on s t a t i o n i n t h e launch a b o r t a r e a w i l l be t h e d e s t r o y e r USS Rich, t h e i n s e r t i o n t r a c k i n g s h i p USNS Vanguard and t h e a t t a c k t r a n s p o r t USS C h i l t o n . I n a d d i t i o n t o t h e primary recovery v e s s e l steaming up and down t h e mid-Pacific recovery l i n e and s u r f a c e v e s s e l s on t h e A t l a n t i c Ocean recovery l i n e and i n t h e launch a b o r t a r e a , 14 HC-130 a i r c r a f t w i l l be on standby a t seven s t a g i n g bases around t h e Earth: Guam, Pago Pago, American Samoa; H a w a i i , Bermuda; L a j e s , Azores; Ascension I s l a n d ; M a u r i t i u s and t h e Panama Canal Zone. �Apollo 10 recovery operations w i l l be d i r e c t e d from t h e Recovery Operations Control Room i n t h e Mission Control Center and w i l l be supported by t h e A t l a n t i c Recovery Control Center, Worfolk, Va., and t h e P a c i f i c Recovery Control Center, Kunla, H a w a i i . The Apollo 10 crew w i l l be flown from t h e primary r e covery v e s s e l t o t h e Manned Spacecraft Center a f t e r recovery. The s p a c e c r a f t w i l l r e c e i v e a preliminary examination, s a f i n g and power-down aboard t h e Princeton p r i o r t o offloading a t Ford I s l a n d , H a w a i i , where t h e s p a c e c r a f t w i l l undergo a more complete d e a c t i v a t i o n . It i s a n t i c i p a t e d t h a t t h e s p a c e c r a f t w i l l be flown from Ford I s l a n d t o Long Beach, C a l i f . , within 72 hours, and then trucked t o the North American Rockwell Space Division p l a n t i n Downey, Calif., f o r p o s t f l i g h t a n a l y s i s . �APOLLO 10 ALTmNATE MISSIONS Five a l t e r n a t e mission p l a n s have been prepared f o r t h e Apollo 10, each depending upon when i n t h e mission time l i n e it becomes necessary t o switch t o the a l t e r n a t e , Testing of t h e lunar module and a m - a c t i v e rendezvous i n E a r t h o r b i t a r e p r e f e r r e d over a CSM-only flyby mission. When it is impossible t o r e t u r n t o a low Earth o r b i t with rendezvous, a h i g h - e l l i p s e LM t e s t i s p r e f e r r e d over a low Earth o r b i t test. Where p o s s i b l e , Apollo 10 a l t e . r n a t e missions follow the l w r o r b i t mission time l i n e and have a d u r a t i o n of about 10 days. Apollo 10 a l t e r n a t e missions a r e summarized as follows: A l t e r n a t e 1: Early shutdown of S-IVB during TLI with r e s u l t i n g apogee l e s s than 25,000 n a u t i c a l miles, o r f a i l u r e of S-IVB t o i n s e r t s p a c e c r a f t i n t o Earth parking o r b i t and subsequent SPS contingency o r b i t i n s e r t i o n (COI), and in both cases no LM e x t r a c t i o n possible. A l t e r n a t e maneuvers would inc lude : ' * SPS phasing burn t o o b t a i n ground coverage of simulated * * Simulated L O 1 burn t o a 100x400 nm Earth o r b i t . lunar o r b i t i n s e r t i o n . Midcourse c o r r e c t i o n s t o modify o r b i t t o 90x240 nm end-of-mission e l l i p s e and t o complete SPS lunar mission duty cycle during remainder of ten-day mission. A l t e r n a t e 2: S-IW3 f a i l s during TLI burn and r e s u l t i n g apogee i s between 25,000 and 40,000 n a u t i c a l m i l e s ; no LM e x t r a c t i o n . Maneuver sequence would be: * SPS phasing burn t o o b t a i n ground coverage of simulated lunar o r b i t insertion. * * Simulated LO1 burn t o a semi-synchronous Earth o r b i t . SPS phasing maneuver t o place a l a t e r perigee over o r opposite d e s i r e d recovery zone. * SPS maneuver t o place CSM i n semi-synchronous o r b i t with a 12-hour period. * Deorbit d i r e c t l y from semi-synchronous o r b i t into Pacific recovery a r e a (ten-day mission). �Alternate No burn o r d u l l y extracted, : but TLI T L I apogee less than 4,000 mi success * * * * Simulated LO1 burn to lOOxk.lO-nm o r b i t , + IN-active rendezvous, Simulated descent o r b i t inserstion (DOI) maneuver with IN, Simulated powered descent i n i t i a t i o n (PDI) maneuver. Two SPS burns to c i r c u l a r i z e CSM orbit; t o 3-50 run. * Ground-commanded LM a s c e n t p r o p u l s i o n system (APs) b u r n t o d e p l e t i o n under abort guidance system (AGS) control, similar t o APS d e p l e t i o n burn i n Apo1l.o 9. * Additional SPS burns t o place CSM in 90x2@-nm end-ofmission e l l i p s e and t o complete SPS l u n a r mission duty cycle during remainder of ten-day mission, �A l t e r n a t e 4: E a r l y S-IVB TLI c u t o f f w i t h r e s u l t i n g apogee g r e a t e r than 4,000 nrn b u t l e s s than 10,000 nm, and c a p a b i l i t y of SPS and LM d e s c e n t propulsion system t o g e t h e r t o r e t u r n CSM-LW t o low E a r t h o r b i t without compromising CSM1s a b i l i t y t o r e s c u e LM. * SPS phasing burn t o obtain ground coverage of simulated lunar o r b i t insertion. * F i r s t docked DPS burn out-of-plane s i m u l a t e s d e s c e n t orbit insertion. * * * Second docked DPS burn s i m u l a t e s power d e s c e n t i n i t i a t i o n . * SPS burns tc c i r c u l a r i z e CSM o r b i t a t 150 + LM-active rendezvous. SPS simulated L O 1 burn. Phaslng maneuver t o o b t a i n ground coverage o f simulated powered d e s c e n t i n i t i a t i o n . ma. * Ground-commanded a s c e n t propulsion system burn t o d e p l e t i o n under a b o r t guidance system (AGS) c o n t r o l , s i m i l a r t o APS d e p l e t i o n burn i n Apollo 9 , * A d d i t i o n a l S P S burns t o p l a c e CSM i n 90x240 nm end-ofmission e l l i p s e and t o complete SPS l u n a r mission d u t y c y c l e d u r i n g remainder o f ten-day mission. A l t e r n a t e 5: SPS and DPS j o i n t l y cannot p l a c e CSM-LM i n low Earth o r b i t without compromising a b i l i t y o f CSM t o rescue LPI i n a rendezvous sequence, and SPS f u e l q u a n t i t y is too low f o r a CSM-LM circumlunar mission. * SPS phasing burn t o o b t a i n ground coverage of simulated lunar o r b i t insertion. * orbit. Simulated l u n a r o r b i t i n s e r t i o n i n t o semisynchronous * SPS p h a s i n g burn t o o b t a i n ground coverage o f simulated power d e s c e n t i n i t i a t i o n . * First docked DPS burn o u t o f plane s i m u l a t e s d e s c e n t o r b i t insertion. * Second docked DPS burn s i m u l a t e s power d e s c e n t i n i t i a t i o n and is d i r e c t e d o u t of plane. �* SPS phasing burn t o place a l a t e r perigee over or opposite desired recovery zone. * SPS maneuver to place CSM-LM insemi-synchronous orbit with a 12-hour period, * around-commanded LM ascent propulsion system burn t o depletion under abort guidance system control; poslgrade a t apogee. * Additional midcourse corrections along a lunar mission time line and d i r e c t entry from high ellipse, �ABORT MODES The Apollo 10 rni&lon can b e a b o r t e d at any time during t h e launch phase o r terminated during l a t e r phases a f t e r a successful insertion i n t o Earth o r b i t . Abort modes can b e summarized as follows: Launch phase - -- Mode I h u n c h escape (LEs) tower p r o p e l s command module away from launch v e h i c l e . This mode i s i n e f f e c t from about T-45 minutes when LES i s armed u n t i l L E S ' j e t t i s o n a$ 3:07 GET and command module l a n d i n g p o i n t C ~ J I range from the Launch Complex 39B area t o 520 nm (600 sm, 964 km) downrange, Mode 11 - Begins when LES i s jetti'soned and r u n s u n t i l the SPS can be used t o i n s e r t t h e CSM i n t o a s a f e E a r t h o r b i t ( 9 : 2 2 GET) o r u n t i l l a n d i n g p o i n t s t h r e a t e n t h e A f r i c a n c o a s t , Mode I1 r e q u i r e s manual s e p a r a t i o n , e n t r y o r i e n t a t i o n and f u l l l i f t e n t r y w i t h landing between 400 and 3,200 nm (461-3,560 s m , 741-5,931 km) downrange. - Begins when f u l l - l i f t landing p o i n t reaches 3,200 Mode 111 nm (3,560 sm, 5,931 km) and extends through E a r t h o r b i t a l i n s e r t i o n , The CSM would s e p a r a t e fram t h e launch v e h i c l e , and I f necessary, an SPS r e t r o g r a d e burn would b e made, and t h e command module wol~ld be flown h a l f - l i f t t o e n t r y and landing a t approximately 3,350 nm (3,852 sm, 6,197 km) downrange. - Mode I V and Apogee Kick Begins a f t e r t h e p o i n t t h e SPS could b e used t o i n s e r t t h e CSM i n t o a n Earth p a r k i n g o r b i t from about 9:22 GE2. The SPS burn i n t o o r b i t would b e made two minutes a f t e r -- s e p a r a t i o n from t h e S-IVB and t h e mission would continue as an Earth o r b i t a l t e r n a t e . Mode I V i s p r e f e r r e d over Mode 111. A v a r i a t i o n of Mode I V i s t h e apogee k i c k i n which t h e SPS would be ignited a t f i r s t apogee t o r a i s e p e r i g e e f o r a safe o r b i t . Beep Space Aborts Translunar I n j e c t i o n Phase -- Aborts during t h e t r a n s l u n a r i n j e c t i o n phase are only a remote p o s s i b i l i t y , but if an a b o r t became necessary d u r i n g t h e TLI maneuver, a n SPS r e t r o g r a d e burn could be made t o produce s p a c e c r a f e e n t r y , T h i s mode of a b o r t would be used o n l y i n t h e event of a n extreme emergency t h a t a f f e c t e d crew s a f e t y , The s p a c e c r a f t landing p o i n t would vary with launch azimuth and l e n g t h of t h e TLI burn, Another TLI a b o r t s i t u a t i o n would be used if a malfunction cropped up a f t e r i n j e c t i o n . A r e t r o g r a d e SPS burn a t about 90 minutes a f t e r TLI s h u t o f f would allow t a r g e t i n g t o land on t h e A t l a n t i c Ocean recovery l i n e , �Translunar Coast phase -- Aborts a r i s i n g during t h e three-day t r a n s l u n a r c o a s t phase would be similar i n n a t u r e t o t h e 90-minute TLI a b o r t . Aborts from deep space b r i n g i n t o t h e p l a y t h e Moon's a n t i p o d e ( l i n e p r o j e c t e d from Moon's c e n t e r through E a r t h ' s c e n t e r t o o p p o s i t e f a c e ) and t h e e f f e c t of t h e E a r t h ' s r o t a t i o n upon t h e geographlcal l o c a t i o n of t h e antipode. Abort times would be s e l e c t e d f o r landi n g when t h e a n t i p o d e c r o s s e s 1650 West l o n g i t u d e , The a n t i p o d e c r o s s e s t h e mid-pacific recovery l i n e once each 24 hours, and i f a t i m e - c r i t i c a l s i t u a t i o n f o r c e s an a b o r t e a r l i e r t h a n t h e s e l e c t e d f i x e d a b o r t times, l a n d i n g s would be t a r g e t e d f o r t h e A t l a n t i c Ocean, E a s t P a c i f i c , West P a c i f i c o r I n d i a n Ocean recovery l i n e s i n t h a t o r d e r of preference. When t h e s p a c e c r a f t e n t e r s t h e Moon's sphere of i n f l u e n c e , a circumlunar a b o r t becomes faster t h a n an a t t e m p t t o r e t u r n d i r e c t l y t o Earth. Lunar Orbit I n s e r t i o n phase -- E a r l y SPS shutdowns during t h e l u n a r o r b i t i n s e r t i o n burn (MI) a r e covered by t h r e e modes i n t h e Apollo 10 mission. A 1 1 t h r e e modes would r e s u l t i n t h e CM l a n d i n g a t t h e E a r t h l a t i t u d e of t h e Moon a n t i p o d e a t t h e time t h e a b o r t was performedt Mode I would be a I24 DPS posigrade burn i n t o an Earth-return t r a j e c t o r y about two hours ( a t next p e r i c y n t h i o n ) after an LO1 shutdown during t h e f i r s t two minutes of t h e LO1 burn. %ode IT, f o r SPS shutdown between two and t h r e e minutes a f t e r i g n i t i o n , would use t h e LM DPS engine t o a d j u s t t h e o r b i t t o a s a f e , non-lunar impact t r a j e c t o r y followed by a second DPS posigrade burn a t next p e r i c y n t h i o n t a r g e t e d f o r t h e mid-Pacific recovery line. Mode 111, from t h r e e minutes a f t e r LO1 i g n i t i o n u n t i l normal c u t o f f , would a l l o w t h e s p a c e c r a f t t o c o a s t through one o r two l u n a r o r b i t s b e f o r e doing a DPS posigrade burn a t p e r i c y n t h i o n t a r g e t e d f o r t h e mid-pacific recovery l i n e . Lunar O r b i t Phase -- If d u r i n g l u n a r p a r k i n g o r b i t i t became necessary t o a b o r t , the t r a n s e a r t h i n j e c t i o n (TEI) burn would be made early and would t a r g e t s p a c e c r a f t landing t o t h e mid-Pacific recovery l i n e . T r a n s e a r t h I n j e c t i o n phase -- m r l y shutdown of t h e T E I burn between i g n i t i o n and two m i n u t e s would cause a Mode I11 a b o r t and a SPS posigrade TEI burn would be made a t a l a t e r p e r i c y n t h i o n . Cutoffs a f t e r two minutes TEI burn t i m e would c a l l f o r a Mode I a b o r t - - - r e s t a r t of SPS as soon as p o s s i b l e f o r E a r t h - r e t u r n t r a j e c t o r y , Both modes produce mid-Pacific recovery l i n e l a n d i n g s n e a r t h e l a t i t u d e of t h e a n t i pode a t t h e time of t h e TEI burn. �Transearth Coast phase -- Adjustments of the landing point are possible during the transearth coast through burns with the SPS or the service module RCS thrusters, but in general, these are covered in the discussion of transearth midcourse corrections. No abort burns will be made later than 24 hours prior to e n t r y to avoid effects upon GM entry velocity and flight path angle. �A P O U o 10 GO/NO-GO DECISION POINTS Like Apollo 8, Apollo 10 will be flown on a step-by-step commit point or go/no-go basis in which the decisions will be made prior to each major maneuver whether to continue che misston or to switch 'to one of the possible alternate missions. The go/no-go decisions will be made by the flight control teams in Mission Control Center. ~o/no-go decisions will be made prior to the following events: * * * * * * * * + Launch phase go/no-go at 10 min. GEP for orbit insertion Translunar injection Transposition, docking and LM extraction Each translunar midcourse correction burn Lunar orbit insertion burns Nos. 1 and 2 Crew intravehicular transfer to M CSM-LM undocking and separation Hendezvous sequence I&! Ascent Propulsion system burn to depletion * Transearth injection burn (no-go would delay TEI one or more revolutions to allow maneuver preparations to be completed. ) * Each transearth midcourse correction burn �ONBOAHD TELEVISION On Apol i~ ill, onboard v i d e o will o r i g i n a t e f r o m t h e CM; Plans c a l l f o r both b l a c k tliere w i l l b e no 'CV camera i n t h e LM. arid white arld c o l o r ; V t o b e carried. Tkze b l a c k and white camera i s a 4.5 pound RCA camera equipped w i t h a 60-degree field of v i e w wide angle and lOOmm nine-degree i ' i e l d of' v i e w t,elephoto lens, attached to a 12-foot power/video cable. It produces a black-and-white 227 TV l i n e s i g n a l scanned a t 13 frames a second. Madrid, Goldstone and Honeysuckle C r e e k all w i l l Lave equipment t o make s t i l l photographs o f t h e slow s c a n s i g n a l and t o convert t h e s i g n a l t o commercial TV format. The color TV camera i s a 12-pound Westinghouse camera w i t h a zoom lens f o r close-up o r wide a n g l e use and a three-inch monitor which can be mounted on t h e camera o r i n t h e CM. It produces a s t a n d a r d 525-line, 30-frame-per-second s i g n a l i n c o l o r by u s e of a r o t a t i n g color, wheel. The s i g n a l can be viewed i n b l a c k and white. Only MSC, r e c e i v i n g t h e s i g n a l through Goldstone, w i l l have equipment to colorLze t h e s i g n a l . T e n t a t i v e plannlng i s t o use the c o l o r camera predominately, reverting t o t h e lack and white camera if t h e r e i s difficulty with t h e c o l o r system b u t r e q u i r i n g a t l e a s t one b l a c k and white t r a n s mission t o Honeysuckle Creek. The f o l l o w i n g i s a p r e l i m i n a r y p l a n f o r TV p a s s e s based on a 12:49 May 18 launch: GET - DATE/EDT EVENT T r a n s p)Io s i t i o n & dock Madrid Goldstone Transl u n a r c o a s t Goldstone Goldst one Translunar coast Pre-LOI-1 Qoldstone/Madrld Post LOI-2 Goldstone Post undock; formation Goldstone APS Burn t o Depletion Goldstone Landmark Tracking Goldstone Post -TEI Honeysuckle* Transearth coast Goldstone Transearth coast Goldstone *Transmission from RCA b l a c k and white camera. t o be from c o l o r camera. A l l o t h e r s planned �APOLW) 10 PHOTOGRAPHIC TASKS S t i l l a n d motion p i c t u r e s w i l l be made of most s p a c e c r a f t maneuvers as well as of t h e lunar s u r f a c e and of crew a c t i v i t i e s i n t h e ApolLrs 10 cabin. The t r a n s p o s i t i o n , docking and lunar module e j e c t ion maneuver will b e t h e f i r s t major event t o b e photographed. In lunar orbit, t h e IN-active rendezvous sequence w i l l be photographed from both the command and t h e l u n a r module. During t h e period between t h e LN DPS phasing burn and t h e APS i n s e r t i o n burn, t h e commander and lunar module p i l o t w i l l make still photos of t h e l u n a r ground t r a c k and of landing S i t e 2 from t h e eight-mile low p o i n t of t h e M 1 s f l i g h t path. After rendezvous i s complete and t h e LM APS d e p l e t i o n burn h a s been photographed, the crew w i l l make s t e r e o s t r i p s t i l l phot,ographs of t n e l u n a r s u r f a c e and i n d i v i d u a l frames of t a r g e t s of opportunity. Using t h e navigation sextant" o p t i c s a s a camera lens system, lunar s u r f a c e features and landmarks will be recorded on motion p i c t u r e f i l m . Additionally, t h e camerathrougi-1-sextarli. system will photograph star-horizon and star-landmark c m b i n a ; i o n s a s they a r e superimposed i n v i s u a l navigation signtirgs. The A p o i i u iO przotography plan c a l l s f o r motion p i c t u r e s o f crew a c t i v i t i e s srlch as i n t r a v e h i c u l a r t r a n s f e r through t h e CSN-LV docking t u n n e l and of o t h e r crew a c t i v i t i e s such as prcssdre s u i S donning. Long-dfstance E a r t r i and lunar t e r r a i n photographs w i l l be s h o S w i t h tne ? O w . still cameras. Camera eq:liprnent carried on Apollo 10 c o n s i s t s of two 7Omm Hasselbiad s t i l l cameras, each fitted with 80mm f/2.8 t o f/22 Zeiss P l a n a r lenses, a 250m t e l e p h o t o l e n s stowed aboard t h e connand xodule, and a s s o c i a t e d e q ~ i p m e n tsuch as f i l t e r s , r i n g s i g h t , spotmeter and a n i n t e r v a l m e t e r f o r s t e r e o s t r i p hot0 raphy. One iIaseeltlad w i l l b e stowed i n t h e IN and returned t o he C M a f t e r rendezvo~ls. Easselblad s h u t t e r speeds range from one second t o 1/503 s e c , e s For cotion p l c t u r e s , two Maurer data a c q u i s i t i o n cameras (one i n the CSM, one i n t n e 3.24) with v a r i a b l e frame speed selection .dl1 be ~ s e d . . Motion p i c t u r e camera a c c e s s o r i e s Incflde bayonet-mount l e n s e s of 75, 18, and 5m focal length, a r i s h t - a n g l e mirror, a c m a n d module boresignt bracket, a power c a j l e , and an a d a p t e r f o shooting ~ through t h e s e x t a n t . Apollo 10 f i b . stowage i n c l u d e s s i x '7Omrn Hasselblad magazines---two e x t e r i o r c o l o r r e v e r s a l and f o u r f i n e - g r a i n black and white; and 12 140-foot 16mm maoazbes of motion p i c t u r e film---eight e x t e r i o r c o l o r and Pour interior color--f o r a t o l a 1 1630 feet. �LUNAR DESCRIPTION T e r r a i n - Mountainous a n d c r a t e r - p i t t e d , t h e former r i s i n g thousands of feet and t h e l a t t e r ranging from a few i n c h e s t o 180 m i l e s i n diameter. The c r a t e r s a r e thought to be formed by t h e impact of m e t e o r i t e s . The s u r f a c e i s covered with a l a y e r of fine-grained m a t e r l a l resembling s i l t o r sand, a s w e l l a s small rocks and boulders. Environment - No air, no wind, and no moisture. The temperature ranges from 243 degrees i n t h e two-week lunar day t o 279 degrees below zero i n t h e two-week l u n a r a i g h t . Gravity i s one-sixth t h a t of Earth. Micrometeoroids p e l t t h e Moon ( t h e r e i s no atmosphere t o burn them up). Radiation might p r e s e n t a problem during per3 ods of unusual s o l a r a c t i v i t y . - Dark Side The dark o r hidden s i d e of the Moon no longer i s a complete mystery. It was f i r s t photogre~phed by a Russian c r a f t and s i n c e then has been photographed many times, p a r t i c u l a r l y by NASAJs Lunar O r b i t e r s p a c e c r a f t and Apollo 8. - Ori in There i s s t i l l no agreement among s c i e n t i s t s on t h -IT e o r g i n of t h e Moon. The t h r e e t h e o r i e s : (1) t h e Moon once w a s p a r t of E a r t h and s p l i t o f f i n t o i t s own o r b i t , ( 2 ) i t evolved as a s e p a r a t e body a t t h e same time a s E a r t h , and (3) i t formed elsewhere i n space and wandered u n t i l i t was captured by E a r t h ' s g r a v i t a t i o n a l f i e l d . Physical F a c t s Mameter 2,160 miles (about that of Earth) Circumference 6,790 miles (about Distance from E a r t h 238,857 m i l e s (mean; 221,463 minimum t o 252,710 maximum) Surface temperature +243O~(sun a t z e n i t h ) - 2 7 9 ' ~ ( n i g h t ) Surface g r a v i t y 1/6 t h a t of E a r t h Mass 1/100th ghat of E a r t h Volume 1/50th t h a t of E a r t h Lunar day and n i g h t 1 4 E a r t h days each Mean v e l o c i t y i n o r b i t 2,287 m i l e s p e r hour Escape v e l o c i t y 1.48 m i l e s p e r second & t h a t of Earth) Month ( p e r i o d of r o t a t i o n 27 days, 7 hours, 43 minutes around E a r t h ) �Apollo Lunar Landing S i t e s P o s s i b l e l a n d i n g s i t e s f o r t h e Apollo l u n a r module have been under study by NASA's Apollo S i t e S e l e c t i o n Board f o r more than two years. T h i r t y s i t e s o r i g i n a l l y were considered. These have been narrowed down t o f o u r f o r t h e f i r s t l u n a r landing. ( S i t e 1 c u r r e n t l y not considered f o r f i r s t landing.) S e l e c t i o n o f t h e f i n a l f i v e s i t e s was based on high r e s o l u t i o n photographs by Lunar O r b i t e r s p a c e c r a f t , p l u s close-up photos and s u r f a c e d a t a provided by t h e Surveyor s p a c e c r a f t which s o f t landed on t h e Moon. - The o r i i n a l sites a r e l o c a t e d on t h e v i s i b l e s i d e of t h e Moon w i t h i n 5 degrees e a s t and west of t h e Moon's c e n t e r and 5 degrees n o r t h and s o u t h of i t s equator. !$ The f i n a l s i t e choices were based on t h e s e f a c t o r s : *Smoothness ( r e l a t i v e l y few c r a t e r s a n d b o u l d e r s ) "Approach (no l a r g e hills, h i g h c l i f f s , o r deep c r a t e r s t h a t could cause i n c o r r e c t a l t i t u d e s i g n a l s t o t h e l u n a r module l a n d i n g r a d a r ) "Propellant requirements ( s e l e c t e d s i t e s r e q u i r e t h e least expenditure of s p a c e c r a f t p r o p e l l a n t s ) *Recycle ( s e l e c t e d s i t e s allow e f f e c t i v e launch p r e p a r a t i o n r e c y c l i n g i f t h e Apollo Saturn V countdown i s delayed) "Free r e t u r n ( s i t e s a r e w i t h i n reach of t h e s p a c e c r a f t luanched on a f r e e r e t u r n t r a n s l u n a r t r a j e c t o r y ) -- "Slope ( t h e r e i s l i t t l e s l o p e l e s s t h a n 2 degrees i n t h e approach p a t h and landing a r e a ) �The F l v e Landing S i t e s P i n a l l y Selected Are: Designations - Center Coordinates l a t i t u d e 2' 37' 54" North longitude 34 01' 31" East S i t e 1 is l o c a t e d on t h e e a s t c e n t r a l p a r t of t h e Moon i n s o u t h e a s t e r n Mare Tranq u i l l i t a t i s . The s i t e i s approximately 62 m i l e s (100 k i l o m e t e r s ) east of t h e rlm of C r a t e r Maskelyne, Site 2 l a t i t u d e 0' 43l $" North longitude 23' 38' 51" East S i t e 2 i s located on t h e e a s t c e n t r a l p a r t of t h e Moon in southwestern Mar Tranq u i l l i t a t i s , The s i t e i s approximately 62 m i l e s (100 k i l o m e t e r s ) e a s t o f t h e r h of Crater Sabine and approximately 118 m i l e s (190 k i l o m e t e r s ) southwest of t h e C r a t e r Maskelyne. Site 3 l a t i t u d e o0 22' 27'' North longitude lo 20' 42" West S i t e 3 i s l o c a t e d n e a r t h e c e n t e r of the v i s i b l e f a c e of t h e Moon i n t h e southwestern p a r t of Sinus Medii. The s i t e i s approximately 25 m i l e s (40 k i l o m e t e r s ) west of t h e c e n t e r or' the face and 21 m i l e s (50 kilometers) southwest of t h e C r a t e r Bruce, Site 4 l a t i t u d e 3 O 28' 34" South longitude 36 41' 53" West S i t e 4 i s l o c a t e d on the west c e n t r a l p a r t of t h e Moon i n s o u t h e a s t e r n Oceanus Procellanun. The s i t e i s approximately 149 m i l e s (240 k i l o m e t e r s ) south of t h e r i m of C r a t e r Encke and 136 m i l e s (220 k i l o m e t e r s ) e a s t of t h e r i m of C r a t e r Flamsteed, Site 5 l a t i t u d e lo 461 19" North longitude 41' 50' 20" West S i t e 5 i s l o c a t e d on t h e w e s t c e n t r a l p a r t of t h e v i s i b l e f a c e in southeastern Oceanus Procellanun, The s i t e i s approximately 130 m i l e s (210 k i l o m e t e r s ) s o u t h s e s t of t h e rim of C r a t e r Kepler and 118 m i l e s (190 kilometers) n o r t h n o r t h e a s t of t h e r i m of Crater Flamsteed, �APOLLO LUNAR LANDING S I T E S �COMMAND AND SERVICE MOUDLE STRUCTURE, SYSTEMS The Apollo s p a c e c r a f t for t h e Apollo 10 mission i s comprised o f Command Module 106, S e r v i c e Module 106, Lunar Module 4, a s p a c e c r a f t - l u n a r module a d a p t e r (SLA) and a launch escape system, The SLA s e r v e s as a m a t i n g s t r u c t u r e between t h e instrument u n i t a t o p t h e S-IVB s t a g e of t h e S a t u r n V launch v e M c l e and as a housing f o r t h e l u n a r mcdule. -- Launch Escape System (LES) P r o p e l s command module t o s a f e t y i n a n a b o r t e d launch, It i s made up of an open-frame tower s t r u c t u r e , mounted t o t h e command module by f o u r f r a n g i b l e b o l t s , and three s o l i d - p r o p e l l a n t rocket motors: a 147,000 poundt h r u s t launch escape system motor, a 2,400-pound-thrust p i t c h c o n t r o l motor, and a 31,500-pound-thrust tower j e t t i s o n motor. Two canard vanes n e a r t h e t o p deploy t o t u r n t h e command module aerodynamically t o an a t t i t u d e w i t h t h e h e a t - s h i e l d forward. Attached t o t h e base of t h e launch escape tuwer i s a boost prot e c t i v e c o v e r composed of g l a s s , c l o t h , and honeycomb, t h a t p r o t e c t s t h e command module from r o c k e t exhaust g a s e s from t h e main and t h e j e t t i s o n motors, The system I s 33 f e e t t a l l , f o u r P e e t i n diameter a t t h e base, and weighs 8,848 pounds. Command Module (CM) S t r u c t u r e -- The basic s t r u c t u r e of' t h e command module i s a pressure v e s s e l encased i n h e a t s h i e l d s , cone-shaped 11 f e e t 5 i n c h e s high, base diameter of 1 2 feet-10 inches, and launch weight 12,27'7 pounds. The command module c o n s i s t s o f t h e forward compartment which c o n t a i n s two r e a c t i o n c o n t r o l engines and components of t h e Earth l a n d i n g system; t h e crew compartment o r i n n e r p r e s s u r e v e s s e l c o n t a i n i n g crew accomodatlons, c o n t r o l s and d i s p l a y s , and s p a c e c r a f t systems; and t h e a f t compartment housing t e n r e a c t i o n c o n t r o l engines and p r o p e l l a n t tankage. The crew compartment c o n t a i n s 210 c u b i c f e e t o f h a b i t a b l e volume. Heat-shields around the t h r e e compartments are made of brazed s t a n l e s s steel honeycomb w i t h an o u t e r l a y e r of phenolic epoxy resin as an a b l a t i v e material, S h i e l d thickness, varying according t o hea% l o a d s , ranges from 0.7 inch at the apex t o 2.7 Inches a t the a f t end, The s p a c e c r a f t inner s t r u c t u r e i s of sheet-aluminum honeycomb bonded sandwhich ranging i n t h i c k n e s s from 0.25 i n c h t h i c k a t fo*ard a c c e s s t u n n e l t o 1.5 inches t u c k a t base. CSM 106 and LM-4 are equipped w i t h the probe-and-drogue docking hardware. The probe assembly i s a f o l d i n g coupling and Impact a t t e n t u a t i n g d e v i c e mounted on the CM t u n n e l t h a t mates w i t h a c o n i c a l drogue mounted on t h e Lfvl docking t u n n e l . After t h e docking latches are dogged down f o l l o w i n g a docking maneuver, both t h e probe and drogue a s s e m b l i e s are removed from the v e h i c l e t u n n e l s and stowed t o a l l o w free crew t r a n s f e r between the CSM a n d LM. �APOLLO SPACECRAFT �EARTH LANDING SUBSYSTEM DOCKING M E C H A N I S M STABILIZATION EARTH LANDING ENVIRONMENTAL ( I N BOOST COVER) ROLL E N G I N E S WI*DOW ( 2 PLACES1 ENGINES COMMAND MODULE FLY AWAY UMBILICAL SERVICE MODULE SECTOR I V O X I G I N TANKS 1 I O R O G I N T A N K S L I P S FUEL C I L L S CENTER SECTION S I R V I C I PROPUlSlON SISTEM n f L l u M T A N K S > �LUNAR MODULE COMMAND MODULE DROGUE ASSEMBLY DOCKING RING \ PROBE ASSEMBLY \ LATCH ASSEMBLIES APOLLO DOCKING MECHANISMS �-- S e r v i c e Module (SM) S t r u c t u r e The s e r v i c e module f s a c y l i n d e r 12 feet 10 i n c h e s f n d i a m e t e r by 24 feet 7 I n c h e s U g h , F o r the Apollo 10 m i s s i o n , it w 5 l l weigh, 51,371 pounds a t launch. Aluminum honeycomb p a n e l s one i n c h t h i c k form the o u t e r skin, and m i l l e d aluminum r a d i a l beams separate the i n t e r i o r InCo s i x s e c t i o n s c o n t a i n i n g s e r v i c e propulsion system and r e a e t f o n c o n t r o l f u e l - o x i d i z e r tankage, f u e l c e l l s , c r y o g e n i c oxygen and hydrogen, and onboard conszunables. -- S p a c e c r a f t -LM Adapter (sLA) S t r u c t u r e The spacecrat't LM a d a p t e r 1s a t r u n c a t e d cone 28 f e e t l o n g t a p e r i n g from 200 i n c h e s d i a m e t e r a t the base t o 154 i n c h e s a t t h e forward end a t t h e s e r v i c e module m a t i n g l i n e . Aluminum honeycomb 1.75 i n c h e s t h i c k i s the s t r e s s e d - s k i n s t r u c t u r e f o r the s p a c e c r a f t adapter. The SLA weighs 4,000 pounds. CSM Systems --e -- Guidance, Navigation and C o n t r o l S s t e m D N C S ) Measures caland c o n t r o l s s p a c e c r a f t p o s i t i o n , att t u d e anmelocity, c u l a t e s t r a d e c t o r y , c o n t r o l s s p a c e c r a f t p r o p u l si on s y s t e m t h r u s t v e c t o r , and d i s p l a y s a b o r t data. The g u i d a n c e s y s t e m c o n s i s t s a:' three subsystems: I n e r t i a l , made up of' a n inertial measurement u n i t and a s s o c i a t e d power and data components; computer which p r o c e s s e s i n f o r m a t i o n t o o r from ocher components; and o p t i c s , i n c l u d i n g s c a n n i n g t e l e s c o p e and sext3mt f o r celesl3al and/or landmark s p a c e c r a f t n a v i g a t i o n . CSM 106 and subsequent modules a r e equipped with a VHF r a n g i n g d e v i c e a s a backup t o the LM rendezvous r a d a r . S t a b i l i z a t i o n and C o n t r o l System (SCS) -- C o n t r o l s spacec r a f t r o t a t i o n , t r a n s l a t i o n , and t h r u s t v e c t o r a n d p r o v i d e s d i s p l a y s f o r c r e w - i n i t i a t e d maneuvers; backs up tihe guidance system. It has t h r e e subsystems: a t t i t u d e r e f e r e n c e , a t t l t u d e c o n t r o l , and t h r u s t v e c t o r c o n t r o l , -- Provides t h r u s t f o r l a r g e S e r v i c e P r o p u l s i o n System ( S P S ) s p a c e c r a f t v e l o c i t y changes t h r o u g n a gimbal-mounted 20,500pound-thrust h y p e r g o l i c e n g i n e u s i n g a n i t r o g e n t e t r i o x i d e o x i d i z e r and a 50-Fj0 m i x t u r e o f unsymmetrl c a l dimethyl h y d r a z i n e and h y d r a z i n e f u e l . Tankage o f t h i s s y s t e m i s i n zhe s e r v i c e module. The system responds t o a u t o m a t i c f l r i n g commands from the guida n c e and n a v i g a t i o n system o r t o manual commands from t h e crew. The e n g i n e p r o v i d e s a c o n s t a n t t h r u s t rate. The s t a b i l i z a t i o n and c o n t r o l system g i m b a l s the e n g i n e t o f i r e t h r o u g h t h e s p a c e c r a f t c e n t e r of g r a v i t y . -- The command module and t h e R e a c t i o n C o n t r o l System (RCS) s e r v i c e module e a c h has i t s own independent system. The SM RCS has f o u r i d e n t i c a l RCS "quads mounted around t h e SM 90 d e g r e e s apart. Each quad has f o u r 100 p o u n d - t h r u s t e n g i n e s , two f u e l and two o x i d i z e r t a n k s and a helium p r e s s u r i z a t i o n sphere. The SM RCS p r o v i d e s redundant s p a c e c r a f t a t t i t u d e c o n t r o l t h r o u g h c r o s s - c o u p l i n g l o g i c i n p u t s from the s t a b i l i z a t i o n and g u i d a n c e systems. �Small v e l o c i t y change maneuvers can a l s o be made w i t h the SM RCS. The CM RCS c o n s i s t s o f two independent s i x - e n g i n e sub- systems o f s i x 93 pound-thrust e n g i n e s each. Both subsystems are a c t i v a t e d a f t e r CM s e p a r a t i o n from t h e SM: one is used f o r s p a c e c r a f t a t t i t u d e c o n t r o l d u r i n g e n t r y . The o t h e r s e r v e s i n s t a n d b y as a backup. P r o p e l l a n t s for b o t h CM and SM RC$ are monomethyl h y d r a z i n e f u e l and n i t r o g e n t e t r o x i d e o x i d i z e r with helium p r e s s u r i z a t i o n . These p r o p e l l a n t s are h y p e r g o l i c , i . e . , t h e y burn s p o n t a n e o u s l y when combined w i t h o u t an i g n l t e r . -- E l e c t r i c a l Power System (EPS) C o n s i s t s o f t h r e e , 31c e l l Bacon-type hydrogen-oxygen f u e l c e l l power p l a n t s i n t h e s e r v i c e module which supply 2 8 - v o l t DC power, t h r e e 28-volt DC z i n c - s i l v e r o x i d e main s t o r a g e b a t t e r i e s i n t h e command module lower equipment bay, and three 115-200-volt 400 h e r t z t h r e e phase AC i n v e r t e r s powered by t h e main 2 8 - v o l t DC bus. The i n v e r t e r s are a l s o l o c a t e d i n t h e lower equipment bay, Cryogenic hydrogen and oxygen react i n the f u e l c e l l s t a c k s t o provide e l e c t r i c a l power, p o t a b l e water, and h e a t . The command module main b a t t e r i e s can be switched t o f i r e p y r o t e c h n i c s i n an emergency. A b a t t e r y c h a r g e r r e s t o r e s s e l e c t e d batteries t o f u l l s t r e n g t h as r e q u i r e d w i t h power from t h e f u e l c e l l s . -- Environmental C o n t r o l System (Ecs) Controls spacecraft atmosphere, p r e s s u r e , and t e m p e r a t u r e and manages water. In a d d i t i o n t o r e g u l a t i n g c a b i n and s u i t gas p r e s s u r e , t e m p e r a t u r e and humidity, t h e system removes carbon d i o x i d e , o d o r s and p a r t i c l e s , and v e n t i l a t e s t h e c a b i n a f t e r l a n d i n g . I t c o l l e c t s and s t o r e s f u e l c e l l p o t a b l e water f o r crew use, s u p p l i e s water t o t h e g l y c o l e v a p o r a t o r s f o r c o o l i n g , and dwnps s u r p l u s w a t e r overboard t h r o u g h the u r i n e dump v a l v e . P r o p e r o p e r a t i n g tempe r a t u r e of e l e c t r o n i c s and e l e c t r i c a l equipment i s m a i n t a i n e d by t h i s system t h r o u g h t h e u s e of t h e c a b i n h e a t exchangers, t h e s p a c e r a d i a t o r s , and t h e f l y c o l e v a p o r a t o r s . Telecommunications System -- P r o v i d e s v o i c e , t e l e v i s i o n t e l e metry, and command d a t a and t r a c k i n g and r a n g i n g between t h e spacec r a f t and E a r t h , between t h e command module and t h e l u n a r module and between t h e s p a c e c r a f t and t h e e x t r a v e h i c u l a r a s t r o n a u t . It a l s o p r o v i d e s intercommunications between a s t r o n a u t s . The t e l e c o m u n i c a t i o n s system c o n s i s t s o f p u l s e code modulated t e l e m e t r y f a r r e l a y i n g t o Manned Space P l i g h t Network s t a t i o n s d a t a on s p a c e c r a f t systems and crew c o n d i t i o n , VHP/AM voice, and u n i f i e d S-Band t r a c k i n g t r a n s p o n d e r , a i r - t o - g r o u n d v o i c e communications, onboard t e l e v i s i o n , and a VHF' recovery beacon. Network s t a t i o n s can t r a n s m i t t o t h e s p a c e c r a f t s u c h i t e m s as u p d a t e s t o t h e Apollo guidance computer and c e n t r a l t i m i n g equipment, and r e a l time commands f o r c e r t a i n onboard f u n c t i o n s . �S-band inflight antenna- 7 LM docking light SPACECRAFT AXIS A N D ANTENNA LOCATIONS �Two scimitar VHF omni antennas on SM--I (180deg. apart) axis Rendezvous radar SPACECRAFT AXIS A N D ANTENNA LOCATIONS �The high-gain s t e e r a b l e S-Band antenna c o n s i s t s o f four, 31-inch-diameter p a r a b o l i c d i s h e s mounted on a f o l d i n g boom a t the a f t end of t h e s e r v i c e module. Nested a l o n g s i d e t h e s e r v i c e p r o p u l s i o n system engine nozzle u n t i l deployment, t h e antenna swings out a t r i g h t a n g l e s t o t h e s p a c e c r a f t l o n g i t u d i n a l a x i s , w i t h t h e boom p o i n t i n g 52 degrees below t h e heads-up h o r i z o n t a l , S i g n a l s from t h e ground s t a t i o n s can be t r a c k e d e i t h e r automati c a l l y o r manually with t h e a n t e n n a ' s g i m b a l l i n g system. Normal S-Band voice and uplink,downlink communications w i l l be handled by t h e omni and high-gain antennas. -- S e q u e n t i a l System I n t e r f a c e s w i t h o t h e r s p a c e c r a f t systems and subsystems t o i n i e i a t e time c r i t i c a l f u n c t i o n s d u r i n g launch, docking maneuvers, s u b - o r b i t a l a b o r t s , and e n t r y p o r t i o n s of a mission. The system a l s o c o n t r o l s r o u t i n e s p a c e c r a f t sequencing such as s e r v i c e module s e p a r a t i o n and deployment of t h e E a r t h landing system. -- Detects and d i s p l a y s t o the c d i t i o n s , such as e x c e s s i v e p i t c h o r r o l l r a t e s o r two engines out, and a u t o m a t i c a l l y o r manually s h u t s down t h e b o o s t e r and a c t i v a t e s t h e launch escape system; f'unctions u n t i l t h e s p a c e c r a f t i s i n o r b i t , -- ) Includes t h e drogue and main s t - l a n d i n g recovery a i d s . I n a parac normal e n t r y descent, t h e command module forward h e a t s h i e l d i s j e t t i s o n e d a t 24,000 f e e t , p e r m i t t i n g m o r t a r deployment of two r e e f e d 16.5-foot diameter drogue p a r a c h u t e s f o r o r i e n t i n g and d e c e l e r a t i n g t h e s p a c e c r a f t , After d i s r e e f and drogue r e l e a s e , t h r e e p i l o t mortar deployed c h u t e s p u l l o u t t h e t h r e e main 83.3-foot diameter p a r a c h u t e s with two-stage r e e f i n g t o provide g r a d u a l i n f l a t i o n i n t h r e e s t e p s , Two main p a r a c h u t e s out of t h r e e can provide a s a f e landing. Recovery a i d s i n c l u d e t h e u p r i g h t i n g system, swimmer i n t e r phone connections, s e a dye marker, f l a s h i n g beacon, VHF recovery beacon, and VHF t r a n s c e i v e r , The u p r i g h t i n g system c o n s i s t s of t h r e e compressor-inflated bags t o u p r i g h t t h e s p a c e c r a f t if i t should land i n t h e water apex down ( s t a b l e I1 p o s i t i o n ) . -- Monitors s p a c e c r a f t systems f o r o~t-o a l e r t s crew by v i s u a l and a u d i b l e alarms s o t h a t c r e m e n may trouble-shoot t h e problem. -- Controls and Displays Provide r e a d o u t s and c o n t r o l f u n c t i o n s of a l l o t h e r s p a c e c r a f t systems i n t h e command and s e r v i c e modules, A l l c o n t r o l s a r e designed t o be operated by crewmen i n p r e s s u r i z e d s u i t s . Displays a r e grouped by system and l o c a t e d according t o t h e frequency t h e crew r e f e r s t o them. �WNAR MODULE STRUCTURESy WEIGHT The lunar module is a two-stage v e h i c l e designed f o r space o p e r a t i o n s near and on t h e Moon, The W is incapable of r e e n t e r i n g the atmosphere. The lunar module s t a n d s 22 f e e t 11 inches high and is 31 f e e t wide (diagonally a c r o s s landing g e a r ) , Joined by four explosive b o l t s and umbilicals, t h e asc e n t and descent s t a g e s of t h e LM operate as a u n i t u n t i l s t a g i n g , when the a s c e n t s t a g e f u n c t i o n s as a s i n g l e spacec r a f t f o r rendezvous and docking with t h e CSM. Ascent Stage Three main s e c t i o n s make up t h e a s c e n t stage: t h e crew compartment, midsection, and a f t equipment bay. Only t h e crew compartment and midsection a r e p r e s s u r i z e d (4.8 psig; 337.4 gm/sq cm) as p a r t o f t h e LM cabin; a l l o t h e r s e c t i o n s of t h e LM a r e unpressurized, The cabin volume is 235 cubic f e e t ( 6 . 7 cubic m e t e r s ) . The a s c e n t s t a g e measures 12 f e e t 4 inches high by 14 f e e t 1 inch i n diameter. S t r u c t u r a l l y , t h e a s c e n t s t a g e has s i x s u b s t r u c t u r a l areas: crew compartment, midsection, a f t equipment bay, t h r u s t chamber assembly c l u s t e r supports, antenna supports and thermal and microme teoroid s h i e l d . The c y l i n d r i c a l crew compartment i s a semimonocoque s t r u c t u r e o f machined longerons and fusion-welded aluminum s h e e t and i s 92 inches (2.35 m ) i n diameter and 42 inches (1.07 m) deep, Two f l i g h t s t a t i o n s a r e equipped with c o n t r o l and d i s play panels, a r m r e s t s , body r e s t r a i n t s , landing aids, two f r o n t windows, an overhead docking window, and a n alignment o p t i c a l telescope In t h e c e n t e r between t h e two f l i g h t s t a t i o n s , The h a b i t a b l e volume i s 160 cubic feet. Two t r i a n g u l a r f r o n t windows and t h e 32-inch (0.81 rn) square inward-opening forward h a t c h are i n t h e crew compartment f r o n t face. External s t r u c t u r a l beams support t h e crew compartment and serve t o support t h e lower i n t e r s t a g e mounts a t t h e i r lower ends, R i n g - s t i f fened semimonocoque c o n s t r u c t i o n i s employed i n the midsection, w i t h chem-milled aluminum skin over fusion-welded longerons and s t i f f e n e r s , Fore -and-aft beams a c r o s s t h e t o p of t h e midsection j o i n with those running a c r o s s t h e t o p of t h e cabin t o take a l l a s c e n t s t a g e stress loads and, i n e f f e c t , i s o l a t e t h e cabin from stresses, �DOCKING LUNAR SURFACE SENSING PROBE (4) APOLLO LUNAR MODULE �VHF ANTENNA(2) TRANSFER TUNNEL AND HATCH ALIGNMENT OPTICAL TELESC OCKING TARGET RECESS GASEOUS OXYGEN TANK (2) RENDEZVOUS RADAR ANTENNA AFT EQUIPMENT BAY REPLACEABLE ELECTRONIC ASSEMBLY FUEL TANK (REACTION CONTROL) IQUlD OXYGEN TANK ASCENT ENGINE COVER S-BAND INFLIGHT ANTENNA Q) HELIUM TANK @) HELIUM TANK (REACTION CONTROL) REACTION CONTROL ASSEMBLY (4 PLACES) OXIDIZER TANK (REACTION CONTROL) INGRESS/EGRESSHATCH CREW COMPARTMEN WATER TANKQ) APOLLO LUNAR MODULE - ASCENT STAGE �LM CABIN INTERIOR, LEFT HALF �LM CABIN INTERIOR, RIGHT HALF �The a s c e n t s t a g e engine compartment i s formed by two beams running a c r o s s t h e lower midsection deck and mated t o t h e f o r e and a f t bulkheads. Systems located i n t h e midsection include t h e LM guidance computer, t h e power and servo assembly, a s c e n t engine propellant tanks, RCS prop e l l a n t tanks, t h e environmental c o n t r o l system, and t h e waste management section. A tunnel r i n g a t o p t h e a s c e n t s t a g e meshes with t h e command module l a t c h assemblies. During docking, t h e r i n g and clamps a r e aligned by t h e LM drogue and the CSM probe, The docking tunnel extends downward i n t o t h e midsection The tunnel is 32 Inches (0.81 cm) i n diameter and is used f o r crew t r a n s f e r between t h e CSM and LFnl by crewmen. The upper hatch on t h e inboard end of' t h e docking tunnel hinges downward and cannot be opened with t h e pressurized and undocked. 16 inches (40 cm). A thermal and micrometeoroid s h i e l d of multiple l a y e r s of mylar and a s i n g l e thickness of t h i n aluminum s k i n encases t h e e n t i r e ascent s t a g e s t r u c t u r e . Descent Stage The descent s t a g e c o n s i s t s of a cruciform load-carrying s t r u c t u r e of two p a i r s of p a r a l l e l beams, upper and lower decks, and enclosure bulkheads -- a l l of conventional skin-and-stringer aluminum a l l o y construction. The c e n t e r compartment houses the descent engine, and descent propellant tanks a r e housed i n the four square bays around the engine. The descent stage measures 10 f e e t 7 inches high by 14 f e e t 1 inch i n diameter. Pour-legged t r u s s o u t r i g g e r s mounted on the ends of each p a i r of beams serve a s SLA a t t a c h points and a s "knees" f o r the landing g e a r main s t r u t s . Triangular bays between t h e main beams a r e enclosed i n t o quadrants housing such components a s t h e ECS water tank, helium tanks, descent engine c o n t r o l assembly of t h e guidance, navig a t i o n and c o n t r o l subsystem, ECS gaseous oxygen tank, and b a t t e r i e s f o r the e l e c t r i c a l power system. Like the ascent stage, t h e descent s t a g e is encased i n the mylar and aluminum a l l o y thermal and micrometeoroid shLeld. The I;M e x t e r n a l platform, o r "porch", is mounted on the forward o u t r i g g e r j u s t below t h e forward hatch. A ladder extends down t h e forward landing gear s t r u t from t h e porch f o r crew lunar s u r f a c e operations. ��I n a r e t r a c t e d p o s i t i o n u n t l . 1 a f t e r t h e crew mans t h e LM, t h e landing g e a r struts a r e e x p l o s i v e l y extended and provide l u n a r s u r f a c e landing impact a t t e n u a t l o n W 4 e ma i n s t r u t s a r e f i l l e d with c r u s h a b l e aluminum honeycomb f o r absorbing compression l o a d s . Footpads 37 inches ( 0 . 9 5 m) I n diameter a t t h e end o f each landing g e a r provide v e h i c l e " f l o a t a t i o n " on t h e l u n a r s u r f a c e , . Each pad i s f i t t e d with a l u n a r - a u ~ f a c e s e n s i n g probe which s i g n a l s t h e crew t o s h u t down t h e d e s c e n t engine upon contact with the lunar surface. LM-11 flown on t h e Apollo 10 mission w i l l have a launch weight o f 30,849 pounds. The weight breakdown is as follows: Ascent s t a g e , d r y 4,781 l b s . Descent s t a g e , d r y 4,703 l b s . RCS propel l a n t s DPS propel l a n t s 612 ~ b s . 18,134 l b s . APS p r o p e l l a n t s Lunar Module Systems E l e c t r i c a l Power System -- The LM DC electrical system masts of s i x s i l v e r z i n c primary b a t t e r i e s -- f o u r i n the d e s c e n t s t a g e and two i n t h e a s c e n t s t a g e , each w i t h i t s own e l e c t r i c a l c o n t r o l assembly (ECA) Power f e e d e r s from a l l primary b a t t e r i e s pass through c i r c u i t b r e a k e r s t o e n e r g i z e t h e LM DC buses, from which 28-volt DC power i d distributed through c i r c u i t b r e a k e r s t o a l l LM systems. A? power (117v 400Hz) i s s u p p l i e d by two i n v e r t e r s , e l t h e r o f which can supply s p a c e c r a f t AC load needs t o t h e AC buses. . Environmental Control System -- C o n s i s t s c f t h e atmosphere r e v i t a l i z a t i o n s e e t l o n , oxygen supply n - - and cabin pressure c f ~trcl s e c t i o n , water management,-heat t r a n s p o r t s e c t i o n , and o u t i e t s f o r oxy en and water s e r v i c i n g o f t h e F o r t a b i e L i f e Support, Sys tem TPLSS). �Components of t h e atmosphere r e v i t a l i z a t i o n s e c t i o n are the s u i t c i r c u i t assembly which c o o l s and v e n t i l a t e s t h e pressure garments, reduces carbon d i o x i d e l e v e l s , removes o d c r s , noxious g a s e s and e x c e s s i v e moisture; t h e c a b i n rec l r c u l a t J o n assembly which v e n t i l a t e s and c o n t r o l s c a b i n atmosphere temperatures; and t h e steam f l e x d u c t which v e n t s t o space steam from t h e s u i t c i r c u i t water e v a p o r a t o r . The oxygen supply and cabin p r e s s u r e s e c t i o n s u p p l i e s gaseous axygen t c t h e atmosphere r e v i t a l i z a t i o n s e c t i o n f o r maintaining s u i t and c a b i n p r e s s u r e . The d e s c e n t s t a g e oxygen supply provides d e s c e n t f l i g h t phase and l u n a r s t a y oxygen needs, and t h e a s c e n t s t a g e oxygen supply provides oxygen needs f o r t h e a s c e n t and rendezvous f l i g h t phase. Water f o r d r i n k i n g , cooling, f i r e f i g h t i n g , food p r e p a r a t i o n , and r e f i l l i n g t h e PLSS c o o l i n g water s e r v i c i n g tank i s s u p p l i e d by t h e water management s e c t i o n . The water i s contained i n t h r e e n i t r o g e n - p r e s s u r i z e d bladder-type tanks, one o f 367-pound c a p a c i t y i n t h e d e s c e n t s t a g e and two of 147.5-pound c a p a c l t y i n t h e a s c e n t s t a g e . The heat t r a n s p o r t s e c t i o n h a s primary and secondary water-glycol s o l u t i o n c o o l a n t loops. The primary c o o l a n t l o o p c i r c u l a t e s water-glycol f o r temperature c o n t r o l o f cabin cnd s u i t c l r c u i t oxygen and f o r thermal c o n t r o l of b a t t e r i e s and electronic components mounted on cold p l a t e s and r a i l s . If' the primary loop becomes i n o p e r a t i v e , t h e secondary loop c i r c u l a t e s c o o l a n t through t h e r a i l s and c o l d p l a t e s only. E u i t c i r c u i t c ~ o l i n gd u r i n g secondary c o o l a n t loop o p e r a t i o n ?s provided by the s u i t loop water b o i l e r . Waste h e a t from b o t h l o o p s is v e n t e d overboard by water e v a p o r a t i o n o r subllrnators. Zomunlcation System -- Two S-band t r a n s m i t t e r - r e c e i v e r s , two VHF t r a n s m i t t e r - r e c e i v e r s , a s i g n a l processing assembly, and a s s o c t a t e d s p a c e c r a f t antenna make up t h e LM communications system. The system t r a n s m i t s and r e c e i v e s v o i c e , t r a c k i n g and ranglng d a t a , and t r a n s m i t s t e l e m e t r y d a t a on 281 measurements and TV s i g n a l s t o t h e ground. Voice communications between t h e TLM and ground s t a t i o n s i s by S-band, and between t h e LN and CSM voice i s on VHF. �Real-time commands t o t h e l u n a r module are r e c e i v e d and encoded by t h e d i g i t a l u p l i n k assembly--a black box t i e d i n t o the S-band r e c e i v e r . The d i g i t a l u p l i n k assembly w i l l be used on Apollo 10 t o arm and f i r e thg a s c e n t propulsion system f o r the unmanned APS d e p l e t i o n burn following f i n a l docking and LM j e t t i s o n . LM-4 w i l l b e t h e l a s t s p a c e c r a f t t o be f i t t e d with equipment f o r a c c e p t i n g r e a l - t i m e commands from t h e ground. The d a t a s t o r a g e e l e c t r o n i c s assembly (DSEA) i s a f o u r channel voice r e c o r d e r with timing s i g n a l s w i t h a 10-hour recording c a p a c i t y which w i l l be brought back i n t o t h e CSM for r e t u r n t o Earth. DSEA r e c o r d i n g s cannot be "dumped" t o ground s t a t i o n s . rsJI antennas a r e one 26-inch diameter p a r a b o l i c S-band s t e e r a b l e antenna, two S-band i n f l i g h t antennas and two VHF I n f l i g h t antennas. Guidance, Navigation and Control System -- Comprised o f six s e c t i o n s : idance and n a v i g a t l o n s e c t i o n (PGNS), a b o r t guidance radar section, control electronics s e c t i o n (CES), and o r b i t a l r a t e d r i v e e l e c t r o n i c s f'or Apollo and LM (ORDEAL). * The PGNS i s a n i n e r t i a l system a i d e d by t h e alignment o p t i c a l t e l e s c o p e , a n i n e r t i a l measurement u n i t , and t h e r e n dezvous and landing r a d a r s . The system provides i n e r t i a l r e f e r e n c e d a t a f o r computations, produces i n e r t fa1 alignment r e f e r e n c e by feeding o p t i c a l s i g h t i n g data i n t o the LM guidance computer, d i s p l a y s p o s i t i o n and v e l o c i t y d a t a , computes TA-CSM rendezvous d a t a from r a d a r i n p u t s , c o n t r o l s a t t i t u d e and t h r u s t t o maintain d e s i r e d LM t r a j e c t o r y , and c o n t r o l s d e s c e n t engine t h r o t t l i n g and gimbaling. * The AGS i s an independent backup s y s t e m f o r t h e PGNS, having i t s own i n e r t i a l s e n s o r and computer. *. The r a d a r s e c t i o n i s made up of t h e rendezvous radar which provldes CSM range and range r a t e , and l i n e - o f - s i g h t a n g l e s f o r maneuver computation t o t h e LM guidance computer; t h e landing r a d a r which provide a l t i t u d e and v e l o c i t y data t o t h e TSJI guidance computer during l u n a r l a n d i n The rendezvous radar has an o p e r a t i n g range from 80 f e e t t o 4 6 n a u t i c a l miles. The range t r a n s f e r tone assembly, u t i l i z i n g VKF e l e c t r o n i c s , i s a p a s s i v e responder t o t h e CSM VHF ranging device and i s a backup t o the rendezvous r a d a r . d �+ 217e CES c o n t r o l s I24 a t t i t u d e and t r a n s l a t i o n about a l l axes. I t a l s o c o n t r o l s by PGNS command t h e automatic o p e r a t i o n of t h e a s c e n t and d e s c e n t engines., and t h e r e a c t i o n c o n t r o l t h r u s t e r s . Manual a t t j t u d e c o n t r o l l e r and t h r u s t - t r a n s l a t i o n controller commands are a l s o handled by t h e CES. * ORDEAL, d i s p l a y s on t h e f l i g h t d i r e c t o r a t t i t u d e i n d i c a t o r , is t h e computed l o c a l v e r t i c a l i n t h e p i t c h a x i s during circular, Earth o r lunar o r b i t s . Reaction C o n t r o l System -- The LM has f o u r RCS engine c l u s t e r s o f four 100-pound (45.8 kg) t h r u s t engines each which use helium-pressurized hypergollc p r o p e l l a n t s . The o x l d l z e r 1s n i t r o g e n t e t r o x i d e , f u e l i s Aerozlne 50 ( 5 0 / 5 0 blend of hydrazine and unsymmetrical dimethyl h y d r a z i n e ) . P r o p e l l a n t plumblng, valves and p r e s s u r i z i n g components are i n two p a r a l l e 1, independent s y s terns, each f e e d i n g h a l f the e n g i n e s i n each c l u s t e r . E i t h e r system is capable o f m a i n t a i n l n g a t t i t u d e a l o n e , b u t if one supp3.y system f a i l s , a p r o p e l l a n t c r o s s f e e d a l l o w s one system t o s u p p l y a l l 16 engines, A d d i t i o n a l l y , i n t e r c o n n e c t valves permit t h e RCS system t o draw from a s c e n t engine p r o p e l l a n t t a n k s . The engine c l u s t e r s a r e mounted on o u t r i g g e r s 90 degrees a p a r t on t h e a s c e n t s t a g e . The RCS provides s m a l l s t a b i l i z i n g Impulses d u r i n g a s c e n t and d e s c e n t burns, c o n t r o l s LM a t t i t u d e d u r i n g maneuvers, and produces t h r u s t f o r s e p a r a t i o n , and ascent/deseent engine tank u l l a g e . The system may be o p e r a t e d i n e i t h e r t h e p u l s e o r s t e a d y - s t a t e modes. Descent Propulsion System -- Maximum r a t e d t h r u s t o f t h e d e s c e n t engine i s g,tjq(O pounds (4,380.9 kg) and is t h r o t t l e a b l e between 1,050 pounds (476.7 kg) and 6,300 pounds (2,860.2 kg). The engine can be gi-nbaled s i x degrees i n any d i r e c t i o n f o r o f f s e t c e n t e r of g r a v i t y trimming. P r o p e l l a n t s are heliumpressurized Aerozine 50 and n i t r o g e n t e t r o x i d e . -- The 3,500-pound (1,589 kg) Ascent Propulsion System t h r u s t a s c e n t engine i s n o t gimbaled and performs a t f u l l t h r u s t . The engine remains dormant u n t i l a f t e r t h e a s c e n t s t a g e s e p a r a t e s f r o & t h e d e s c e n t s t a g e . P r o p e l l a n t s are the same as are burned by the RCS engines and t h e d e s c e n t engine. Caution and Warning, C o n t r o l s and Displays -- These two systems have t h e same f u n c t i o n aboard t h e lunar module as t h e y do aboard t h e command module. (see CSM systems s e c t i o n . ) �Tracking and Docking Lights -- A flashing tracking l i g h t (once per second, 20 milliseconds duration) on t h e front face of the lunar module i s an a i d f o r contingency CSM-active rendezvous IH rescue. V i s i b i l i t y ranges from 400 n a u t i c a l miles through the CSM sextant t o 130 miles with the naked eye. Five docking l i g h t s analagous t o a i r c r a f t running l i g h t s a r e mounted on the IN f o r CSM-active rendezvous: two forward yellow l i g h t s , a f t white light, p o r t red l i g h t and starboard green l i g h t . All docking l i g h t s have about a 1,000-foot visibility. �SATURN V LAUNCH VEHICLE DESCRIPTION AND OPERATION The S a t - ~ r nV, 363 feet t a l l with the Apollo s p a c e c r a f t i n place, g e n e r a t e s enough t h r u s t t o place a 125-ton payload i n t o a lO5-nm c i r c u l a r o r b i t of t h e Earth, It can boost about 50 t o n s t o l u n a r o r b i t . The t h r u s t of t h e t h r e e prop u l s i v e s t a g e s range Prom almost 7.6 m i l l i o n pounds f o r t h e booster t o 230,000 pounds f o r t h e t h i r d s t a g e a t operating a l t i t u d e , Including t h e instrument u n i t , t h e launch v e h i c l e without t h e s p a c e c r a f t is 281 feet t a l l , F i r s t Stage The first s t a g e (s-IC) w a s developed j o i n t l y by t h e National Aeronauties and Space Administration's Marshall Space p l i g h t Center, Huntsville, A l a . and t h e Roeing Co. The Marshall Center assembled f o u r S-IC stages: a s t r u c t u r a l test model, a s t a t i c test version, and t h e first two f l i g h t stages. Subsequent f l i g h t s t a g e s are assembled by Boeing a t t h e Michoud Assembly F a c i l i t y , New Orleans, The S-IC s t a g e destined f o r t h e Apollo 10 mission w a s t h e second f l i g h t booster s t a t i c t e s t e d a t t h e NASA-Mississippi Test F a c i l i t y . The f i r s t S-IC test a t MTF w a s on May 11, 1967, and t h e t e s t of t h e second S-IC t h e r e -- t h e booster f o r Apollo 10 -- was completed Aug. 9, 1967. E a r l i e r f l i g h t s t a g e s were s t a t i c f i r e d a t t h e Marshall Center. The S-IC s t a g e boosts t h e space v e h i c l e t o a n a l t i t u d e of 35.8 nm a t 50 nm downrange and i n c r e a s e s t h e v e h i c l e ' s v e l o c i t y t o 5,343 knots i n 2 minutes 40 seconds of powered flight. It then s e p a r a t e s and f a l l s i n t o t h e A t l a n t i c Ocean about 351 nm downrange (30 degrees North l a t i t u d e and 74 degrees West longitude) about nine minutes a f t e r l i f t o f f . Normal propellant flow rate t o t h e f i v e F-1 engines i s Four of t h e engines a r e mounted on a r i n g , each 90 degrees from i t s neighbor, These f o u r are gimballed t o c o n t r o l t h e r o c k e t ' s d i r e c t i o n of P l i g h t . The f i f t h engine i s mounted r i g i d l y i n t h e center. 29,522 pounds p e r second. Seccnd Stage The second stage (S-11), l i k e the t h i r d stage, u s e s high performance 3-2 engines t h a t burn l i q u i d oxygen and l i q u i d hydrogen. The s t a g e ' s purpose is t o provide s t a g e boost n e a r l y t o Earth o r b i t , �SATURN V LAUNCH VEHICLE 5,031,023 LBS. FUELED 294,200 LBS .DRY / LM \ PROPE LLANTS l NSTRUMENT LIQUID OXYGEN (3,258,280 LBS.) RP-I (KEROSENE) (1,417,334 LBS .) (S- IVB . 1,074,590 isS FUELED 84,367 LBS. DRY tf / SECOND STAGE PROPELLANTS LIQUID OXYGEN (829,114 LBS .) LIQUID HYDROGEN . 261,836 LBS FUELED ST STAGE (S-IC) PROPE LLANTS LIQUID OXYGEN (190,785 LBS .) LlQUlD HYDROGEN (43,452 LBS .) NOTE: WEIGHTS AND MEASURES GIVEN ABOVE ARE FOR THE N O M I N A L VEHICLE CONFIGURATION FOR APOLLO 10. THE FIGURES M A Y VARY SLIGHTLY DUE TO CHANGES BEFORE LAUNCH TO MEET C H A N G I N G CONDITIONS. �A t outboard engine cutoff, the S-I1 separates and, following a b a l l i s t i c t r a j e c t o r y , plunges i n t o t h e Atlantic mean abmat 2,400 nm downrange from Kennedy Space Center (31 degrees ~ o p t hl a t i t u d e and 34 degrees west longitude) about 20 minutes a f t e r l i f t o f f , Five J-2 enaines power t h e S-11, The o u t e r four engines a r e equally spaced on a 17.5-foot diameter c i r c l e . These four engines may be glmbaled through a plus o r mlnus sevendegree square p a t t e r n f o r t h r u s t vector control. A s on t h e first stage, t h e c e n t e r engine (number 5) i s mounted on the s t a g e c e n t e r l i n e and is f i x e d i n position, The S - I 1 c a r r i e s t h e rocket t o an a l t i t u d e of about 101,6 nm and a distance of some 888 nm downrange, Before burnout, t h e vehicle w l l l be moving a t a speed of 13,427 knots, The outer 5-2 engines w i l l burn 6 minutes 32 seconds during t h i s powered phase, but t h e c e n t e r engine w i l l be c u t off a t 4 minutes 59 seconds of burn tine, The Space Division of North American Rockwell Corp, builds t h e S-I1 a t Seal Beach, Calif, The c y l i n d r i c a l vehicle i s made up of t h e forward s k i r t t o which t h e t h i r d s t a g e attaches, t h e l i q u i d hydrogen tar&, the l i q u i d oxygen tank (separated from t h e hydrogen tank by a common bulkhead), t h e t h r u s t s t r u c t u r e on which t h e engines a r e mounted and an i n t e r stage s e c t i o n t o which t h e first stage attaches. The common bulkhead between t h e two tanks i s heavily insulated. The S-I1 f o r Apollo 10 was s t a t i c t e s t e d by North American Rockwell a t the NASA-Nississippi Test F a c i l i t y on Aug. 9, 1968, This stage was shipped t o the t e s t s i t e v i a t h e Panama Canal f o r the t e s t f i r i n g , Third Stage The Ehird stage (s-M3) was developed by t h e McDonnell Douglas Astronautics Co, a t Huntington Beach, C a l i f , A t Sacramento, Calif., t h e stage passed a s t a t i c f i r i n g t e s t on O e t , 9, 1967 a s p a r t of the preparation f o r t h e Apollo 10 mission. The stage was flown d i r e c t l y t o t h e NASA-Kennedy Space Center, Measuring 58 f e e t 4 inches long and 21 feet 8 inches i n diameter, t h e S - N B weighs 25,750 pounds Qry, A t first i g n i t i o n , i t weighs 261,836 pounds, The i n t e r s t a g e s e c t i o n weighs an a d d i t i o n a l 8,081 pounds, The s t a g e 1s 5-2 engine burns l i q u i d oxygen and l i q u i d hydrogen, �The s t a g e provides propulsion t w l c e during t h e Apollo 10 mission, The first burn occurs e d i a t e l g after separat%on from the S-XI, It w i l l last long enough (156 seconds) to Znsert t h e v e h i c l e and s p a c r c r a f t i n t o a c i r c u l a r W r t h parking o r b i t a t about 52 degrees West longitude and 32 degrees North l a t i t u d e , The second bum, which begins a t 2 hours 33 minutes 25 seconds after l i f t o f f ( f o r first opportunity t r a n s l u n a r inj e c t i o n ) o r 4 hours 2 minutes 5 seconds ( f o r second TLI opport u n i t y ) , w i l l plaee t h e stage, instrument u n i t , and spacecraft i n t o t r a n s l u n a r t r a J e c t o r y . "The burn w i l l continue u n t i l proper "nI end conditions are m e t , The f u e l tanks contain 4?,452 pounds of l i q u i d hydrogen and 190,785 pounds of IiquLd oxygen a t first i g n i t i o n , totalling 234,237 pounds of propellants, I n s u l a t i o n between t h e two tanks i s necessary because t h e l i q u i d oxygen, a t about 293 degrees below zero I?, is warm enough, r e l a t i v e l y , t o heat t h e l i q u i d hydrogen, a t 423 degrees below zero F, r a p i d l y and cause i t t o t u r n I n t o gas. Instrument Unit The instrument u n i t (IN) i s a cylinder t h r e e f e e t high and 21 f e e t 8 inches i n diameter, It weighs 4,254 pounds and contains t h e guidance, navigation, and c o n t r o l equipment which w i l l s t e e r t h e vehicle through its Earth o r b i t s and i n t o t h e f i n a l t r a n s l u n a r i n j e c t i o n maneuver, The IU a l s o contains telemetry, communieations, tracking, and crew s a f e t y systems, along with i t s own supporting e l e c t r i c a l power and environmental c o n t r o l systems, Components making up the "brain" of t h e Saturn V are mounted on cooling panels fastened t o t h e i n s i d e surface of t h e instrument u n i t skin, The "cold p l a t e s " a r e p a r t of a system t h a t removes heat by c i r c u l a t i n g cooled fluid through a heat exchanger t h a t evaporates water from a separate s u p p l y i n t o t h e vacuum of space. The six maJor systems of the instrument u n i t a r e s t r u c t u r a l , thermal control, guidance and control, measuring and telemetry, r a d i o frequency, and e l e c t r i c a l . The instrument u n i t provides navigation, guidance, and c o n t r o l of t h e vehicle; measurement of vehicle performance and environment; data transmission with ground s t a t i o n s ; radio tracking of t h e vehicle; checkout and monitoring of vehicle functions; i n i t i a t i o n of stage functional sequencing; detection f o emergency s i t u a t i o n s ; generation and network d i s t r i b u t i o n of e l e c t r i c power system operation; and p r e f l i g h t checkout and launch and f l i g h t operations. �A path-adaptive guidance scheme i s used i n t h e Saturn A programmed t r a j e c t o r y i s used i n t h e V instrument u n i t . i n i t i a l launch phase with guidance beginning only a f t e r t h e v e h i c l e h a s l e f t t h e atmosphere. This i s t o prevent movements t h a t might cause t h e v e h i c l e t o break a p a r t while a t t e m p t i n g t o compensate f o r winds, J e t streams, and g u s t s encountered i n t h e atmosphere. If such a i r c u r r e n t s d i s p l a c e t h e v e h i c l e from t h e optimum t r a j e c t o r y i n climb, t h e v e h i c l e d e r i v e s a new traJ e c t o r y . C a l c u l a t i o n s are made about once each second througho u t t h e f l i g h t . The launch v e h i c l e d i g i t a l computer and d a t a a d a p t e r perform t h e n a v i g a t i o n and guidance computations. -- The ST-124M i n e r t i a l platform t h e h e a r t of t h e navigat i o n , guidance and c o n t r o l system -- provides space-fixed r e f e r e n c e c o o r d i n a t e s and measures a c c e l e r a t i o n a l o n g t h e t h r e e mutually perpendicular a x e s of t h e c o o r d i n a t e system. I n t e r n a t i o n a l Buuiness Machines Corp., i s prime c o n t r a c t o r f o r t h e instrument u n i t and i s t h e s u p p l i e r of t h e guidance s i g n a l processor and guidance computer. Major s u p p l i e r s of instrument u n i t components a r e : E l e c t r o n i c Communications, Inc., c o n t r o l computer; Bendix Corp., ST-124M i n e r t i a l platform; and IBM Federal Systems Division, launch v e h i c l e d i g i t a l comp u t e r and launch v e h i c l e data a d a p t e r . Propulsion The 4 1 r o c k e t engines of t h e S a t u r n V have t h r u s t r a t i n g s ranging from 72 pounds t o more t h a n 1.5 m i l l i o n pounds. Some e w i n e s burn l i q u i d p r o p e l l a n t s , o t h e r s use s o l i d s . The f i v e F-1 engines i n t h e f i r s t s t a g e burn RP-1 (kerosene) and l i q u i d oxygen. Fngfnes i n t h e f i r s t s t a g e develop approximately 1,536,197 pounds of t h r u s t each a t l i f t o f f , b u i l d i n g up t o 1,822,987 pounds b e f o r e c u t o f f . The c l u s t e r of f i v e engines g i v e s t h e first s t a g e a t h r u s t range from 7,680,982 m i l l i o n pounds a t l i f t o f f t o 9,114,934 pounds just b e f o r e c e n t e r engine c u t o f f . The F-1 engine w e i ~ h salmost 10 t o n s , i s more t h a n 18 f e e t h i a h and has a n o z z l e - e x i t diameter of n e a r l y 14 f e e t . The F-1 undergoes s t a t i c t e s t i n g f o r a n average 650 seconds i n q u a l i f y i n g f o r t h e 160-second run d u r i n g t h e S a t u r n V f i r s t s t a g e b o o s t e r phase. The engine consumes almost t h r e e t o n s of p r o p e l l a n t s p e r second. �The first stage of t h e Saturn V f o r t h i s mission h a s e i g h t other rocket motors, These are t h e s o l i d - f u e l r e t r o rockets which w i l l slow and separate t h e s t a g e from t h e second stage, Each rocket produces a t h r u s t of 87,900 pounds f o r 0.6 second. The main propulsion f o r t h e seaend stage i s a c l u s t e r of f i v e 3-2 engines burning l i q u i d hydrogen and l i q u i d oxygen, Each engine develops a mean t h r u s t of more than 205,000 pounds a t 5,0:1 mixture r a t i o ( v a r i a b l e from 184,000 t o 230,000 i n pbases of f l i g h t ) , giving t h e stage a t o t a l mean t h r u s t of more than a m i l l i o n pounds. Designed t o operate i n t h e hard vacuum of space, t h e 3,500-pound 5-2 i s mere e f f i c i e n t than t h e F-1 because it burns t h e high-energy f u e l hydrogen. F-1 and 5-2 engines are produced by t h e Rocketdyne Division of North American Roekwell Corp . The second s t a g e has f o u r 21,000-pound-thrust s o l i d f u e l rocket engines. These a r e t h e u l l a g e rockets mounted on t h e S-IC/S-11 i n t e r s t a g e section, These rockets f i r e t o s e t t l e l i q u i d propellant i n t h e bottom of the main tanks and help a t t a i n a "clearn" separation from t h e first stage, they remain with t h e I n t e r s t a g e when it drops away a t second plane separation. Four retrorockets are located I n t h e S-IVB a f t i n t e r s t a g e (which never separates from the S-11) t o separate t h e S-I1 f r m the S-IVB p r i o r t o S-TVB i g n i t i o n . Eleven rocket engines perform various functions on t h e t h i r d stage. A s i n g l e 5-2 provides t h e main propulsive force; t h e r e a r e two J e t t i s o n a b l e main u l l a g e rockets and e i g h t smaller engines i n t h e two a u x i l i a r y propulsion system modules. Launch Vehicle Instrumentation and Comrnunloation A t o t a l of 2,342 measurements w i l l be taken I n f l i t on t h e Saturn V launch vehicle: 672 on the first stage, 9 6 on '?f the second stage, 386 o n t h e t h i r d stage, and 298 on t h e i n s t r u ment u n i t . The Saturn V has 16 telemetry systems: six on t h e first stage, s i x on t h e second stage, one on the t h i r d stage and t h r e e on the instmment u n i t . A C-band system and command system are a l s o on t h e instrument u n i t , Each powered stage has a range s a f e t y system a s on previous f l i g h t s , �S-IVB R e s t a r t The t h i r d s t a g e of t h e Saturn V rocket f o r t h e Apollo 10 mission w i l l burn t w i c e i n apace, The second b u m places t h e spacecraft on t h e t r a n s l u n a r t r a j e c t o r y , =Thefirst opportunity f o r t h i s burn is a t 2 hours 33 minutes and 25 seconds after JLauach,, The second opportunity f o r TLI begins a t 4 hours 2 minutes and 5 seconds after l i f t o f f , The primary p r e s s u r i z a t i o n system of the propellant tanks f o r t h e 5-nr13 restart uses a helium heater, I n t h i s sytem, nine helium storage spheres i n t h e l i q u i d hydrogen tank contain gaseous helium charged t o about 3,000 p s i , This h e f h m is passed through t h e h e a t e r wh%chh e a t s and expands t h e gas before it e n t e r s t h e propellant tanks, The h e a t e r operates on hydrogen and oxygen gas from t h e main propellant tanks, The backup system c o n s i s t s of f i v e ambient helium spheres mounted on t h e s t a g e t h r u s t s t r u c t u r e . This system, controlled by t h e f u e l repressurization c o n t r o l module, can repressurize %he tanks i n case t h e primary system fails, !Phe r e s t a r t w i l l use t h e primary system. If t h a t system fails, t h e backup system w i l l be used. The t h i r d stage f o r Apollo 10 w i l l not be Ignited f o r a t h i r d burn a s on Apollo 9, Following spacecraft separation i n t r a n s l u n a r t r a j e c t o r y , the s t a g e w i l l undergo the normal 5-2 engine chilldown sequence, stopping j u s t short of r e i g n i t i o n , On Apollo 10 t h e r e i s no requirement f o r a t h i r d burn, and t h e r e w i l l not be s u f f i c i e n t propellants aboard, most of t h e f u e l s having been expended during the tranalunar i n j e c t i o n maneuver, Differences i n Apollo 9 and Apollo 10 Launch vehicles Two modifications r e s u l t i n g from problems encountered during the second Saturn V f l i g h t were incorporated and proven successful an t h e t h i r d and f o u r t h Saturn V missions. The new helium prevalve c a v i t y pressurization system w i l l again be flown on the first (s-IC) stage of Apollo 10, New augmented spark I g n i t e r l i n e s which f l e w on t h e engines of t h e two upper s t a g e s of Apollo 8 and 9 w i l l again be used on Apollo 10, �The major first s t a g e (s-IC) d i f f e r e n c e s between Apollo 9 and 10 a r e : 1. pounds, Dry weight was reduced from 295,600 t o 294,200 2. Weight a t ground i g n i t i o n increased from 5,026,200 t o 5,031,023 pounds. 3. Instrumentation measurements were increased from 666 t o 672. S-I1 s t a g e changes a r e : 1. Nominal vacuum t h r u s t f o r 5-2 engines i n c r e a s e w i l l change maximum s t a g e t h r u s t from 1,150,000 t o 1,168,694 pounds. 2. The approximate empty weight of t h e S-I1 has been reduced from 84,600 t o 84,367 pounds. The S-IC/S-11 i n t e r stage weight was reduced from 11,664 t o 8,890 pounds. 3. Approximate s t a g e g r o s s l i f t o f f weight was increased from 1,069,114 t o 1,074,590 pounds. 4. to 986. 975 Instrumentation measurements increased i ~ m Major d i f f e r e n c e s on t h e S-IVB s t a g e of Apollo 9 and 10 a r e : S - N B dry s t a g e weight increased from 25,300 t o T h i s does n o t include t h e 8,084-pound i n t e r stage section. 1. 25,750 pounds. 2. S-NB 8r o s s s t a g e weight a t l i f t o f f increased from 259,337 t o 261, 36 pounds. 3. Instrumentation measurements were increased from 296 t o 386. �APOLLO 10 CREW L i f e Support muipment - Space S u i t s Apollo 10 crewmen w i l l wear two versions of t h e Apollo space s u i t : an i n t r a v e h i c u l a r p r e s s u r e garment assembly worn by t h e command module p i l o t and t h e e x t r a v e h i c u l a r press u r e garment assembly worn by the commander and the lunar module p i l o t , Both versions a r e b a s i c a l l y i d e n t i c a l except t h a t t h e e x t r a v e h i c u l a r version has an i n t e g r a l thermal/ meteoroid garment over the b a s i c s u i t . From the s k i n o u t , the b a s i c pressure garment c o n s i s t s of a nomex comfort l a y e r , a neoprene-coated nylon pressure bladder and a nylon r e s t r a i n t l a y e r , The o u t e r l a y e r s of t h e i n t r a v e h i c u l a r s u i t a r e , from t h e inside o u t , nomex and two l a y e r s of Tef lon-coated Beta c l o t h . The e x t r a v e h i c u l a r i n t e g r a l thermal/meteoroid cover c o n s i s t s o f a l i n e r o f two l a y e r s of neoprene-coated nylon, seven l a y e r s o f ~ e t a / K a p t o nspacer laminate, and an o u t e r l a y e r o f Teflon-coated Beta f a b r i c . The e x t r a v e h i c u l a r s u i t , t o g e t h e r with a l i q u i d cooling garment, p o r t a b l e l i f e support system (PLsS), oxygen purge system, e x t r a v e h i c u l a r v i s o r assembly and o t h e r components make up t h e e x t r a v e h i c u l a r m o b i l i t y u n i t (EMU). The EMD provides an e x t r a v e h i c u l a r crewman with l i f e support f o r a , f o u r hour mission o u t s i d e t h e l u n a r module without r e p l e n i s h i n g expendables. EPlIZ t o t a l weight i s 183 pounds. The i n t r a vehicular suit weighs 35.6 pounds. Liquid cooling garment--A k n i t t e d nylon-spandex garment w i t h a network of p l a s t i c tubing through which cooling watelr from the PLSS i s c i r c u l a t e d . It i s worn next t o the s k i n and r e p l a c e s t h e constant wear-garment during EVA only. Portable l i f e support system--A backpack supplying oxygen a t 3.9 p s i and cooling water t o t h e l i q u i d cooling garment. Return oxygen i s cleansed o f s o l i d and gas contaminants by a l i t h i u m hydroxide canister. The PLSS i n c l u d e s communications and telemetry equipment, d i s p l a y s and c o n t r o l s , and a main power supply. The PLSS i s covered by a thermal i n s u l a t i o n Jacket. (one stowed i n LM). Oxygen purge sys tern--Mounted a t o p t h e PLSS, the oxygen purge system provides a contingency 30-minute supply of gaseous oxygen i n two two-pound b o t t l e s p r e s s u r i z e d t o 5,880 p s i a . The system may a l s o be worn s e p a r a t e l y on the f r o n t of t h e pressure garment assembly t o r s o , It serves as a mount f o r t h e VHF antenna f o r the PLSS. (Two stowed i n LM) . ��HOLD DOWN STRAP ACCESS FLAP L U V Y lAPt SHOULDER DISCONNECT \ CONNECTOR COVER CHEST COVER SUNG LASSES +--SHELL -+iNSUlATION +-LINER PENLIGHT POCKET TYPICAL CROSS SECTION LM RESTRAINT BELT ASSEMBLY LITY POCKET SLlDE FASTENER DATA LIST POCKET WRIST CLAMP ASSIST STRAP URINE TRANSFER CONNECTOR AND BIOMEDICAL INJECTION P ! LOOP TAPE L U U P IAPE ACTIVE DOSIMETER POCKET ENTRANCE SLIDE FASTENER FLAP a ------I/, '\I , L ASSISTS SCISSORS POCKET CHECKLIST POCKET �-56~- BACKPACK SUPPORT STRAPS OXYGEN PURGE SYST CKPACK CONTROL BOX SYSTEM ACTUATOR PENLIGHT POCKET CONNECTOR COVER COMMUNICATION, VENT1 LATI ON, AND LIQUI D COOLING PURGE SYSTEM LM RESTRA lNT R ING INTEGRATED THERMAL METEOR0 I D GARMENT UR INE TRANSFER CONNECTOR, DOS IMETER ACCESS FLAP AND DONN I NG LANYARD POCKET UTILITY POCKET �Extravehicular v i s o r assembly--A polycarbonate s h e l l and two v i s o r s with thermal c o n t r o l and o p t i c a l coatings on them, The EVA v i s o r i s attached over t h e pressure helmet t o provide impact, micrometeoroid, thermal and l i g h t protection t o t h e EVA crewman. Extravehicular gloves--Built of an o u t e r s h e l l of Chromel-R f a b r i c and thermal i n s u l a t i o n t o provide protect i o n when handling extremely hot and cold o b j e c t s , he f i n g e r t i p s a r e made of s i l i c o n e rubber t o provide the crewman more sensitivity. A one -piece cons tan%-wear garment, similar t o " long johns", is worn as an undergarment f o r the space suit in i n t r a vehicular operations and f o r the i n f l i g h t coveralls. The garment 5s porous-knit cotton with a waist-to-neck zipper f o r doming. Biomedical harness a t t a c h points are provided. During periods out of the space s u i t s , crewmen w i l l wear two-piece Teflon f a b r i c i n f l i g h t c o v e r a l l s f o r warmth and f o r pocket stowage of personal items. Communications c a r r i e r s ( " ~ n o o p yh a t s " ) with redundant microphones and earphones a r e worn w i t h the pressure helmet; a lightweight headset i s worn with the i n f l i g h t coveralls, Meals The Apollo 10 crew has a wide Pange of food items from which t o s e l e c t t h e i r d a i l y mission space menu, More than 60 items comprise the food s e l e c t i o n l i s t of freeze-dried rehydratable foods. I n addition, one "wet pack" meal-per-man per-day w i l l be stowed f o r a t o t a l of 27. These meals, cons i s t i n g of foil-wrapped beef and potatoes, ham and potatoes and turkey chunks and gravy, a r e s i m i l a r t o the Christmas meals c a r r i e d aboard Apollo 8 and can be eaten with a spoon. Water f o r drinking and rehydrating food is obtained from three sources i n the command module a dispenser f o r drinking water and two water spigots a t the food preparation s t a t i o n , one supplying water a t about 155 degrees F., the other a t about 55 degrees F, The potable water dispenser s q u i r t s water continuously as long a s the t r i g g e r i s held down, and the food preparation s p i g o t s dispense water i n one-ounce increments. -- �Command module potable water i s supplied from s e r v i c e module f u e l ce 11 byproduct water, Three one - p i n t " p i c n i c Jugs", o r p l a s t i c bags, w i l l be stowed aboard Apollo 10 f o r drinking water, Each crewman once a day w i l l f i l l a bag with water and then s p i n it up t o s e p a r a t e t h e suspended hydrogen gas from t h e water so t h a t he w i l l have hydrogenl e s s water t o d r i n k t h e following day. The suspended hydrogen i n t h e f u e l c e l l byproduct water has caused i n t e s t i n a l d i e comfort t o crewmen i n previous Apollo missions. A continuous-feed hand water dispenser similar t o t h e one i n the command module i s used aboard the l u n a r module f o r cold-water rehydration of food packets stowed aboard t h e M. A f t e r water has been i n j e c t e d i n t o a food bag, it is kneaded f o r about t h r e e minutes, TZle bag neck i s then c u t o f f and t h e food squeezed i n t o t h e crewman's mouth. A f t e r a meal, germicide p i l l s attached t o t h e o u t s i d e of the. food bags a r e placed i n the bags t o prevent fermentation and gas formation. The bags a r e then r o l l e d and stowed i n waste d i s p o s a l compartments, The day-by-day, meal-by-meal Apollo 10 menu f o r each crewman f o r both t h e command module and the l u n a r module i s l i s t e d on t h e following pages. �MEAL Day 2, 6, 1 0 Day I*, 5, 9 A Peaches Bacon Squares (8) Cinn Tstd Bread Cubes (4) Grapefruit Drink Orange Drink F r u i t Cocktail Sugar Coated Corn Flakes Bacon Squares (8) Grapefruit Drink Grape Drink B Salmon Salad Chicken & Rice** Sugar Cookie Cubes (4) Cocoa Grape Punch P o t a t o Soup Chicken & Vegetables Tuna Salad Pineapple Fruitcake (4) Orange Drink S (D I Day 3, 7, 11 Peaches Bacon Squares (8) Strawberry Cubes (4) Cocoa Orange Drink Cream of Chicken Soup (Turkey & Gravy Wet Pack) Butterscotch Pudding Brownies ( 4 ) G r a p e f r u i t Drink - F r u i t Cocktail Sausage P a t t i e s Bacon Squares (8) Cocoa Grape Drink P o t a t o Soup Pork & Scalloped P o t a t o a Applesauce Orange Drink & \O I C - (Beef & Potatoes Wet pack) Cheese Cracker Cubes (4) Chocolate Pudding Grange-Grapefruit Drink *Day 1 c o n s i s t s of Meal C only **Nev spoon-bowl package Spaghetti & Meat Sauce** (Ham & Potatoes Wet pack) Banana Pudding Pineapple-Grapefruit Drink - Pea Soup Beef StewY* Chicken Salad Chocolate Cubes (4) Grape Punch Shrimp Cocktail Chicken Stew** Turkey B i t e s (4) Date Fruitcake ( 4 ) Orange-Grapefruit Drink �APOLLO 10 (YOUNG) MEAL Day l*,5 , 9 Day 2, 6, 10 A Peaches Bacon Squares (8) Cinn Tstd Bread Cubes ( 4 ) Grapefruit' Drink Orange Drink F r u i t Cocktail Sugar Coated Corn Flakes Brownies ( 4 ) Grapefruit Drink Grape Drink B Salmon Salad Chicken & Rice** Sugar Cookie Cubes (4) Cocoa Grape Punch Potato Soup Tuna Salad Chicken & Vegetables Pineapple Fruitcake ( 4 ) Pineapple-Grapefruit Drink '3 CD I C - (Beef & Potatoes Wet pack) Cheese Cracker Cubes ( 4 ) Chocolate Pudding Orange-Grapefruit Drink *T)sy 1 c o n s i s t s o f Meal C: only **Nev spoon-Sow1 psckage S p a g h e t t i & Meat SauceY* (Ham & P o t a t o e s Wet pack) Banana Pudding Grange Drink - Day 3, 7, 11 Peaches Bacon Squares (8) Strawberry Cubes ( 4 ) Cocoa Orange Drink Cream of Chicken Soup (Turkey & Gravy - Wet Pack) Butterscotch Pudding Grapefruit Drink Beef StewY* Chicken Salad Corn Chowder Chocolate Cubes ( 4 ) Grape Punch F r u i t Cocktail Sausage P a t t i e s Bacon Squares (8) Cocoa Grape Drink Pea Soup Pork & Scalloped P c t s t o e s Applesauce Orange D r i n k Shrimp Cocktail Chicken Stew** Turkey Bites ( 4 ) Date Fruitcake (4) Orange-Grapef r u i t Drink �MEAL Uay l * , 5, 9 Day 2, 6, 1 0 A Peaches Bacon Squares (8) Cinn T s t d Bread Cubes (4) Orange Drink Orange-Pineapple Drink F r u i t Cocktail Sugar Coated Corn F l a k e s Bacon Squares (8) Orange Drink Grape Drink B Salmon S a l a d Chicken & Rice** Sugar Cookie Cubes ( 4 ) Cocoa Grape Punch P o t a t o Soup Tuna Salad Chicken & Vegetables Brownies (4) Orange-Grapefruit Drink Day 3, 7, 11 Peaches Bacon Squares (8) Strawberry Cubes ( 4 ) Cocoa Orange Drink Cream of Chicken Soup (Turkey & Gravy Wet pack) Cinn T s t d Bread Cubes ( L ) B u t t e r s c o t c h Pudding Pineapple-Grapefrui t Drink - Day 4, 8 F m i t Cocktail Sausage P a t t i e s Bacon Squares (8) Cocoa Grape Drink P o t a t o Soup Pork & Scalloped P o t a t o e s Applesauce Orange Drink Y I ui I-' I C Cream of Chicken Soup Wet pack) (Beef & P o t a t o e s Cheese Cracker Cubes ( 4 ) F r u i t Cocktail Orange-Grapefruit Drink - *Day 1 c o n s i s t s of Meal C only **New spoor-'mwl package S p a g h e t t i & Meat Sauce** (Ham & P o t a t o e s Wet pack) Banana Pudding Orange Drink - Pea Soup Chicken S a l a d Beef Stew** Grape Punch Shrimp C o c k t a i l Chicken Stew** Turkey B i t e s (6) Chocolate Cubes (6) Orange-Grapefruit Drink �-62- APOLLX) 10 ZM MENU Meal A F m it Cocktail Bacon Squares ( 8 ) Brownies ( 4 ) Orange Drink Grape Punch Meal I3 Beef and Vegetables Pineapple F r u i t c a k e (4) Orange-Grapefruit Drink Grape Punch Meal C Cream o f Chicken Soup Beef Hash Strawberry Cubes (4) Pineapple-Grapefruit ."I Drink 2 man-days only L meals p e r overwrap Red and Blue Velcro �Personal Hygiene Crew personal hygiene equipment aboard Apollo 10 i n cludes body c l e a n l i n e s s items, t h e waste management system and one medical k i t . Packaged with t h e food a r e a toothbrush and a two-ounce tube of t o o t h p a s t e f o r each crewman. Each man-meal package contains a 3.5-by-four-Inch wet-wipe cleansing towel. Additionally, t h r e e packages of 12-by-12-Inch dry towels ape stowed beneath t h e command module p i l o t ' s couch. Each package c o n t a i n s seven towels. Also stowed under t h e command module p i l o t ' s couch a r e seven t i s s u e d i s p e n s e r s containing 53 t h r e e p l y t i s s u e s each. S o l i d body wastes are c o l l e c t e d i n Gemini-type p l a s t i c d e f e c a t i o n bags which contain a germicide t o prevent b a c t e r i a and gas formation. The bags a r e sealed a f t e r use and stowed i n empty food c o n t a i n e r s f o r p o s t - f l i g h t a n a l y s i s . Urine c o l l e c t i o n devices a r e provided f o r use while wearing e i t h e r the pressure s u i t o r the f n f l i g h t c o v e r a l l s . The u r i n e i s dumped overboard through t h e s p a c e c r a f t u r i n e dump valve i n the CM and s t o r e d i n t h e LM. The 5 x 5 ~ 8 - i n c hmedical accessory k i t i s stowed i n a cornpartment on t h e s p a c e c r a f t r i g h t s i d e w a l l beside t h e lunar module p i l o t couch. The medical k i t c o n t a i n s t h r e e motion sickness i n j e c t o r s , t h r e e pain suppression i n J e c t o r s , one twoounce b o t t l e f i r s t a i d ointment, two one-ounce b o t t l e eye drops, t h r e e n a s a l sprays, two compress bandages, 12 adhesive bandages, one o r a l thermometer and two s p a r e crew biomedical harnesses. P i l l s i n t h e medical k i t a r e 60 a n t i b i o t i c , 12 nausea, 12 s t i m u l a n t , 18 pain k i l l e r , 60 decongestant, 24 d i a r r h e a , 72 a s p i r i n and 2 1 sleeping. Additionally, a small medical k i t containing four stimulant, e i g h t d i a r r h e a , two s l e e p i n g and four pain k i l l e r p i l l s , 12 a s p i r i n , one b o t t l e eye drops and two compress bandages i s stowed i n t h e lunar module f l i g h t d a t a f i l e compartment. Survival Gear The s u r v l v a l k i t i s stowed i n two rucksacks in the r i g h t hand forward equipment bay above t h e lunar module p i l o t . Contents of rucksack No. 1 are: two combination s u r v i v a l l i g h t s , one d e s a l t e r k i t , t h r e e p a i r sunglasses, one r a d i o beacon, one spare r a d i o beacon b a t t e r y and s p a c e c r a f t connector cable, one k n i f e i n sheath, t h r e e water c o n t a i n e r s and two cont a i n e r s of Sun l o t i o n . ��Rucksack No. 2: one three-man l i f e raft with CO i n f l a t e r , one sea anchor, two s e a dye markers, t h r e e unbonnets, one mooring lanyard, t h r e e manllnes, and two a t t a c h brackets. 5 The s u r v i v a l k i t is designed t o provide a 48-hour postlanding (water o r land) s u r v i v a l c a p a b i l i t y f o r t h r e e crewmen between 40 degrees North and South l a t i t u d e s . Biomedical I n f l i g h t Monitorin4 The Apollo 10 crew biomedical telemetry d a t a received by the Manned Space F l i g h t Network w i l l be relayed f o r Instantaneous d i s p l a y a t Mission Control Center where h e a r t r a t e and breathing r a t e d a t a w i l l be displayed on the f l i g h t surgeon's console. Heart r a t e and r e s p i r a t i o n rate average, range and d e v i a t i o n a r e computed and displayed on d i g i t a l TV screens. I n a d d i t i o n , t h e instantaneous h e a r t r a t e , real-time and delayed EXG and r e s p i r a t i o n a r e recorded on s t r i p c h a r t s f o r each man. Biomedical telemetry w i l l be simultaneous from a l l crewmen while i n the CSM, but s e l e c t a b l e by a manual onboard switch i n the LM. Biomedical data observed by t h e f l i g h t surgeon and h i s team i n the L i f e Support Systems S t a f f Support Room w i l l be c o r r e l a t e d wlth s p a c e c r a f t and space s u i t environmental data displays. Blood pressures a r e no longer telemetered as they were i n the Mercury and Gemini programs. Oral temperature, however, can be measured onboard f o r d i a g n o s t i c purposes and voiced down by the crew In case o f i n f l i g h t i l l n e s s . Rest-Work Cycles A l l t h r e e Apollo 10 crewmen w i l l s l e e p simultaneously during r e s t periods. The average mission day w i l l c o n s i s t of 16 hours of work and e i g h t hours of r e s t . Two crewmen normally w i l l s l e e p i n t h e s l e e p s t a t i o n s ( s l e e p i n g bags) under t h e couches, w i t h t h e t h i r d man i n the couch. During r e s t periods, one crewman w i l l wear h i s communications headset. The only exception t o t h i s s l e e p i n g arrangement w i l l be during the r e s t period on lunar o r b i t i n s e r t i o n day, when two crewmen w i l l s l e e p i n the couches s i n c e the docking probe and drogue assemblies w i l l be stowed i n one o f t h e s l e e p s t a t i o n s . When poss'ible, a l l t h r e e crewmen w i l l e a t together i n onehour e a t p e r i o d s during which o t h e r a c t i v i t i e s w i l l be held t o a minimum. �The crewmen of Apollo 10 have spenlt; more than f i v e hours of forrnal crew t r a i n i n g f o r each hour of t h e l u n a r - o r b i t missiont s e i g h t -day d u r a t i o n . Almost 1,000 hours of t r a i n i n g were i n the Apollo 10 crew t r a i n i n g s y l l a b u s over and above t h e normal p r e p a r a t i o n s f o r the mission--technical b r i e f i n g s and reviews, p i l o t meetings and study. The Apollo 10 crewmen also took p a r t i n s p a c e c r a f t manuf a c t u r i n g checkouts a t the Nosrth American Rockwell p l a n t i n Downey , C a l i f . , a t Orumman A i r c r a f t Engineering Gorp,, Bethpaga, N.Y., and i n prelaunch t e s t i n g a t NASA Kennedy Space Center. Taking p a r t i n f a c t o r y and launch a r e a t e s t i n g has provided t h e crew with thorough o p e r a t i o n a l knowledge of the complex vehicle. Highlights of s p e c i a l i z e d ApoPlo 10 crew t r a i n i n g t o p i c s are: * Detailed s e r i e s of b r i e f i n g s on s p a c e c r a f t systems, operation and modifications. * Saturn launch vehicle b r i e f i n g s on countdown, range s a f e t y , f l i g h t dynamics, f a i l u r e modes and a b o r t conditions. The launch vehicle b r i e f i n g s were updated p e r l o d e a l l y . * Apollo ouidance and Navigation system b r i e f i n g s a t the Massachusetts I n s t i t u t e of Technology I n s t e n t a t i o n Laboratory. * B r i e f i n g s and continuous t r a i n i n g on mission photographic o b j e c t i v e s and use of camera equipment. * Extensive p i l o t p a r t i c i p a t i o n i n reviews of a l l f l i g h t procedures f o r normal as well as emergency s i t u a t i o n s . * Stowage reviews and p r a c t i c e i n t r a i n i n g s e s s i o n s i n t h e s p a c e c r a f t , mockups and command module simulators allowed t h e crewmen t o evaluate s p a c e c r a f t stowage of crew-associated equipment. * More than 300 hours of t r a i n i n g p e r man i n command module and lunar module simulators a t NSC and KSC, including cloeedloop simulations with f l i g h t c o n t r o l l e r s i n t h e Mission Control Center. Other Apollo simulators a t various l o c a t i o n s were used e x t e n s i v e l y f o r s p e c i a l i z e d crew t r a i n i n g . * Entry c o r r i d o r d e c e l e r a t i o n p r o f i l e s a t lunar-return conditions i n t h e MSC F l i g h t Acceleration F a c i l i t y manned centrifuge, �* Zero-g a i r c r a f t f l i g h t s using command module and lunar module mockups f o r EVA and pressure s u i t doffing/donning p r a c t i c e and t r a i n i n g . * Underwater zero-g t r a i n i n g i n the MSC Water Immersion F a c i l i t y using spacecraft mockups t o f a m i l i a r i z e f u r t h e r crew with a l l a s p e c t s of CSM-LM docking tunnel i n t r a v e h i c u l a r t r a n s f e r and GVA i n pressurized s u i t s . * Water e g r e s s t r a i n i n g conducted i n indoor tanks a s well as i n t h e Gulf of Mexico included uprighting from the Stable I1 p a a i t i o n (apex downj t o the S t a b l e I p o s i t i o n (apex up), egress onto r a f t s and h e l i c o p t e r pickup. * Launch pad egress t r a i n i n g from mockups and from the a c t u a l s p a c e c r a f t on the launch pad f o r possible emergencies such as f i r e , contaminants and power f a i l u r e s . + The t r a i n i n g covered use of Apollo s p a c e c r a f t f i r e suppress ion equipment i n t h e cockpit. * Planetarium reviews a t Morehead Planetarium, Chapel and a t G r i f f i t h Planetarium, Los Angeles, Calif., of t h e c e l e s t i a l sphere with s p e c i a l emphasis on the 37 navigational s t a r s used by t h e Apollo guidance computer. H i l l , N.C., �Crew Biographies NAME: Thomas P. S t a f f o r d ( c o l o n e l , USAF) Apollo 10 commander NASA Astronaut BIRTHPLACE AND DATE: Born September 17, 1930, i n Weatherford, Okla., where h i s mother, Mrs. Mary E l l e n S t a f f o r d , now resides. PHYSICAL DESCRIPTION: Black h a i r , blue eyes; height: weight: 175 pounds. 6 feet; EDUCATION: Qraudated from Weatherford High School, Weatherford, Okla.; received a Bachelor of Science degree from the United S t a t e s Naval Academy i n 1952; r e c i p i e n t of an Honorary Doctorate of Science from Oklahoma C i t y U n i v e r s i t y i n 1967. MARITAL STATUS: Married t o t h e former Faye L. Shoemaker of Weatherford, Okla. H e r p a r e n t s , M r . and Mrs. E a r l e R. Shoemaker, r e s i d e i n Thomas, Okla. CHILDREN: Dionne, July 2, 1954; Karin, Aug. 28, 1957. H i s hobbies include handball, weight l i f t i n g and swimming. OTHER ACTIVITIES: ORGANIZATIONS: Pilots. Member of t h e S o c i e t y o f Experimental Test SPECIAL HONORS: Awarded two NASA Exceptional Service Medals and t h e A i r Force Astronaut Wings; t h e Distinguished Flying Cross; the A I A A A s t r o n a u t i c s Award; and co-rec i p i e n t of t h e 1966 Harmon I n t e r n a t i o n a l Aviation Trophy. EXPERIENCE: Staffo.rd, an A i r Force c o l o n e l , was colnmissioned i n i n t h e United S t a t e s A i r Force upon graduation from Annapolis. Following h i s f l i g h t t r a i n i n g , he flew f i g h t e r i n t e r c e p t o r a i r c r a f t i n t h e United S t a t e s and Germany and l a t e r a t t e n d e d t h e USAF m p e r i m e n t a l F l i g h t T e s t School a t Edwards A i r Force Base, C a l i f . H e served as Chief of t h e Performance Branch a t t h e USAP Aerospace Research P i l o t School a t Edwards and was res p o n s i b l e f o r t h e s u p e r v i s i o n and a d m i n i s t r a t i o n o f t h e f l y i n g curriculum f o r s t u d e n t test p i l o t s . H e was also an i n s t r u c t o r i n f l i g h t test t r a i n i n g and s p e c i a l i z e d academic s u b j e c t s - - e s t a b l i s h i n g b a s i c textbooks and d i r e c t i n g t h e w r l t i n g o f f l i g h t t e s t manuals f o r use by t h e s t a f f and s t u d e n t s . He i s co-author o f t h e P i l o t ' s Handbook for Performance F l i g h t T e s t i n g and t h e Asrodynamics Handbook f o r Performance F l i g h t Testing, - �H e has accumulated over 5,000 hours f l y i n g t b e , of which over 4,000 hours are i n jet a i r c r a f t . Colonel S t a f f o r d was s e l e c t e d as an a s t r o n a u t by NASA i n September 1962. H e has s i n c e served as backup p i l o t f o r the Gemini 3 f l i g h t . CURRENT ASSIGNMENT: On Dec. 15, 1965, he and command p i l o t Walter M. S c h i r r a were launched i n t o space on the history-making Qemini 6 mission and subsequently p a r t i c i p a t e d i n the f i r s t s u c c e s s f u l rendezvous of two manned maneuverable spacec r a f t by joining the a l r e a d y o r b i t i n Gemini 7 crew. Gemini 6 returned t o Earth on k c . 1 , 1965, a f t e r 25 hours 51 minutes and 24 seconds of f l i g h t . ti He made h i s second f l i g h t as command p i l o t o f t h e Gemini 9 mission. During t h i s 3-day f l i g h t which began on June 3, 1966, the s p a c e c r a f t a t t a i n e d a c i r c u l a r o r b i t of 161 s t a t u t e m i l e s ; t h e crew performed t h r e e d i f f e r e n t types of rendezvous with the previously launched Augmented Target Docking Adapter; and p i l o t Eugene Cernan logged two hours and t e n minutes o u t s i d e t h e s p a c e c r a f t i n e x t r a v e h i c u l a r a c t i v i t y . The f l i g h t ended a f t e r 72 hours and 20 minutes with a p e r f e c t r e e n t r y and recovery as Gemini 9 landed within 0.4 naukical m i l e s of t h e des i g n a t e d t a r g e t point and 13 miles from the prlme recovery s h i p , USS WASP. �NAm: John W. Young(Commander, USN) pilot NASA Astronaut Apollo 10 conrmand module BIRTHPLACE AND DATE: Born i n San Francisco, C a l i f . , on Sept. 24, 1930. H i s parents, M r . and Mrs. W i l l i a m 8 . Young, r e s i d e i n Orlando, Fla. PHYSICAL DESCRIPTION: Brown h a i r ; green eyes; height: 9 inches; weight: 165 pounds. 5 feet . Qraudated from Orlando High School, Orlando, Fla ; received a Bachelor o f Science degree i n Aeronautical Engineering from the Georgia I n s t i t u t e of Technology i n 1952* EIXJCATION: MARITAL STAWS: Married t o the former Barbara V. White of Savannah, Ga, Her parents, M r . and Mrs. Robert A . White, r e s i d e i n Jacksonville, Fla. CHILDREN: Sandy, Apr. 30, 1957; John, Jan. 17, 1959. OTHER ACTIVITIES: H i s hobbles a r e bicycle r i d i n g and handball. ORGAMIZATIONS: Member of the American I n s t i t u t e of Aeronautics and Astronautics and the Society of Experimental Test Pilots. SPECIAL HONORS: Awarded two NASA Exceptional Service Medals, t h e Navy Astronaut Wings, and three Distinguished Flying Crosses. EXPWIENCE: Upon graduation from Georgia Tech, Young entered t h e U,S, Navy i n 1952 and holds t h e rank of commander. He was a t e s t p i l o t a t t h e Naval A i r Test Center from 1959 t o 1962. Test p r o j e c t s included evaluations of t h e F8D and F4B f i g h t e r weapons systems. I n 1962, he set world time-to-climb records t o 3,000 and 25,000-meter a l t i t u d e s i n the F4B. P r i o r to h i s assignment t o NASA he was k i n t e n a n c e O f f i c e r of All-Weather -Fighter Squadron 143 a t t h e Naval A i r S t a t i o n , M i r a m a r , C a l i f . H e has logged more than 4,500 hours f l y i n g time, including more than 3,900 hours i n j e t a i r c r a f t . �CURRENT ASSIGNMENT: Commander Poumze; was s e l e c t e d as an a s t r o naut by NASA in September 1962. H e served as p i l o t on t h e first manned G e m i n i f l i g h t - - a 3 - o r b i t mission, launched on March 23, 1965, during which t h e crew accomplished t h e first manned s p a c e c r a f t o r b i t a l t r a j e c t o r y modifications and l i f t i n g r e e n t r y , and f l i g h t t e s t e d all systems i n G e m i n i 3. After t h f a assignment, he was backup p i l o t f o r Gemini 6. 18, 1966, Young occupied t h e co&d p i l o t seat f o r t h e Gemini 10 mission and, with Michael C o l l i n s as p i l o t , e f f e c t e d a successf'ul rendezvous and docking with t h e Agena target vehicle. men, they i g n i t e d t h e large Agena main engine t o propel t h e docked combination t o a record a l t i t u d e of approximately 475 miles above t h e Earth--the first manned operation o f a large r o c k e t engine i n space. They later performed a completely o p t i c a l rendezvous (without r a d a r ) on a second passive Agena. A f t e r t h e rendezvous, while Young f l e w formation on t h e passive Agena, C o l l i n s performed e x t r a v e h i c u l a r a c t i v i t y t o it and recovered a micrometeorite d e t e c t i o n experiment, accomplfahing an In-space r e t r i e v a l of t h e d e t e c t o r t h a t had been o r b i t i n g the Earth f o r t h r e e months. On July The f l i g h t was concluded a f t e r 3 days and 44 revolutions-during which Gemini 10 t r a v e l e d a t o t a l d i s t a n c e of 1,275, 091 s t a t u t e miles. Splashdown occurred in the West A t l a n t i c , 529 s t a t u t e miles e a s t of' Cape Kennedy, where Gemini 10 landed 2.6 miles from the USS GUADAUANBL w i t h i n eye and camera range of t h e prime recovery v e s s e l . �NAME: Eugene A. Cernan (Commander, USN) pilot NASA Astronaut Apollo 10 lunar module BIRTHPLACE AND DATE: Born i n Chicago, Ill,, on March 14, 1934, H i s mother, H r s . Andrew a. Cernan, r e s i d e s i n Bellwood, Ill. Brown h a i r ; blue eyes; height: 170 pounds. PHYSICAL DESCRIPTION: weight: 6 feet; EDJCATION: araduated from Proviso Township High School i n Maywood, Ill.; received a Bachelor of Science degree i n E l e c t r i c a l Engineering from Purdue University and a Master of Science degree i n Aeronautical Engineering from t h e U.S. Naval Postgraduate School. MARITAL STATUS: Married t o t h e former Barbara J . Atchley of Houston, Tex. CHILDREN: Teresa Dawn, March 4 , 1963. OTHER ACTIVITIES: H i s hobbies include gardening and a l l s p o r t s activities. ORQANIZATIONS: Member of Tau Beta P i , n a t i o n a l engineering s o c i e t y ; Sigma X i , n a t i o n a l science research s o c i e t y ; and Phi Gamma Delta, n a t i o n a l s o c i a l f r a t e r n i t y . SPECIAL HONORS: Awarded t h e NASA Exceptional Service Medal; t h e Navy Astronaut Wings; and t h e Distinguished Flying Cross. EXPERIENCE: Cernan, a United S t a t e s Navy commander, received h i s commission through t h e Navy ROTC program a t Purdue. He entered f l i g h t t r a i n i n g upon h i s graduation. P r i o r t o a t t e n d i n g the Naval Postgraduate School, he was assigned t o Attack Squadrons 126 and 113 a t t h e Miramar, C a l i f . , Naval A i r S t a t i o n , H e has logged more than 3,000 hours flying time with more than 2,810 hours i n jet a i r c r a f t . CURRENT ASSIGNMENT: Commander Cernan was one of t h e t h i r d group of a s t r o n a u t s s e l e c t e d by NASA i n October 1963. �He occupied t h e p i l o t seat alongside Command Pilo"u0m S t a f f o r d on t h e Gemini 9 mission. During t h i s 3-day f l i g h t which began on June 3, 1966, t h e s p a c e c r a f t a t t a i n e d a c i r c u l a r o r b i t o f 161 s t a t u t e miles; t h e crew used t h r e e d i f f e r e n t techniques t o e f f e c t rendezvous with t h e previous ly launched Augmented Target Docking Aaap t e r ; and Cernan logged two hours and t e n minutes o u t s i d e t h e spacec r a f t i n e x t r a v e h i c u l a r a c t i v i t y , The f l i g h t ended a f t e r 72 hours and 20 minutes with a p e r f e c t r e e n t r y and recovery as Gemini g landed within 1* miles of t h e prime recovery s h i p USS WASP and 3/8 of a mile from t h e predetermined t a r g e t p o i n t . He has s i n c e served as backup p i l o t f o r Gemini 12. �APOLLO LAUNCH OPERATIONS NASA's John F, Kennedy Space Center performs p r e f l i g h t checkout, t e s t , and launch of t h e Apollo 10 space v e h i c l e , A government-industry team of about 550 w i l l conduct t h e f i n a l countdown from F i r i n g Room 3 of t h e Munch Control Center (LCC). The f i r i n g room team i s backed up by more t h a n 5,000 persons who a r e d i r e c t l y involved i n launch o p e r a t i o n s a t KSC from t h e time t h e v e h i c l e and s p a c e c r a f t s t a g e s a r r i v e a t t h e c e n t e r u n t i l t h e launch i s completed, -- I n i t i a l checkout of t h e Apollo s p a c e c r a f t i b conducted i n work s t a n d s and i n t h e a l t i t u d e chrunbers i n t h e Manned Spacec r a f t Operations Building (MSOB) a t Kennew Space Center. A f t e r completion of checkout t h e r e , t h e a s s a b l e d s p a c e c r a f t I s taken t o t h e v e h i c l e Assembly Building (vAB) and mated with t h e launch vehicle. There t h e f i r s t i n t e g r a t e d s p a c e c r a f t and launch v e h i c l e tests a r e conducted, The assembled space v e h i c l e i s then r o l l e d o u t 60 t h e luanch pad f o r f i n a l p r e p a r a t i o n s and countdown t o launch, I n mid-October 1968, P l i g h t hardware f o r Apollo 10 began a r r i v i n g a t Kennedy Space Center, j u s t as Apollo 7 was being launched from Complex 34 on Cape Kennedy and as Apollo 8 and Apollo 9 were undergoing checkout a t lCennedy Space Center. The l u n a r module was t h e f i ~ s pt i e c e of' .&pollo 10 f l i g h t hardware t o a r r i v e a t KSC, The two s t a g e s e r e moved i n t o t h e a l t i t u d e chamber i n t h e Manned S p a c e c r a f t Operations Building (MSOB) a f t e r a n i n i t i a l m c e i v i n g i n s p e c t i o n i n October, I n t h e chamber &he I$I underwent systems tests and both unmanned and manned chamber runs, During t h e s e runs t h e chamber a i r was pumped out t o s i m u l a t e t h e vacuum of space a t a l t i t u d e s i n excesa of 200,000 f e e t , There t h e s p a c e c r a f t systems and t h e a s t r o n a u t s g l i f e support systems were t e s t e d , While t h e 1C4\11 was undergoLng p r e p a r a t i o n f o r i t s manned a l t i t u d e chamber runs, t h e Apollo 10 command/service module a r r i v e d a t KSC and a f t e r r e c e i v i n g i n s p e c t i o n , it, too, was placed i n a n a l t i t u d e chamber i n t h e MSOB f o r systems t e s t s and unmanned and manned chamber runs, The prime and back-up crews p a r t i c i p a t e d i n t h e chamber r u n s on both t h e LM and t h e CSM , I n January, t h e I24 and CSM were removed from t h e chambers. A f t e r i n s t a l l i n g t h e landing g e a r on t h e LM and t h e SPS engine nozzle on t h e CSM, t h e LM was encapsulated i n t h e s p a c e c r a f t W a d a p t e r (SLA) and t h e CSM was mated t o t h e SLA. On February 6, t h e assembled s p a c e c r a f t was moved t o t h e VAB where i t was mated t o t h e launch v e h i c l e , �The launch vehicle flight hardware began a r r i v i n g a t KSC i n late November, and by t h e end of December t h e t h r e e stages and t h e instrument unit were erected on t h e mobile launcher i n high bay 2, This was the first time high bay 2, on t h e west s i d e of t h e VAB, had been used f o r assembling a Saturn V, Tests were conducted on Individual systems on each of t h e s t a g e s and on t h e o v e r a l l launch vehicle before the spacecraft was erected a t o p t h e vehicle, After spacecraft erection, t h e spacecraft and launch vehicle were e l e c t r i c a l l y mated and t h e first o v e r a l l test (plugs-in) of t h e space vehicle was conducted, I n accordance with t h e philosophy of a c c m p l i s h i n g as much of t h e checkout as possible i n t h e VAB, t h e o v e r a l l test was conducted before t h e space vehicle was moved t o t h e launch pad. The plugs-in test v e r i f i e d the compatibility of the space vehicle systems, ground support equipment, and o f f - s i t e support f a c i l i t i e s by demonstrating t h e a b i l i t y of t h e systems t o proceed through a simulated countdown, launch, and f l i g h t . During t h e simulated f l i g h t portion of t h e test, t h e systems were required t o respond t o both emergency and normal f l i g h t conditions, The move t o Pad B from t h e VAB on March 11 occurred while t h e Apollo 9 c i r c l e d t h e Earth i n t h e first manned test of t h e lunar module. Apollo LO w i l l mark the first launch a t Pad B on complex 39. The first two unmanned Saturn V launches and t h e manned Apollo 8 and 9 launches took place at Pad A. It a l s o marked t h e f i r s t time t h a t t h e t r a n s p o r t e r maneuvered around t h e VAB carrying a f u l l load from high bay 2 on t h e 5-mile t r i p t o the launch pad, The s t a c e vehicle F l i g h t Readiness Test was conducted i n e a r l y April. Both t h e prime and backup crews p a r t i c i p a t e i n portions of t h e FFtT, which is a f i n a l o v e r a l l t e s t of t h e space vehicle systems and gmund support equipment when a l l systems are a s near as possible t o a launch configuration, After hypergolic f u e l s were loaded aboard the spsce vehicle, and t h e launch vehicle first s t a g e f u e l (RP-1) was brought aboard, t h e f i n a l major test of the space vehicle began. T h i s w a s the countdown demonstration test ( c D ~ ) , a d r e s s r-?hearsal f o r the f i n a l countdown t o launch, The CDM! f o r Apollo 10 was divided into a "wet" and a "dryf' portion. D u r i n g t h e first, o r "wet" portion, t h e e n t i r e countdown, including propellant loading, rlas c a r r i e d out down t o T-8.9 seconds, The astronaut crews did not p a r t i c i p a t e i n t h e w e t CDm. A t t h e completion of the wet CDEP, t h e cryogenic �. p r o p e l l a n t s ( l i q u i d oxygen and liquid hydrogen) were off-loaded, and t h e f i n a l p o r t i o n of t h e countdown was re-run, t h i s time s i m u l a t i n g t h e f u e l i n g and w i t h t h e prime a s t r o n a u t crew p a r t i c i p a t i n g as t h e y will on launch day. By t h e time Apollo 10 was e n t e r i n g t h e f i n a l phase of Its checkout procedure a t Complex 39B, crews had a l r e a d y s t a r t e d t h e checkout of Apollo 11 and Apollo 12. The Apollo 11 s p a c e c r a f t completed a l t i t u d e chamber t e s t i n g and was mated t o t h e launch v e h i c l e i n tne VAR i n mid-April a s t h e Apollo 12 CSM and LM begari checkout i n t h e a l t i t u d e chambers. Because of t h e complexity involved i n t h e checkout of t h e 363-foot-tall (110.6 meters) Apollo/Saturn V configuration, t h e launch teams make use of e x t e n s i v e automation in t h e i r checkout. Automation i s one of t h e major d i f f e r e n c e s i n checkout used on Apollo compared t o t h e procedures used i n t h e Mercury and Gemini programs. Computers, data d i s p l a y equipment, and d i g i t a l d a t a techniques are used throughout t h e automatic checkout f r o m t h e time t h e launch v e h i c l e i s e r e c t e d i n t h e VAB through l i f t o f f , A s i m i l a r , but s e p a r a t e computer o p e r a t i o n c a l l e d ACE ( ~ c c e p t a n c e Checkout Equipment) i s used t o v e r i f y t h e f l i g h t r e a d i n e s s of t h e s p a c e c r a f t . Spacecraft checkout i s c o n t r o l l e d from s e p a r a t e rooms i n t h e Manned Spacecraft Operations Building. ' �LAUNCH C O M P U X 39 Launch Complex 39 f a c i l i t i e s a t t h e Kennedy Space Center were planned and b u i l t s p e c i f i c a l l y f o r t h e Apollo S a t u r n V program, t h e s p a c e v e h i c l e t h a t will be u s e d t o c a r r y a s t r o n a u t s t o t h e Moon. Complex 39 i n t r o d u c e d t h e m o b i l e concept of l a u n c h operat,ions, a d e p a r t u r e from t h e f i x e d l a u n c h pad t e c h n i q u e s u s e d p r e v i o u s l y a t Cape Kennedy and o t h e r l a u n c h s i t e s . S i n c e t h e e a r l y 1950's when t h e first b a l l i s t i c misslles were launched, t h e f i x e d l a u n c h concept had been used on NASA m i s s i o n s , T h i s method c a l l e d f o r assembly, checkout and l a u n c h of a rocket a t one s i t e o m t h e l a u n c h pad. I n a d d i t i o n t o t y i n g up t h e pad, t h i s method a l s o o f t e n l e f t t h e flight equipment exposed t o t h e o u t s i d e i n f l u e n c e s of t h e weather f o r extended p e r i o d s . Using t h e mobile concept, t h e s p a c e v e h i c l e i s t h o r o u g h l y checked i n a n e n c l o s e d b u i l d i n g b e f o r e i t i s moved t o the launch pad f o r f i n a l p r e p a r a t i o n s . T h i s a f f o r d s g r e a t e r p r o t e c t i o n , a more s y s t e m a t i c checkout p r o c e s s u s i r g computer t e c h n i q u e s and a h i g h l a u n c h r a t e f o r t h e f u t u r e , s i n c e t h e pad time i s minimal. S a t u r n V s t a g e s are s h i p p e d t o t h e Kennedy Space C e n t e r b y ocean-going v e s s e l s and s p e c i a l l y d e s i g n e d a i r c r a f t , s u c h as the Guppy, Apollo s p a c e c r a f t modules a r e t r a n s p o r t e d by a i r . The s p a c e c r a f t components a r e f i r s t t a k e n t o t h e Manned Spacecraft O p e r a t i o n s B u i l d i n g f o r p r e l i m i n a r y checkout, The S a t u r n V s t a g e s are b r o u g h t immediately t o t h e V e h i c l e Assembly B u i l d i n g a f t e r a r r i v a l a t t h e nearby t u r n i n g b a s i n . Apollo 10 i s t h e f i r s t v e h i c l e t o be launched from Pad B, Complex 39. "11 p r e v i o u s S a t u r n V v e h i c l e s were launched Pad A a t Complex 39, The h i s t o r i c first l a u n c h of t h e S a t u r n V, d e s i g n a t e d Apollo 4 , took p l a c e Nov. 9, 1967 a f t e r a p e r f e c t countdown and on-time l i f t o f f a t 7 a.m. EST. The second S a t u r n V mission--Apollo 6--was conducted last A p r i l 4, The t h i r d S a t u r n V m i s s i o n , Apollo 8 , was conducted last Dec. 21-27. Apollo 9 was March 3-13, 1969. The major components of Complex 39 i n c l u d e : (1) t h e V e h i c l e Assembly B u i l d i n (VAB) where t h e A p o l l o 1 0 w a s assembled and p r e p a r e d ; 2 ) t h e Launch C o n t r o l C e n t e r , where t h e launch team c o n d u c t s t h o p r e l i m i n a r y checkout and f i n a l countdown; ( 3 ) t h e mobile l a u n c h e r , upon which t h e Apollo 10 was e r e c t e d f o r checkout and from where i t w i l l be launched; ( 4 ) t h e mobile s e r v i c e s t r u c t u r e , which p r o v i d e s e x t e r n a l access t o t h e s p a c e v e h i c l e a t t h e pad; ( 5 ) t h e t r a n s p o r t e r , which a r r r i e s t h e s p a c e v e h i c l e and mobile l a u n c h e r , as w e l l as t h e mobile s e r v i c e s t r u c t u r e t o t h e pad; ( 6 ) t h e crawlerway over which t h e s p a c e v e h i c l e t r a v e l s from t h e VAB t o t h e l a u n c h pad; and ( 7 ) t h e l a u n c h pad i t s e l f t , 'T �Vehicle Assembly build in^ The Vehicle Assembly Building i s t h e h e a r t of Launch Complex 39. Covering e i g h t a c r e s , i t i s where t h e 363-foot-tall space v e h i c l e i s assembled and t e s t e d . The VAB c o n t a i n s 129,482,000 cubic f e e t of space, It i s 716 f e e t long, and 518 f e e t wide and it covers 343,500 square f e e t of f l o o r space. The foundat i o n of t h e VAB rests on 4,225 s t e e l p i l i n g s , each 16 inches i n diameter, d r i v e n from 150 t o 170 f e e t t o bedrock. If placed end t o end, t h e s e p i l i n g s would extend a d i s t a n c e of 123 miles. The s k e l e t a l s t r u c t u r e of t h e b u i l d i n g c o n t a i n s approximately 60,000 t o n s of s t r u c t u r a l s t e e l . The e x t e r i o r i s covered by more t h a n a m i l l i o n square f e e t of i n s u l a t e d aluminum siding, The b u i l d i n g i s divided i n t o a h i g h bay a r e a 525 f e e t high and a low bay area 210 f e e t high, with both a r e a s s e r v i c e d by a t r a n s f e r a i s l e f o r movement of v e h i c l e s t a g e s . The low bay work a r e a , approximately 442 f e e t wide and 274 f e e t long, c o n t a i n s e i g h t s t a g e - p r e p a r a t i o n and checkout c e l l s . These c e l l s a r e equipped with systems t o s i m u l a t e s t a g e i n t e r f a c e and o p e r a t i o n with o t h e r s t a g e s and t h e instrument u n i t of t h e S a t u r n V launch v e h i c l e . A f t e r t h e Apollo 10 launch v e h i c l e upper s t a g e s a r r i v e d a t t h e Kennedy Space Center, t h e y were moved t o t h e low bay of t h e VAB. Here, t h e second and t h i r d s t a g e s underwent acceptance and checkout t e s t i n g p r i o r t o mating w i t h t h e S-IC f i r s t s t a g e a t o p mobile launcher 3 i n t h e high bay a r e a . The high bay provides f a c i l i t i e s f o r assembly and c h e c k o ~ t of both t h e launch v e h i c l e and s p a c e c r a f t . It c o n t a i n s f o u r s e p a r a t e bays f o r v e r t i c a l assembly and checkout. A t p r e s e n t , t h r e e bays a r e equipped, and t h e f o u r t h w i l l be r e s e r v e d f o r p o s s i b l e changes i n v e h i c l e c o n f i g u r a t i o n . -- -- Work platforms some as high a s t h r e e - s t o r y b u i l d i n g s in t h e high bays provide a c c e s s by surrounding t h e v e h i c l e a t varying l e v e l s . Each high bay has f i v e platforms, Each platform c o n s i s t s of two b i - p a r t i n g s e c t i o n s t h a t move i n from opposite s i d e s and mate, providing a 360-degree a c c e s s t o t h e s e c t i o n of t h e space v e h i c l e being checked. A 10,000-ton-capacity a i r c o n d i t i o n i n g system, s u f f i c i e n t t o cool about 3,000 homes, h e l p s t o c o n t r o l t h e environment within t h e e n t i r e o f f i c e , l a b o r a t o r y , and workshop complex l o c a t e d i n s i d e t h e low bay a r e a of t h e VAB. A i r c o n d i t i o n i n g i s a l s o fed t o i n d i v i d u a l platform l e v e l s l o c a t e d around t h e v e h i c l e . �There a r e 141. l i f t i n g devices i n t h e VAB, ranging from onet o n h o i s t s t o two 250-ton h i g h - l i f t brrdge cranes. The mobile launchers, c a r r i e d by t r a n s p o r t e r v e h i c l e s , move i n and out of t h e VAB through f o u r doors i n t h e high bay a r e a , one i n each of t h e bays, Each door i s shaped l i k e an i n v e r t e d T. They a r e 152 f e e t wide and 114 f e e t high a t t h e base, narrowing t o 76 f e e t i n w i d t h . T o t a l door h e i g h t i s 456 f e e t , The Lower s e c t i o n of each door i s of t h e a i r c r a f t hangar t y p e t h a t s l i d e s h o r i z o n t a l l y on t r a c k s . Above t h i s a r e seven t e l e s c o p i n g v e r t i c a l l i f t p a n e l s s t a c k e d one above t h e o t h e r , each 50 f e e t high and d r i v e n by a n i n d i v i d u a l motor, ]Each p a n e l s l i d e s over t h e next t o c r e a t e a n opening l a r g e enough t o p e n n i t passage of t h e mobile launcher, Munch Control Center Adjacent t o t h e VAB i s t h e h u n c h Control Center (LcC). This four-story s t r u c t u r e i s a r a d i c a l d e p a r t u r e from t h e dame-shaped blockhouses a t o t h e r launch s i t e s , The e l e c t r o n i c " b r a i n " of Launch Complex 39, t h e LCC was used f o r checkout and t e s t o p e r a t i o n s while Apollo 10 was being assembled i n s i d e t h e VAB. The LCC c o n t a i n s d i s p l a y , monitoring, and c o n t r o l equipment used f o r both checkout and launch o p e r a t i o n s . The b u i l d i n g has t e l e m e t e r checkout s ' t a t i o n s on i t s second f l o o r , and f o u r f i r i n g rooms, one f o r each high bay of t h e VAB, on i t s t h i r d f l o o r , Three f i r i n g rooms conta%n i d e n t i c a l s e t s of c o n t r o l and monitoring equipment, s o t h a t launch of a v e h i c l e and checkout of o t h e r s t a k e p l a c e simultaneously, A ground computer f a c i l i t y i s a s s o c i a t e d with each f i r i n g room, The high speed computer d a t a l i n k i s p r o ided between t h e LCC and t h e mobile launcher f o r checkout of t h e 1 unch v e h i c l e . This l i n k can be connected t o t h e mobile launcher t e i t h e r t h e VAB o r a t t h e pad, I The t h r e e equipped f i r i n g rooms have some 450 consoles which c o n t a i n c o n t r o l s and d i s p l a y s r e q u i r e d f o r the1 checkout process. The d i g i t a l d a t a l i n k s connecting taith t h e high b a y areas of t h e VAB and t h e launch pads car-ry v a s t amounts of data r e q u i r e d during checkout and launch, I I. There a r e 15 d i s p l a y systems i n each LCC i r i n g room, with each system capable of providing d i g i t a l infornlation i n s t a n t a n e ously, �S i x t y t e l e v i s i o n cameras a r e p o s i t i o n e d around t h e Apollo/ S a t u r n V t r a n s m i t t i n g p i c t u r e s on 10 modulated channels. The LCC f i r i n g room a l s o c o n t a i n s 112 o p e r a t i o n a l intercommunication channels used by t h e cpews i n t h e checkout and launch countdown. Mobile Launcher The mobile l a u n c h e r i s a t r a n s p o r t a b l e launch base and u m b i l i c a l tower f o r t h e space v e h i c l e . Three mobile launchers a r e used a t Complex 39. The launcher base i s a two-story s t e e l s t r u c t u r e , 25 f e e t h i g h , 160 f e e t long, and 135 f e e t wide. It i s p o s i t i o n e d on s i x s t e e l p e d e s t a l s 22 f e e t high when i n t h e VAB o r a t t h e launch pad, A t t h e launch pad, i n a d d i t i o n t o t h e s i x s t e e l p e d e s t a l s , f o u r extend a b l e columns a l s o are used t o s t i f f e n t h e mobile launcher a g a i n s t rebound l o a d s , i f t h e S a t u r n engines c u t o f f , The u m b i l i c a l tower, extending 398 f e e t above t h e launch p l a t form, i s mounted on one end of t h e launcher base. A hammerhead c r a n e a t t h e t o p h a s a hook h e i g h t of 376 f e e t above t h e deck with a t r a v e r s e r a d i u s of 85 f e e t from t h e c e n t e r of t h e tower. The 12-million-pound mobile launcher s t a n d s 445 f e e t high when r e s t i n g on its p e d e s t a l s , The base, covering about h a l f an a c r e , i s a compartmented s t r u c t u r e b u i l t of 25-foot s t e e l g i r d e r s , The launch v e h i c l e s i t s over a 45-foot-square opening which a l l o w s an o u t l e t f o r engine exhausts i n t o t h e launch pad t r e n c h c o n t a i n i n g a flame d e f l e c t o r . T h i s opening i s l i n e d w i t h a r e p l a c e a b l e s t e e l b l a s t s h i ~ l d ,independent of t h e s t r u c t u r e , and i s cooled by a water c u r t a i n i n i t i a t e d two seconds a f t e r l i f t o f f . There a r e n i n e h y d r a u l i c a l l y - o p e r a t e d s e r v l c e arms on t h e u m b i l i c a l tower, These s e r v i c e arms s u p p o r t l i n e s f o r t h e v e h i c l e u m b i l i c a l systems and provide a c c e s s f o r personnel t o t h e s t a g e s as well as t h e a s t r o n a u t crew t o t h e s p a c e c r a f t . On Apollo 10, one of t h e s e r v i c e arms i s r e t r a c t e d e a r l y i n t h e count. The Apollo s p a c e c r a f t a c c e s s arm i s p a r t i a l l y r e t r a c t e d a t T-43 minutes, A t h i r d s e r v i c e am i s r e l e a s e d a t T-30 seconds, and a f o u r t h a t about T-16.5 seconds, The remaining f i v e arms a r e s e t t o swing back a t v e h i c l e f i r s t motion a f t e r T-0. The s e r v i c e arms a r e equipped w i t h a backup r e t r a c t i o n system i n c a s e t h e primary mode f a i l s . �The Apollo a c c e s s arm ( s e r v i c e arm g ) , l o c a t e d a t t h e 320f o o t l e v e l above t h e l a u n c h e r base, provides a c c e s s t o t h e spacec r a f t c a b i n f o r t h e c l o s e o u t team and a s t r o n a u t crews, The f l i g h t crew w i l l board t h e s p a c e c r a f t s t a r t i n g about T-2 hours, 40 minutes i n t h e count, The a c c e s s a m w i l l be moved t o a parked position, 12 degrees from t h e s p a c e c r a f t , a t about T-43 minutes, T h i s i s a d i s t a n c e of about t h r e e f e e t , whish p e r m i t s a r a p i d r e c o n n e c t i o n of t h e arm t o t h e s p a c e c r a f t i n t h e event of a n emergency condition. The arm i s f u l l y r e t r a c t e d a t t h e T-5 mlnute mark i n t h e count, The Apollo 10 v e h i c l e i s secured t o t h e mobile l a u n c h e r by f o u r combination s u p p o r t and hold-down arms mounted on t h e launcher deck. The hold-down ams are c a s t i n one p i e c e , about 6 x 9 feet a t t h e b a s e and 10 f e e t t a l l , weighing more t h a n 20 t o n s . Damper s t r u t s s e c u r e t h e v e h i c l e n e a r i t s top. A f t e r t h e engines i g n i t e , the arms hold Apollo LO f o r about s i x seconds u n t i l t h e engines build u p t o 95 p e r c e n t t h r u s t and o t h e r monitored systems i n d i c a t e they a r e f u n c t i o n i n g p r o p e r l y . The arms r e l e a s e on r e c e i p t of a launch commit s i g n a l a t t h e z e r o mark i n t h e count. B u t t h e v e h i c l e i s prevented from a c c e l e r a t i n g t o o r a p i d l y by c o n t r o l l e d r e l e a s e mechanisms. Transporter The six-million-pound t r a n s p o r t e r s , t h e l a r g e s t t r a c k e d vehi c l e s known, move mobile l a u n c h e r s i n t o t h e VAB and mobile launchers w i t h assembled Apollo space v e h i c l e s t o t h e launch pad. They also a r e used t o t r a n s f e r t h e mobile s e r v i c e s t r u c t u r e t o and from t h e launch pads. Two t r a n s p o r t e r s are i n u s e a t Complex 39, The TYansporter i s 131 f e e t long and 114 f e e t wide. The v e h i c l e moves on f o u r double-tracked c r a w l e r s , each 10 feet high and 40 f e e t long, Each shoe on t h e c r a w l e r t r a c k i s seven f e e t six i n c h e s i n l e n g t h and weighs about a ton. S i x t e e n t r a c t i o n motors powered by f o u r 1,000-kilowatt gene r a t o r s , which i n t u r n a r e d r i v e n by two 2,750-ho~sepower d i e s e l engines, p r o v i d e t h e motive power f o r t h e t r a n s p o r t e r . Two 750k w g e n e r a t o r s , d r i v e n by two 1,065-horsepower d i e s e l engines, power t h e jacking, s t e e r i n g , l i g h t i n g , v e n t i l a t i n g and e l e c t r o n i c systems. Maximum speed of t h e t r a n s p o r t e r is about one-mile-per-hour loaded and about two-miles-per-hour unloaded, A five-mile t r i p t o Pad I3 with a mobile launcher, made a t l e s s t h a n maximum speed, t a k e s approximately 10-12 hours, �The t r a n s p o r t e r has a l e v e l i n g system designed t o keep t h e t o p of t h e space v e h i c l e v e r t i c a l within plus-or-minus 10 minutes of a r c about t h e dimensions of a basketball. -- This system a l s o provides l e v e l i n g operations required t o n e g o t i a t e t h e f i v e percent ramp which l e a d s t o t h e launch pad and keeps t h e load l e v e l when it i s r a i s e d and lowered on p e d e s t a l s both a t t h e pad and within t h e VAB. The o v e r a l l level t o the top transportation. b a l l diamond (90 height of t h e t r a n s p o r t e r i s 20 f e e t from ground deck on which t h e mobile launcher i s mated f o r The deck is f l a t and about t h e s i z e of a baseby 90 f e e t ) , Two operator c o n t r o l cabs, one a t each end of t h e c h a s s i s located diagonally opposite each other, provide t o t a l l y enclosed s t a t i o n s f r a m which a l l operating and c o n t r o l functions a r e coordinated. Crawlerway The t r a n s p o r t e r moves on a roadway 131 f e e t wide, divided by a median s t r i p . This i s almost a s broad a s an eight-lane turnpike and i s designed t o accommodate a combined weight of about 18 m i l l i o n pounds. The roadway i s b u i l t i n t h r e e l a y e r s with an average depth of seven f e e t . The roadway base l a y e r i s two-and-one-half f e e t of hydraulic f i l l compacted t o 95 percent density. The next l a y e r c o n s i s t s of t h r e e f e e t of crushed rock packed t o maximum density, followed by a l a y e r of one f o o t of s e l e c t e d hydraulic fill. The bed I s topped and s e a l e d w i t h an a s p h a l t prime coat. On top of t h e t h r e e l a y e r s i s a cover of r i v e r rock, e i g h t inches deep on t h e curves and s i x inches deep on t h e straightway, This l a y e r reduces the f r i c t i o n during s t e e r i n g and helps d i s t r i b u t e the load on the t r a n s p o r t e r bearings. Mobile Service S t r u c t u r e A 402-foot-tall, 9.8-million-pound tower i s used t o s e r v i c e t h e Apollo launch vehicle and spacecraft a t t h e pad. The 40-story s t e e l - t r u s s e d tower, c a l l e d a mobile s e r v i c e s t r u c t u r e , provides 360-degree platform access t o t h e Saturn launch vehicle and t h e Apollo s p a c e c r a f t . -- The s e r v i c e s t r u c t u r e has f i v e platforms two self-propelled Two e l e v a t o r s carry personnel and equipment between work platforms. The platforms can open and c l o s e around t h e 363-foot space vehicle, and t h r e e fixed, but movable. �A f t e r dep<:*sitingt h e mobile launcher wLth i t s space vehicle on t h e pad, the t r 8 a n s p o r t e r r e t u r n s t o a parking a r e a about 13,000 f e e t from pad B. There i t p i c k s up the mobile s e r v i c e s t r u c t u r e and moves it t o t h e launch pad. A t t h e pad, t h e huge tower i s lowered and secured t o f o u r mount mechanisms. The t o p t h r e e work platforms are l o c a t e d i n f i x e d p o s i t i o n s which s e r v e t h e Apollo s p a c e c r a f t , The two lower movable platforms s e r v e t h e S a t u r n V. The mobile s e r v i c e s t r u c t u r e remains i n p o s i t i o n u n t i l about T-11 hours when it i s removed from i t s mounts and r e turned t o t h e parkinff area. Water Deluge System 4 water deluge system w i l l provide a m i l l i o n g a l l o n s of i n d u s t r i a l water f o r c o o l i m and f i r e prevention d u r i n g launch of Apollo 10. Once t h e s e r v i c e anns a r e r e t r a c t e d a t l i f t o f f , a s p r a y system w i l l come on t o c o o l t h e s e arms from t h e h e a t of t h e f i v e S a t u r n F-1 engines d u r i n g l i f t o f f . On t h e deck of t h e mobile launcher are 29 water nozzles. This deck deluge w i l l s t a r t immediately a f t e r l i f t o f f and w i l l pour a c r o s s t h e f a c e of t h e launcher f o r 30 seconds a t t h e r a t e of 50,000 gallons-per-minute, a f t e r 30 seconds, t h e flow w i l l be reduced t o 20,000 gallons-per-minute, Positioned on both s i d e s of t h e flame t r e n c h a r e a s e r i e s of nozzles which w i l l begin pouring water at 8,000 gallons-per-minute, 10 secorcl s before l i f t o f f . This water w i l l be d i r e c t e d over t h e flame d e f l e c t o r . Other f l u s h mounted nozzles, p o s i t i o n e d around t h e pad, w i l l wash away any f l u i d s p i l l a s a p r o t e c t i o n a g a i n s t f i r e hazards. Water spray systems a l s o a r e a v a i l a b l e along t h e e g r e s s r o u t e t h a t t h e a s t r o n a u t s and c l o s e o u t crews would follow i n c a s e a n emergency evacuation w a s required. Flame Trench and D e f l e c t o r The flame t r e n c h i s 58 f e e t wide and approximately s i x f e e t above mean s e a l e v e l a t t h e base. The h e i g h t of t h e t r e n c h and d e f l e c t o r i s approximately 42 f e e t . �The Tiam-.d e f l e c t o r weighs about 1.3 m i l l i o n pounds and i s s t o r e d o u t s i d e t h e flame t r e n c h on rails. Wehn i t i s moved beneath the launcher, i t i s raised h y d r a u l i c a l l y i n t o p o s i t i o n , The d e f l e c t o r i s covered w i t h a four-and-one-half-inch t h i c k ness of r e f r a c t o r y c o n c r e t e c o n s i s t i n g of a v o l c a n i c a s h aggregate and a calcuim aluminate binder. The heat and b l a s t of t h e engines a r e expected t o wear about t h r e e - q u a r t e r s of a n i n c h from t h i s r e f r a c t o r y s u r f a c e d u r i n g t h e Apollo l o launch. pad Areas Both Pad A and Pad B of -hunch Complex 39 are roughly octagonal I n shape and cover about one f o u r t h of a square mile of t e r r a i n . The c e n t e r of t h e pad i s a hardstand c o n s t r u c t e d of heavily reinforced concrete. I n addition t o supporting t h e weight of t h e mobile launcher and t h e Apollo S a t u r n V v e h i c l e , it a l s o must support t h e 9.8-million-pound mobile s e r v i c e s t r u c t u r e and 6-million-pound t r a n s p o r t e r , a l l a t t h e same time. The t o p of t h e pad s t a n d s some 48 f e e t above s e a l e v e l , Saturn V p r o p e l l a n t s -- l i q u i d oxygen, l i q u i d hydrogen and RP-1 are s t o r e d n e a r t h e pad perimeter. -- S t a i n l e s a s t e e l , vacuum-jacketed p i p e s c a r r y t h e l i q u i d oxygen (LOX) and l i q u i d hydrogen from t h e s t o r a g e t a n k s t o t h e pad, up t h e mobile launcher, and f i n a l l y i n t o t h e launch v e h i c l e p r o p e l l a n t tanks. LOX i s supplied from a 900,000-gallon s t o r a g e t a n k . c e n t r i f u g a l pump w i t h a d i s c h a r g e p r e s s u r e of 320 poundsper-square-inchpumps LOX t o t h e v e h i c l e a t flow rates as high as 10,000-gallons-per-minute. A Liquid hydrogen, u s e d i n t h e second and t h i r d s t a g e s , i s s t o r e d i n an 850,000-gallon tank, and i s s e n t through 1,500 f e e t of 10-inch, vacuum-Jacketed i n v a r pipe. A vapori z i n g h e a t exchanger p r e s s u r i z e s t h e s t o r a g e tank t o 60 p s i f o r a 10,000 gallons-per-munute flow r a t e , The RP-1 f u e l , a high grade of kerosene i s s t o r e d i n t h r e e tanks--each with a c a p a c i t y of 86,000 g a l l o n s . It i s pumped a t a r a t e of 2,000 gallons-per-minute a t 175 p s i g , The Complex 39 pneumatic system i n c l u d e s a convertercompressor f a c i l i t y , a pad high-pressure gas s t o r a g e b a t t e t y , a high-pressure s t o r a g e b a t t e r y i n t h e VAB, low and high-press u r e , cross-country supply l i n e s , h i ~ h - p r e s s u r e hydrogen s t o r a g e and conversion equipment, and pad d i s t r i b u t i o n pipinp, t o pneumatic c o n t r o l panels, The v a r i o u s purging systems r e q u i r e 187,000 pounds of l i q u i d n i t r o g e n and 21,000 g a l l o n s of helium, �Pad B is v i r t u a l l y a twin of Pad A , The $op sf Pad B i s 5 f e e t h i g h e r i n e l e v a t i o n above mean sea l e v e l than Pad A t o provide b e t t e ~dratnage of t h e general area p tus b e t t e r drainage from h o P d i n ~and burn ponds. The e l e c t r i c a l s u b s t a t i o n f o r Pad B is l o c a t e d undern e a t h t h e w e s t s l o p e of t h e p a d whereas t h e corresponding s u b s t a t i o n f o r Pad A i s i n t h e open approximately 150 f e e t from t h e lower edge of t h e west s l o p s of t h e pad, The pad B d e s i g n change was made t o harden t h e s u b s t a t i o n a g a l n s t tfre launch environment. The only o t h e r major d i f f e r e n c e i s i n t h e l o c a t i o n of t h e i n d u s t r i a l / f i r e / p o t a b l e water valve p i t . A t Pad A, i t ' s on t h e west s i d e of t h e Pad and a t Pad B i t ' s on t h e east s i d e of t h e pad. The d i f f e r e n c e r e s t s i n t h e r o u t ing of water l i n e s a l o n g s i d e t h e crawlerway. Basic c o n s t r u c t i o n work on Pad B began on Dec, 7, 1964, and t h e f a c i l i b y was accepted by t h e government on August 22, 1966. The intemrening period h a s been s p e n t i n equipping t h e pad and b r i n g i n g it up t o launch r e a d i n e s s , Mission Control Center The Hission Control Center a t t h e Manned Spacecraft Center, Houston, i s t h e f o c a l p o i n t f o r Apollo flight c o n t r o l a c t i v i t i e s . 'Pbe c e n t e r r e c e i v e s t r a c k i n g and t e l e m e t r y d a t a from the Manned Space F l i g h t Network, p r o c e s s e s t h i s d a t a through t h e Mission Control Center Real-Time Computer Complex, and d i s p l a y s t h i s d a t a t o t h e f l i g h t c o n t r o l l e r s and e n g i n e e r s i n t h e Mission Operations Control Room and staff support rooms. The Manned Space F l i g h t Network t r a c k i n g and d a t a acqufaftfon s t a t i o n s link t h e f l i g h t controllers a t t h e center t o the spacecraft, For Apollo 10 a l l network s t a t i o n s w i l l be remote s i t e s , t h a t is, without f l i g h t c o n t r o l teams, A l l u p l i n k commands and voice c o m n i c a t i o n s w i l l o r i g i n a t e from Houston, and t e l e m e t r y d a t a w i l l be s e n t back t o Houston a t high speed r a t e s (2,400 b i t s - p e r - s e c o n d ) , on two s e p a r a t e d a t a l i n e s . They can be e % t h e r r e a l time o r playback information. S i g n a l flow f o r voice c i r c u i t s between Houston and t h e remote s i t e s i s v i a commercial c a r r i e r , u s u a l l y s a t e l l i t e , wherever p o s s i b l e u s i n g leased l i n e s which a r e part of t h e NASA n i c a t i o n s Network. Comands a r e s e n t from Houston t o NASA's Goddard Space F l i g h t Center, Greenbelt, Md., on l i n e s which l i n k computers a t t h e two p o i n t s . The Goddard communication computers prov i d e automatic switching f a c i l i t i e s and speed b u f f e r i n g f o r t h e command d a t a , Data a r e t r a n s f e r r e d from Goddard t o remote s i t e s on high speed (2,400 bits-per-second) l i n e s . Command loads a l s o can be s e n t by t e l e t y p e from Houston t o the remote sites a t 100 wor8-s-per-minute . Again, Goddard computers provide s t o r a g e and switching f u n c t i o n s . -more- �Telemetry data at the remote site are received by the RF receivers, processed by the pulse aede modulation ground stations, and transferred to the 642B remote-site telemetry computer for storage. Depending on the format selected by the telemetry controller at Houston, the 642B willsend the desired format through a 2010 data trans mission unit which provides parallel to serial conversion, and drives a 2,400 bit-per-second mode. The data mode converts the digital serial data to phase-shifted keyed tones which are fed to the high speed data lines of the comunications network. Tracking data are sent from the sites in a low speed (100 words) teletype format and a 240-bit block high speed (2,400 bits) format. Data rates are one sample-6 seconds for teletype and 10 samples (frames) per second for high speed data. All high-speed data, whether tracking or telemetry, which originate at a remote site are sent to cfoddard on highspeed lines. Goddard reformats the data when necessary and sends them to Houston in 600-bit blocks at a 40,800 bits-persecond rate. Of the 600-bit block, 480 bits are reserved for data, the other 120 bits for address, sync, intercomputer instructions, and polynominal error encoding. All wideband 40,800 bits-per-second data originating at Houston are converted to high speed (2,400 bits-per-second) data at Goddard before being transferred to the designated remote site. �MANNED SPACE FLIGHT NETWORK The Manned Space F l i g h t Network (MSFN) w i l l support the complete Apollo s p a c e c r a f t , o p e r a t i n g a t l u m r d i s t a n c e , f o r t h e first t i m e i n Apollo 10, The network had i t s i n i t i a l s e r v i c e w i t h l u n a r d i s t a n c e s i n Apollo 8 last December, b u t that flfght d i d n o t c a r r y t h e l u n a r module. For Apollo 10, the MSPN will employ a'? ground s t a t i o n s ( i n c l u d i r t ~thtSee wing, or backup, s i t e s ) , f s ~ i rinstrumented shLps, and s i x to e i g h b instrumented aiseraft, t o track spacecraft position and furnish a large volume of e o m u n i c a t i o n s , t e l e v i s i o n arad telemetry servfces, Essentially, t h e e n t i r e network I s d e s i ~ n e dt o provide r e l i a b l e and continuous c o m u n i c ~ t i o n sw i t h t h e a s t r o n a u t s , launch v e h i c l e and s p a c e c r a f t from l i f t o f f through l u n a r o r b i t t o splashdown. It w i l l keep ground c o n t r o l l e r s i n c l o s e cont a c t with t h e s p a c e c r ~ f tand a s t r o n a u t s a t a l l times, except f o r approximately 45 minutes when Apollo 1 0 w i l l be behind t h e Moon d u r i n g each l u n a r o r b i t =nd t h e time between s t a t i o n s w h i l e i n Earth o r b i t , As tke space v e h i c l e l i f t s o f f from Kennedy Space Center, t h e t r a c k i n g s t a t i o n s w i l l be watchine; it. A s t h e S a t u r n ascends, v o i c e and d a t a w i l l be i n s t a n t a n e o u s l y t r a n s m i t t e d t o Mission . Control Center (MCC) i n Houston. Data w i l l be run through computers a t MCC f o r v i s u a l d i s p l a y t o f l i g h t c o n t r o l l e r s . Depending on t h e launch azimuth, a s t r i n g of 30-footdiameter antennas around t h e Earth w i l l keep t a b s on Apollo 10 and t r a n s m i t information back t o Houston: beginning with t h e s t a t i o n a t Merritt I s l a n d , F l a , ; thence Grand Bahama I s l a n d , Bermuda; t h e t r a c k i n g s h i p Vanguard; Canary I s l a n d ; Carnarvon, Australia; Hawaii, t r a c k i n g s h i p Redstone, Guaymas, Mexico; and Corpus Christi, T e x . To i n j e c t Apollo 1 0 i n t o t r a n s l u n a r t r a j e c t o r y WCC w i l l send a s i g n a l through one of t h e land s t a t i o n s o r one of t h e Apollo s h i p s i n t h e P a c i f i c . A s t h e s p a c e c r a f t head f o r t h e Moon, t h e engine burn w i l l be monitored by t h e s h i p s and a n Apollo Range I n s t r u m e n t a t i o n A i r c r a f t ( A R I A ) , The A R I A p r o v i d e s a r e l a y f o r t h e a s t r o n a u t s 1 v o i c e s and d a t a communication w i t h Houston. As t h e s p a c e c r a f t moves away from Earth, t h e s m a l l e r 30-foot diameter antennas communicate first w i t h t h e spacec r a f t . A t a s p a c e c r a f t a l t i t u d e of 10,000 miles the t r a c k i n g f u n c t i o n goes t o t h e more powerful 85-foot antennas. These a r e l o c a t e d n e a r Madrid, Spain; Goldstone, C a l i f . ; and Canberra, Australia. �A R C T I C OCEAN 1 0 1 W C I C I f I C OCfAU I N D I A N OCEAN M A N N E D SPACE FLIGHT TRACKING NETWORK �The 85-foot a n t e n n a s are spaced a t approximately 120degree i n t e r v a l s around U r t h $0 at least one antenna has thp Moon in view a t glla times. As &he & r t h revolveg from we@C f;o east, one s t a t i o n hands over c o n t r o l t o t h e next s t a t i o n a@ i t moves i n t o view of Che s p a c e c r a f t . I n this way, cont$nuous d a t a and communication flow 1s maintained. Data are c o n s t a n t l y r e l a y a d back through t h e huge antennas and t r a n s m i t t e d v i a t h e NASA Communications Network (NASCOM) a h a l f m i l l i o n milea of land and underseas c a b l e s and r a d i o c i r c u i t s , i n c l u d i n g t h o s e t h m ugh communications s a t e l l i t e s , t o MCC, T h i s information i s f e d i n t o computers f o r v i s u a l d i s p l a y i n Missidn Control. For example, a d i s p l a y would show t h e exact p o s i t i o n of t h e s p a c e c r a f t on a l a r g e map. Returning data could i n d i c a t e a drop i n power o r some o t h e r d i f f i c u l t y which would r e s u l t i n a red l i g h t going on t o a l e r t a f l i g h t controller t o corrective action. Returning data flowing t o t h e Earth s t a t i o n s g i v e t h e necessary information f o r commanding mid-course maneuvers t o keep t h e Apollo 1 0 i n a proper t r a j e c t o r y f o r o r b i t i n g , t h e Moon, While t h e f l i g h t i s i n t h e v i c i n i t y of t h e Moon, t h e s e data i n d i c a t e t h e amount of r e t r o g r a d e burn necessary f o r t h e s e r v i c e module engine t o p l a c e t h e s p a c e c r a f t u n i t s i n l u n a r orbit. Once t h e l u n a r module s e p a r a t e s from t h e command module/ s e r v i c e module and goes i n t o a s e p a r a t e l u n a r o r b i t , t h e MSFN w i l l be r e q u i r e d t o keep t r a c k of both c r a f t and provide cont i n u o u s two-way communicatlons and t e l e m e t r y between them and t h e Earth, The prime antenna a t each of t h e t h r e e MSFN deep space t r a c k i n g s t a t i o n s w i l l handle one c r a f t while t h e wing o r back-up antenna a t each of t h e s e s t a t i o n s w i l l handle t h e o t h e r c r a f t d u r i n g each pass. Continuous t r a c k i n g and a c q u i s i t i o n of d a t a between Earth and t h e Apollo s p a c e c r a f t w i l l provide support f o r t h e Apollo rendezvous and docking maneuvers. T h i s information a l s o w i l l be used t o determine t h e time and d u r a t i o n of t h e s e r v i c e module propulsion engine burn r e q u i r e d t o place t h e command s e r v i c e module i n t o a p r e c i s e t r a j e c t o r y f o r reenterkng t h E a r t h ' s atmosphere a t t h e planned l o c a t i o n . A s t h e s p a c e c r a f t moves toward E a r t h a t about 25,000 miles-per-hour, i t must ree n t e r a t t h e proper angle. l Data coming t o t h e v a r i o u s t r a c k i n g s t a t i o n s and s N p s a r e f e d i n t o t h e computers a t MCC. From computer c a l c u l a t i o n s . , t h e P l i g h t c o n t r o l l e r s w i l l provide t h e r e t u r n i n g s p a c e c r a f t with t h e necessary information t o m k e a n a c c u r a t e r e e n t r y . Appropriate MSFN s t a t i o n s , i n c l u d i n g t r a c k i n g s h i p s and a irc r a f t p o s i t i o n e d i n t h e P a c i f i c f o r t h i s event a r e on hand t o provide support d u r i n g r e e n t r y . An A R I A a i r c r a f t w i l l r e l a y a s t r o n a u t voice communications t o MCC and Qntennas on r e e n t r y s h i p s w i l l follow the s p a c e c r a f t . �During t h e journey t o t h e Moon and back, t e l e v i s i o n w i l l be received from t h e s p a c e c r a f t a t t h e t h r e e 85-foot antennas around the world, i n Spain, C a l i f o r n i a , and A u s t r a l i a , Scan c o n v e r t e r s permit imediat e t r a n s m i s s i o n of c o m e r c i a 1 q u a l i t y t e l e v i s i o n v i a NASCOM t o Mission Control where I t w i l l be rel e a s e d t o TV networks. NASA Communications Network The NASA Communications Network (NASCOM) c o n s i s t s of s e v e r a l systems of d i v e r s e l y r o u t e d communications channels l e a s e d on communications satellites, common c a r r i e r systems and high frequency r a d i o f a c i l i t i e s where necessary t o provide the access links, The system c o n s i s t s of both narrow and wide-band channels, and some TV channels, Included a r e a v a r i e t of t e l e g r a p h , voice, and d a t a systems ( d i g i t a l and analog7 with s e v e r a l d i g i t a l data rates. Wide-band systems do not extend overseas. A l t e r n a t e r o u t e s o r redundancy provide added r e l i a bility, A primary switching c e n t e r and i n t e r m e d i a t e switching and c o n t r o l p o i n t s provide c e n t r a l i z e d f a c i l i t y and t e c h n i c a l c o n t r o l , and switching o p e r a t i o n s under d i r e c t NASA c o n t r o l . The primary switching c e n t e r i s a t t h e Goddard Space F l i g h t Center, Greenbelt, Md. I n t e r m e d i a t e switching c e n t e r s a r e l o c a t e d a t Canberra, Madrid, London, Honolulu, Guam, and Kennedy Space Center. F o r Apollo 10, t h e Kennedy Space Center i s connected d i r e c t l y t o t h e Mission Control Center, Houston v i a t h e Apollo Launch Data System and t o t h e Marshall Space F l i g h t Center, H u n t s v i l l e , Ala., by a Launch Information Exchange F a c i l i t y . Both of t h e s e systems a r e p a r t of NASCOM, They c o n s i s t of d a t a g a t h e r i n g and t r a n s m i s s i o n f a c i l i t i e s designed t o handle launch d a t a e x c l u s i v e l y , A f t e r launch, a l l network t r a c k i n g and t e l e m e t r y d a t a hubs a t QSFC f o r t r a n s m i s s i o n t o MCC Houton v i a two 50,000 b i t s - p e r second c i r c u i t s used f o r redundancy and i n c a s t of data overflow. Two I n t e l s a t communications s a t e l l i t e s w i l l be used f o r Apollo 10. The A t l a n t i c s a t e l l i t e w i l l s e r v i c e t h e Ascension I s l a n d u n i f i e d S-band (USB) s t a t i o n , t h e A t l a n t i c Ocean s h i p and t h e Canary I s l a n d s s i t e . These s t a t i o n s w i l l be able t o t r a n s m i t through t h e s a t e 1l i t e v i a t h e Comsat -operated ground s t a t i o n a t Etam W.Va. �A R C T I C OCEAN A R C T I C OCEAN I N D I A N OCEAN SOUTH P A C I F I C OCEAN NASA COMMUNICATIONS NETWORK �The second Apollo I n t e l s a t communications s a t e l l i t e over t h e mid-Pacific w i l l s e r v i c e t h e Carnarvon, A u s t r a l i a USB s i t e and t h e P a c i f i c Ocean ships. A l l t h e s e s t a t i o n s w i l l b e able t o transmit simultaneously through t h e s a t e l l i t e t o Houston v i a Brewster F l a t , Wash,, and t h e Goddard Space F l i g h t Center, Greenbelt, Md. Network Computers A t fraction-of-a-second i n t e r v a l s , t h e network's d i g i t a l data processing systems, with NASA's Manned s p a c e c r a f t . Center a s t h e f o c a l p o i n t , " t a l k " t o each o t h e r o r t o t h e spacecraft High-speed computers a t t h e remote s i t e ( t r a e k i n g ships included) i s s u e commands o r "up-link" d a t a on auch matters as c o n t r o l of cabin p r e s s u r e , o r b i t a l p i d a n c e commands, o r I t go-no-go" i n d i c a t i o n s t o perform c e r t a i n f u n c t i o n s , When information o r i g i n a t e s from Houston, t h e computers rere? t o t h e i r pre-programmed information f o r v a l i d i t y before transmitting t h e required d a t a t o t h e s p a c e c r a f t , Such "up-link" Information i s comminicated by ultrahigh-frequency r a d i o about 1,200 bits-per-second, Communication between remote ground s i t e s , v i a high-speed communications l i n k s , occurs a t about t h e same rate. Houston reads lnf'omation from t h e s e ground s t i e s aG 2,400 bits-per-second, as well a s from remote sites a t 100 words-per-minute. The computer systems perform many o t h e r functions, i n cluding: . . . Assuring t h e q u a l i t y of t h e transmission l i n e s by c o n t i n u a l l y e x e r c i s i n g d a t a paths. Verifying accuracy of t h e messages by r e p e t i t i v e operations, Constantly updating t h e f l i g h t status. For "down l i n k " data, sensors b u i l t i n t o t h e s p a c e c r a f t c o n t i n u a l l y sample cabin temperature, pressure, physical i n f o r mation on t h e a s t r o n a u t s such as h e a r t b e a t and r e s p i r a t i o n , among o t h e r items, These d a t a a r e t r a n s m i t t e d t o t h e ground s t a t i o n s a t 51,2 k i l o b i t s (12,800 binary d i g i t s pe r-second. A t MCC t h e computers: . Detect and s e l e c t changes o r d e v i a t i o n s , compare with t h e i r s t o r e d programs, and i n d i c a t e t h e problem a r e a s o r pertinent data t o t h e f l i g h t controllers. �, Provide d i s p l a y s t o mission personnel, . Assemble output d a t a i n proper formats, , Log d a t a on magnetic t a p e f o r r e p l a y f o r t h e f l i g h t control-lers. . Keep t i m e , The A ~ o l l oS h i ~ s The mission w i l l be supported by f o u r Apollo instrumentat i o n s h i p s o p e r a t i n g a s i n t e g r a l s t a t i o n s of t h e Manned Space F l i g h t Network (MSFN) t o provide coverage i n areas beyond t h e range of land s t a t i o n s , The s h i p s , Vanguard, Redstone, Mercury, and H u n t s v i l l e , . w i l l perform t r a c k i n g , t e l e m e t r y , and communication f u n c t i o n s f o r t h e launch phase, Earth o r b i t i n s e r t i o n , t r a n s l u n a r l n j e c t i o n and r e e n t r y a t t h e end of t h e mission, Vanguard w i l l be s t a t i o n e d about 1,030 m i l e s s o u t h e a s t of Bermuda (25 d e g r e e s N, 49 d e g r e e s W ) t o bridge t h e BermudaAntigua gap during E a r t h o r b i t i n s e r t i o n . Vanguard a l s o f u n c t i o n s as p a r t of t h e A t l a n t i c recovery f l e e t i n t h e event of a launch phase c o n t i w e n c y , The Redstone, a t 14 degrees S , 145.5 degrees E; Mercury, 32 degrees S, 131 d e g r e e s E; and H u n t s v i l l e , 1'7 dee ~ s b i l estations beg r e e s S, 174 degrees W, provide a % r i a n ~ ; lof tween t h e MSFN stations at Carrnarvsn and Hawaii f s eoveTage ~ of t h e burn i n t e r v a l f o r t r a n s l u n a r inJeetion. I n the event t n e launch d a t a slips from May 18, the ships w $ l L a i l move g e n e r a l l y northeastward t o cover the changing flight window patterns. Redstone and H u n t s v i l l e w i l l be r e p o s i t i o n e d along t h e r e e n t r y c o r r i d o r f o r t r a c k i n g , t e l e m e t r y , and communicatfons f u n c t i o n s during r e e n t r y and landing. They w i l l t r a c k Apollo from about 1,000 m i l e s away through comrnunicat i o n s blackout when t h e s p a c e c r a f t w i l l drop below t h e h o r i z o n and w i l l be picked up by t h e A R I A a i r c r a f t , The Apollo s h i p s were develop-d j o i n t l y by NASA and t h e Department of Defense, The DOD oy;(::rates t h e s h i p s - - i n support of Apollo and o t h e r NASA and DOD missions on a non-interference basis w i t h Apollo requirements, Management of t h e Apollo s h i p s i s t h e r e s p o n s i b i l i t y of t h e Commander, A i r Force Western T e s t Range (AFWTR), W e M i l i t a r y Sea T l a n s p o r t S e r v i c e provides t h e m a r i t i m e crews and t h e F e d e r a l E l e c t r i c Corp,, I n t e r n a t i o n a l Telephone and Telegraph, under c o n t r a c t t o AFWTR, provides t h e t e c h n i c a l i n s t r u mentation crews. �The t e c h n i c a l crews o p e r a t e i n accordance w i t h j o i n t NASA/DOD s t a n d a r d s and s p e c i f i c a t i o n s which a r e compatible w i t h MSFN o p e r a t i o n a l procedures. Apollo Range I n s t r u m e n t a t i o n Aircraft (ARIA) The Apollo Range I n s t r u m e n t s t i o n A i r c r a f t w i l l s u p p o r t t h e mission by f i l l i n g gaps i n both land and s h i p s t a t i o n coverage where important and s i g n i f i c a n t coverage requirements exist. During Apollo 10, t h e A R I A w i l l be used p r i m a r i l y t o fill coverage gaps of t h e ?and and s h i p s t a t i o n s i n t h e I n d i a n Ocean and i n t h e P a c i f i c between A u s t r a l i a and Hawaii during t h e t r a n s l u n a r i n j e c t i o n i n t e r v a l , P r i o r t o and d u r i n g t h e burn, t h e A R I A r e c o r d t e l e m e t r y data from Apollo provide a r e a l - t i m e v o i c e communication between t h e a s t r o n a u t s and t h e f l i g h t d i r e c t o r a t Houston. E i g h t a i r c r a f t w i l l p a r t l c i p a t e i n this mission, o p e r a t i n g from P a c i f i c , A u s t r a l i a n and I n d i a n Ocean a i r F i e l d s i n p o s i t i o n s under t h e orbital t r a c k of the s p a c e c r a f t and b o o s t e r . The a i r c r a f t . l i k e t h e t r a c k i n g s h i p s , w i l l be redeployed i n a northeastward d i r e c t i o n i n t h e e v e n t of launch day s l i p s . F o r r e e n t r y , t h e A R I A w i l l be redeployed t o t h e l a n d i n g area t o c o n t i n u e communications between Apollo and Mission Control and provide p o s i t i o n i n f o r m a t i o n on t h e s p a c e c r a f t a f t e r t h e blackout phase of r e e n t r y has passed. The t o t a l A R I A f l e e t f o r Apollo m i s s i o n s c o n s i s t of e i g h t EC-135A ( ~ o e i n g707) j e t s equipped s p e c i f i c a l l y t o meet mission needs, Seven-foot p a r a b o l i c a n t e n n a s have been i n s t a l l e d i n t h e nose s e c t i o n of t h e p l a n e s g i v i n g them a l a r g e , bulbous look. The a i r c r a f t , as w e l l a s f l i g h t and i n s t r u m e n t a t i o n crews, are provided by t h e A i r Force and t h e y a r e equipped through j o i n t A i r Force-NASA c o n t r a c t a c t i o n . A R I A o p e r a t e in Apollo m i s s l o n s i n accordance w i t h MSFN procedures. �Ship Positions f o r Apollo 10 -- 49 degrees W 131 degrees E 145.5 degrees E 172.5 degrees E Insertion Ship I n j e c t i o n Ship I n j e c t i o n Ship I n j e c t i o n Ship Reentry Suppore Reentry Skip (Hw) 25 degrees N 32 degrees S 14 degrees S 20 degrees S 17 degrees S - 174 degrees W I n s e r t i o n Ship I n j e c t i o n Ship I n j e c t i o n Ship Injection ship Reentry Support Reentry Ship (HTV) 25 32 14 13 N S S S I n s e r t i o n Ship (VAN I n j e c t i o n Ship I n j e c t i o n Ship I n j e c t i o n Ship Reentry Support Reentry Ship (HTV) 25 degrees W I n s e r t i o n Ship I n j e c t i o n Ship I n j e c t i o n Ship I n j e c t i o n Ship Reentry Support Reentry Ship (HTV) 25 degrees N Released 3 degrees S 9 degrees M I n s e r t i o n Ship I n j e c t i o n Ship I n j e c t i o n Ship (RED Indection Ship (RED) Reentrg Support Reentry Ship (HTV) 25 degrees N Released 0.5 degrees N 16 degrees N degrees degrees degrees degrees - - 49 degrees W 131 degrees E -- 145.5 degrees E 174 degrees E - - 8 degrees S 173 degrees W - 49 degrees W Released 7.5 degrees S 156 degrees E 1 degree I4 177.5 degrees E - - - 172 degrees W 10 degrees N - - 49 degrees W -175.5 158 degrees E d e ~ r e e sE 15.5 degrees N 22 degrees N - 173 degrees w - 49 degrees W - 161 degrees E - 174 degrees E - 173 degrees W �APOLLO PROGRAM MANAGENEW The Apollo Program, t h e United S t a t e s ' e f f o r t t o land men on t h e Moon and r e t u r n them s a f e l y t o Earth before 1970, i s t h e r e s p o n s i b i l i t y of the O f f i c e of Manned Space F l i g h t (OWSF), National Aeronautics and Space Administration, Washington, D.C. D r . George E. Mueller i s Associlate Administrator f o r Manned Space F l i g h t . NASA Manned Spacecraft Center (MSC), Houston, is r e sponsible f o r development of t h e Apollo s p a c e c r a f t , f l i g h t crew t r a i n i n g and f l i g h t c o n t r o l . Dr. Robert R . Q i l r u t h i s Center D i r e c t o r . NASA Marshall Space F l i g h t Center (MSFC), H u n t s v i l l e , A l a . , i s responsible f o r development o f the Saturn launch vehicles, D r . Wernher von Braun is Center D i r e c t o r . NASA John F. Kennedy Space Center (KSC), F l a . , i s r e sponsible f o r ~ p o l l o / ~ a t u r launch n o p e r a t i o n s . D r . Kurt H. Debus i s Center D i r e c t o r . NASA Goddard Space F l i g h t Center (GSFC), Greenbelt, Md. , manages t h e Manned Space F l i g h t Network under the d i r e c t i o n of the NASA Office of Tracking and Data Acquisition (OTDA). Gerald M. Truszynski i s Associate Administrator f o r Tracking and Data Acquisition. D r . John F. Clark i s Director of GSFC, Apollo/Saturn O f f i c i a l s NASA HEADQUARTERS L t . Gen. Sam C, P h i l l i p s , (USAF) Apollo Program D i r e c t o r , OMSF George H. Hage Apo 110 Program Deputy Director, Mission D i r e c t o r , OMSF Cnester M. Lee A s s i s t a n t Mission D i r e c t o r , OMSF :ol. A s s i s t a n t Mission Director, OMSF Thomas H. McMullen (USAF) Maj. Gen. James W. Humphreys, J r . Director o f Space Medicine, OMSF Norman Pozinsky Director, Network Support Implementation Div. , OTDA �Manned Spacecraft Center George M. Low MBnager, Apollo Spacecraft Program Kenneth S . Kleinknecht Manager, Command and Service Modules B r i g . Gen, C. H. Bolender (USAF) Manager, Lunar Module Donald K. Slayton Director of F l i g h t Crew Operations Chrf stopher C, Kraft , Jr. Director of' F l i g h t Operations Glynn S. Lunney F l i g h t Director Milton L. Windler F l i g h t Director M. P. Frank F l i g h t Director Gerald G r i f f i n F l i g h t Director Charles A. Berry Director of Medical Research and Operations Marshall Space F l i g h t Center Ma3. Gen. Ednn;md P. OtConnor Director of I n d u s t r i a l Operations D r . F. A. Speer Director o f Mission Operations Lee 33. James Manager, Saturn V . Program Off i c e William D. Brown Manager, Engine Program Office Kennedy Space Center Miles Ross Deputy Director, Center Operations Rocco A. Petrone Director, Launch Operations Raymond L. Clark Director, Technisal Support Rear Adm. Roderick 0. Middleton (USN) Manager, Apollo Program Office Walter 3, Kapryan Deputy Director, Launch Operations D r . Hans F. Gruene Director, Launch Vehicle Operations John 3 . Williams Director, Spacecraft Operations �Paul C, DDnnelly Launch Operations Manager Goddard Space Flight Center Assistant Mrector POP Manned Space Flight Tracking - Henry F. Thompson Deputy Assistant Director f o r Manned Space Flight Support H. W i l l i a m Wood Chief, Manned Flight Operations Tecwyn Roberts Chief, Manned F l i g h t Engineering Div. Div. Department of Defense Maj. Gen. Vincent Q . Huston, (USAP) DOD Manager of Planned Space Flight Support Operations Maj. Gen. David M. Jones, (US-) Deputy DOD m g e r of Manned Space Flight Support Operations, Commander of USAF Eastern Test Range Rear A m , F. E. Bakutis, (USW) Commander of Combined Task Force 130, Pacific Recovery Area Rear Adm. P. S. PLcManus, (USN) Commander of Combined Task Force 140, Atlantic Recovery Area Col, Royce G. Olson, (USAF) Director of DOD Manned Space Flight Office Brig. Gen. Allison C. Brooks, Commander Aerospace Rescue and Recovery Service (USAP) �Pllajor Apollo/Satucn V Contractors Contractor Item Bellco~pn Washington, D, C. Apollo Systems Engineering The Boeing Co. Washington, D. C, Technical I n t e g r a t i o n and Evaluation General E l e e t r i c -Apollo Support Dept,, Dagtona Beach, Bla, Apollo Checkout, and Quality and Reliability North American Rockwell Corp. Space D i v e , Downey, Callf. Command and S e w i c e Modules Grumman A i r c r a f t Engineering Corp, , Bethpage, N. I. Lunar Module Massachusetts I n s t i t u t e of Technology, Cambridge, Mass. Guidance h Navigation (Technical Management) General Motors Corp., AC Electronics Div., Milwaukee, W i s . Guidance & Navigation (~anufacturing) TRW Systems Inc. Trajectory Analysis Redondo Beach, C a l i f . Avco Corp., Space Systems D i v . , L o w e l l , Mass, H e a t Shield Ablative Material North American Rockwell Corp, Rocketdyne D i v . Canoga Park, Calif. 3-2 Engines, F-1 Engines The Boeing Co. Mew Orleans F i r s t Stage (SIC) of Saturn V Launch Vehicles, Saturn V Systems Engineering and Integration, Ground Support Equipment North American Rockwell Corp, Space Div, Seal Beach, Calif. Development and Production of S a t u r n V Second Stage (s-11) McDonnell Douglas Astronautics Co. Huntington Beach, Callf. Development and Production of Saturn V . Third Stage (s-IVB) �International Business Machines Federal Systems Div, Huntsville, Ala. Instrument Unit Bendix Corp. Navigation and Control Div. Teterboro, N . 3 . Guidance Components for Instrument Unit (Includin Stabilized Federal Electric Corp. Communications and Instrumentation Support, KSC Bendix Field Engineering Corp. Launch Operations/Complex Support, KSC Catalytic-Don Facilities Engineering and Modifications, KSC Hamilton Standard Division United Aircraft Corp. Windsor Locks, Conn. Portable Life Support System; LM ECS IiC Industries Dover, Del. Space Suits Radio Corp. of America Van Nuys, Calif. llOA Computer Sanders Associates ACashua, N . H . Uperat iona1 Display Systerns Brown Engineering Huntsville, Ala. Discrete Controls Reynolds, Smith and Hill Jacksonville, Fla. Engineering Desfgn of Moblle Launchers Ingalls Iron Works Birmingham, Ala. Mobile Launchers (ML) (structural work) Srnith/Ernst (foint Venture) Tampa, Fla. Washington, D, C. Electrical Mechanical Portion Power Shovel, Inc. Marion, Ohio Transporter Hayes International Birmingham, Ala Mobile Launcher Service Arms . - Saturn Checkout Saturn of E4Ls �APOLLO GLOSSARY Ablating Materials--Special heat-dissipating materials on the surface of a spacecraft that vaporize during veentry. Abort--The unscheduled ternination of a mission prior to its completion, Accelerometer--An instrument to sense accelerative forces and convert them into corresponding electrical quantities usually for controlling, measuring, indicating or recording purposes. Adapter Skirt--A flange or extension of a stage or section that provides a ready meaner of fitting another stage or section to It. Antipode--Point on surface of planet exactly 180 degrees opposite from reciprocal point on a line projected through center of body. In Apollo usage, antipode refers to a line from the center of the Moon through the center of the Earth and projected to the Earth surface on the opposite side. The antipode crasses the mid-Pacific recovery line along the 165th meridian of longitude once each 24 hours. Apocynthion--Point at which object In luna orbit is farthest from the lunar surface object having been launched from body other than Moon. ( , Romm goddess of Moon) -- Apogee--The point at which a Moon or artificial satellite in its orbit is farthest from -rth. Apolune--Point at which object launched from the Moon into lunar orbit is farthest from lunar surface, e,g.: ascent stage of lunar module after staging into lunar orbit fillowing lunar landing . Attitude--The position of an aerospace vehicle as detemined by the inclination of its axes to some frme of reference; for Apollo, an Inertial, space-fixed reference is used. Burnout--The point when combustion ceases in a rocket engine. Canard--A short, stubby wing-like element affixed to the launch escape tower to provide CM blunt end forward aerodpamic capture durlng an abort. Celestial Guidance--me guidance of a vehicle by reference to celestial bodies. �C e l e s t i a l Mechanics--The science t h a t d e a l s primarily with t h e e f f e c t of force as an agent i n determining the o r b i t a l p a t h s of c e l e s t i a l bodies. Cislunar--Adjective r e f e r r i n g t o space between Earth and t h e Moon, o r between Earth and Moon18 o r b i t . Closed Loop--Automatic c o n t r o l u n i t s 1l.nked t o g e t h e r w i t h a process t o form an endless chain, Deboost--A retrograde maneuver which lowers either perigee o r apogee of an o r b i t i n g s p a c e c r a f t , Not t o be confused with deorbit. &elination--Angular measurement of a body above o r below c e l e s t i a l equator, measured n o r t h o r south along t h e body's hour c i r c l e . Corresponds t o Earth surface l a t i t u d e . Delta V--Velocity change. D i g i t a l Computer--A computer i n which q u a n t i t i e s a r e represented numerically and which can be used t o solve complex problems, Down-Link--The part o f a communication system t h a t r e c e i v e s , proc e s s e s and d i s p l a y s d a t a from a s p a c e c r a f t . E n t r y Corridor--The f i n a l f l i g h t path of the s p a c e c r a f t before and during Earth r e e n t r y . Ephemeris--Orbital measurements (apogee, perigee, i n c l i n a t i o n , period, e t c . ) of one c e l e s t i a l body i n r e l a t i o n t o another a t given times. I n s p a c e f l i g h t , t h e o r b i t a l measurements of a s p a c e c r a f t r e l a t i v e t o the c e l e s t i a l body about which it orbited. Escape Velocity--The speed a body must a t t a i n t o overcome a g r a v i t a t i o n a l f i e l d , such as t h a t of Earth; t h e v e l o c i t y of escape a t the E a r t h ' s s u r f a c e i s 36,700 feet-per-second, Explosive Bolts--Bolts destroyed o r severed by a surrounding explosive charge which can be a c t i v a t e d by an e l e c t r i c a l impulse, Fairing--A piece, p a r t o r s t r u c t u r e having a smooth, streaml i n e d o u t l i n e , used t o cover a nonstreamlined o b j e c t o r t o smooth a junction. P l i g h t Control System--A system t h a t s e r v e s t o maintain a t t i t u d e s t a b i l i t y and c o n t r o l during f l i g h t , �Fuel Cell--An electrochemical generator i n which t h e chemical energy from t h e reaction of oxygen and a fuel La converted d i r e c t l y i n t o e l e c t r i c i t y . e x e r t e d upon an o b j e c t by gravity o r by r e a c t i o n t o a c c e l e r a t i o n o r d e c e l e r a t i o n , as In a change o f d i r e c t i o n : one g is t h e measure o f f o r c e required t o a c c e l e r a t e a body a t t h e rate of 32.16 feet-per-second. g o r g Force--Force on a Gimbaled Motor--A rocket motor mounted on gimbal; 1.e.: contrivance having two mutually perpendicular axes o f rot a t i o n , so as t o o b t a i n p i t c h i n g and yawing c o r r e c t i o n moments. Guidance System--A system which measures and e v a l u a t e s f l i g h t information, c o r r e l a t e s t h i s with t a r g e t d a t a , converts t h e r e s u l t i n t o t h e conditions necessary t o achieve t h e d e s i r e d f l i g h t path, and communicates t h i s d a t a i n t h e form of commands t o t h e f l i g h t c o n t r o l system. Heliocentric--Sun-centered Sun a t i t s c e n t e r . o r b i t o r o t h e r a c t i v i t y which h a s the I n e r t i a l , Guidance --Guidance by means o f t h e measurement and i n t e g r a t i o n of a c c e l e r a t i o n from on board t h e s p a c e c r a f t . A s o p h i s t i c a t e d automatic navigation system using gyroscopic devices, accelerameters e t c . , for high-speed v e h i c l e s . It absorbs and i n t e r p r e t s such d a t a a s speed, p o s i t i o n , e t c . , and automatically a d j u s t s t h e vehicle t o a pre-determined f l i g h t path. E s s e n t i a l l y , i t knows where i t ' s going and where it i s by knowing where i t came from and how i t g o t t h e r e . It does n o t give out any r a d i o frequency s i g n a l ao i t cannot be detected by r a d a r o r jammed. Injection--The process of boosting a s p a c e c r a f t i n t o a calculated trajectory. Insertion--The process o f boosting a s p a c e c r a f t i n t o an o r b i t around the Earth o r o t h e r c e l e s t i a l bodies. Multiplexing--The siaiultaneous transmission of two o r more s i g n a l s within a s i n g l e channel. The t h r e e b a s i c methods of multiplexing involve t h e s e p a r a t i o n of s i g n a l s by time d i v i s i o n , frequency d i v i s i o n and phase d i v i s i o n . O p t i c a l Navigation--hlavlgation by s i g h t , as opposed t o i n e r t i a l methods, using stars o r o t h e r v i s i b l e o b j e c t s as reference. Oxidizer--In a rocket p r o p e l l a n t , a substance such as l i q u i d oxygen o r n i t r o g e n t e t r o x i d e which supports combustion of the mel. �Penumbra--Semi-dark portion of a shadow in which light is partly cut off, e .g. : surface of Moon or Earth away from Sun where the disc of the Sun is only partly obscured, Pericynthion--Point nearest Moon of object In lunar orbit--object having been launched fron body other than Moon. Perigee--Point at which a Moon or an artificial satellite I n its orbit is closest to the Earth. Perilune--The point at which a satellite ( e , g . : a spacecraft) in its orbit is closest to the Moon. Differs from pericynthion in that the orbit is Moon-originated. Pitch--The movement of a space vehicle about an axis (Y) that is perpendfcular to its longitudinal axis. Reentry--The return of a spacecraft that reenters the atmosphere after flight above it. Retrorocket--A rocket that gives thrust in a direction opposite to the direction of the object's motion. - Right Ascension -Angu lar measurement of a body eastward alon the celestial equator Prom the vernal equinox (0 degrees RAY to the hour circle of the body. Correaponds roughly to Earth surface longitude, except as expressed in hrs:min:sec instead of 180 degrees west and east from 0 degrees (24 hours-360 degrees) . Roll--The movements of a space vehicle about its longitudinal (x) axis. S-Band--A radio-frequency band of 1,550 to 5,200 megahertz. Selenographic--Adjective relating to physical geography of Moon. Specifically, positions on lunar surface as measured in latitude from lunar equator and in longitude from a reference lunar meridian. Selenocentric--Adjective referring to orbit having Moon as center. (~elene,Or. Moon) Sidereal--Adjective relating to measurement of time, position or angle in relation to the celestial sphere and the vernal equinox. State vector--Ground-generated spacecraft position, velocity and timing information uplinked to the spacecraft computer for crew use as a navigational reference. �Telemetering-A system for taking measurements within an aerospace vehicle in flight and transmitting them by radio to a ground station. Terminator--Separation line between lighted and dark portions of celestial body which is not self luminous. Ullage--me volme in a closed tank or container that is not occupied by the stored liquid; the ratio of this volume to the total volume of the tank; also an acceleration to force propellants into the engine pump intake lines before ignition. Umbra--Darkest part of a shadow in which light is completely absent, e-g.: surface of Moon or Earth away from Sun where the disc of the Sun l a completely obscured. Update pad--Information on spacecraft attitudes, thrust values, event times, navigational data, etc., voiced up to the crew in standard formats according to the purpose, e.g,: maneuver update, navigation check, landmark tracking, entry update, etc. Up-Link Data--Information fed by radio signal from the ground to a spacecraft . Yaw--An l a r displacement of a space vehicle about its vertical ( zraxis . �APOLLO ACRONYMS AND AIEIBREVIATIONS (Note: This l i s t makes no attempt t o inelude a l l Apollo program acronyms and abbreviations, but s e v e r a l are l i s t e d t h a t w i l l be encountered frequently i n the Apsllo 10 mission. Where pronounced a s words i n a i r - t o -ground transmissions, acronyms a r e phonetically shown i n parentheses. Otherwise, abbreviations a r e sounded out by l e t t e r . ) AGCS (At3gs ) Apogee kick AK APS Abort Guidance System ( W ) (APP~) Aacent Propulsion System (LM) Awtiliaqy Propulsion System (S-IVB s t a g e ) (Be-WZ) Body mounted a t t i t u d e gyro CBSf Constant delta height CMC Cornand Module Computer COI Contingency o r b i t i n s e r t i o n CRS Concentric rendezvous sequence CSI Concentric sequence i n i t i a t e DAP (~PP) Digital autopilot DEDA ( Dee -da ) Data Entry and Display Assembly (MIAQS) DFI Development f l i g h t instrumentation DO1 Descent o r b i t i n s e r t i o n DPS ( Dips Descent propulsion system DSKY ( isk key ) Display and keyboard EPO Earth Parking O r b i t FDA1 Flight director attitude i n d i c a t o r FIllI (Fith) F i r e In the hole (LM ascent a b o r t staeing) Fixed t h r o t t l e point High-gain antenna I n e r t i a l measurement u n i t �APOLLO ACRONYMS AND ABBREYIATIONS (Note: T h i s l i s t makes no attempt t o include a l l Apollo program acronyms and abbreviations, but s e v e r a l a r e l i s t e d t h a t w i l l be encountered frequently i n the Apollo 10 mission. Where pronounced a8 words i n air-to-ground transmissions, acronyms a r e phonetically shown irP parentheses. Otherwise, abbreviations a r e sounded out by l e t t e r ) . Abort Guidance System ( W ) Apogee kick APS B31AQ A ~ c e n tPropulsion System (IN) Auxiliary Propulsion Sy~rtem(s-IVB atage) (Bee--) Body mounted a t t i t u d e gyro Constaikt d e l t a height CMC Cormnand Module Computer Contbgency o r b i t i n s e r t i o n CRS Concentric rendezvous sequence CSI Concentric sequence i n i t i a t e DAP Digital autopilot DEDA Data Entry and Display Assembly (LM AM) DFI 1)evelopment f l i g h t instrumentation Descent o r b i t i n s e r t i o n DPS Descent propulsion system DSKY Display and keyboard EPO Earth Parking O r b i t Flight director attitude indicator FITH F i r e in the hole (LM ascent abort staging PPP Fixed t h r o t t l e point High-gain antenna I n e r t i a l measurement u n i t �IRIO I n e r t i a l ra%e i n t e g r a t i n g gyro LO1 Lunar o r b i t f n s s r t i o n LPO Lunar p a r k i w o r b i t MCC Misaion Control Center MC&W Master caution and warning MSI Moon sphere of influence MTVC Manual t h r u s t vector c o n t r o l NCC Combined c o r r e c t i v e maneuver NSR C o e l l i p t i c a l maneuver PIPA ( f ippa) Pulse i n t e g r a t i ~pendulous accelerometer PLSS (~lisro) Portable l i f e support system Passive the PTC mas (Pugs) Propellant u t i l i z a t i o n and gaging systern REFSWT ( ~ esmat) f Reference t o s t a b l e member matrix RHC Rotation h m d c o n t r o l l e r R E Real-time a s SCS S t a b i l i z a t i o n m d c o n t r o l system SLA Spacecraft LM adapter SPS Service p r o ~ l s i o nsystem TEI Transearth I n j e c t i o n THC Thrust hand c o n t r o l l e r TLI Translunar InJection TPF Terminal phase f i n a l i z a t i o n TPI Terminal phase I n i t i a t e TVC Thrust vector c o n t r o l d �CONVERSION FACTORS Multiply 2 To Obtain feet 0,3048 meters Distance : feet kilometers feet kilometers statute miles statute miles kilometers nautical miles kilometers nautical miles statute miles statute miles nautical miles statute mile yards feet/sec meters/sec Velocity: feet/sec statute mph statute miles/hr nautical miles/hr statute miles/hr 1.609 km/hr nautical miles/hr (knots) 1.852 km/hr statute miles/hr Liquid measure, werkht : gallons liters liters gallons pounds kilograms kilograms pounds - more - �Multiply 8 To Obtain cubic f e e t 0.02832 cubic meters pounds/sq i n c h 70.31 grarns/sq cm Volume : Pressure : � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000071 Title A name given to the resource Apollo 10 press kit. Description An account of the resource The press kit includes documentation on the Command and Service Module, Lunar Module, Saturn V launch vehicle, astronauts, and mission descriptions. Release No. 69-68. Creator An entity primarily responsible for making the resource United States. National Aeronautics and Space Administration Date A point or period of time associated with an event in the lifecycle of the resource 1969-05-07 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Project Apollo (U.S.) Space flight to the moon Saturn launch vehicles Saturn Project (U.S.) Type The nature or genre of the resource Press kits Text Source A related resource from which the described resource is derived Saturn V Collection Box 31, Folder 30 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000051_000074 https://digitalprojects.uah.edu/files/original/20/1154/spc_stnv_000070.pdf 070649e619faa748137a414c5949aa33 PDF Text Text Apollo IO/AS-505Mission X I L/ 7 Final Rehearsal for the Manned Lunar Landing Apollo 10 is a demonstration of the ability of all launch vehicle, spacecraft and ground support systems to perform their assigned functions. The mission will mark the first flight of the complete Apollo spacecraft (CMISMILM) in deep space and in the lunar environment. Spacecraft maneuvers are the same as those to be employed on the first manned lunar landing, except that there will be no LM final descent or landing. IBM Space Systems Center Huntsville, Alabama Mission Statistics Crew Duration (approximate): 192 Hours, 04 Min Orbit (Earth Parking): 100 NM Number of Planned Revolutions: 2 or 3 Lunar Orbit: 60 x 170 NIM Number of Planned Revolutions: 2 Lunar Orbit: 60 NM Circular Number of Planned Revolutions: 28 Thomas P. Stafford (Commander) Eugene A. Cernan (Lunar Module Pilot) John W. Young (Command Module Pilot) Notes if- � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000070 Title A name given to the resource Apollo 10/AS-505 mission chart. Description An account of the resource The chart includes diagrams, mission statistics, crew, and notes. There is an additional copy in the David Christensen Collection. Creator An entity primarily responsible for making the resource International Business Machines Corporation. Space Systems Center Date A point or period of time associated with an event in the lifecycle of the resource 1969-05 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Project Apollo (U.S.) Space flight to the moon Saturn launch vehicles Saturn Project (U.S.) Type The nature or genre of the resource Diagrams Text 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_000051_000074