49 20 970 https://digitalprojects.uah.edu/files/original/20/11154/Deciprocforminicost_100107112756.pdf 07915480c1aafcb520dfb0e96c52d7d5 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket. Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite. A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used. Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context Deciprocforminicost_100107112756.pdf spc_stnv_000227 Title A name given to the resource "Decision Procedure for Minimizing Costs of Calibrating Liquid Rocket Engines." Description An account of the resource Prior to acceptance of a liquid rocket engine for use in Saturn vehicles, the average thrust of two consecutive tests without an intervening calibration must satisfy specification requirements. The contractor may recalibrate after the first and subsequent tests if he so chooses, based upon decision limits, until the above requirement is met. Creator An entity primarily responsible for making the resource Lishman, Sidney H. Bombara, E. L. Date A point or period of time associated with an event in the lifecycle of the resource 1965-10-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Calibrating Liquid propellant rocket engines Saturn project Type The nature or genre of the resource Text Essays Source A related resource from which the described resource is derived Saturn V Collection Box 15, Folder 9 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_000225_000249 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. <a href="http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17340"> View this item in ArchivesSpace </a> https://digitalprojects.uah.edu/files/original/20/11155/descst124minerstab.pdf.pdf 498c9649b1614c1582ca1dff9290294c Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket. Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite. A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used. Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context descst124minerstab.pdf spc_stnv_000231 Title A name given to the resource "A description of the ST-124M inertial stabilized platform and its application to the Saturn V launch vehicle." Description An account of the resource This report is a description of the ST-124M inertial stabilized platform system and its application to the Saturn V launch vehicle. It is a summary report providing the system concept, and not a theoretical presentation. Mathematical equations were included only where necessary to describe the equipment; however, the detailed derivations supporting these equations were not presented since this was not the theme of the paper. Creator An entity primarily responsible for making the resource O'Connor, B. J. Date A point or period of time associated with an event in the lifecycle of the resource 1964-06-26 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Inertial guidance Inertial platform Saturn launch vehicles Type The nature or genre of the resource Text Reports Source A related resource from which the described resource is derived Saturn V Collection Box 11, Folder 38 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_000225_000249 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. <a href=" http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17003"> View this item in ArchivesSpace </a> https://digitalprojects.uah.edu/files/original/20/11156/Devsatsys.pdf.pdf 465fbbc3adb2933a2ca96aad5ce44522 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket. Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite. A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used. Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context Devsatsys.pdf Title A name given to the resource "The development of the Saturn system safety program." Description An account of the resource This paper describes the major highlights or milestones passed in the development of a System Safety Program at MSFC since early 1967. it discusses accomplishments, problems resolved, and decisions made for Apollo Saturn vehicles AS-501 and AS-502, and projects that are to be accomplished on future Saturn vehicles. Creator An entity primarily responsible for making the resource Farish, Preston T. George C. Marshall Space Flight Center. Future Projects Office Date A point or period of time associated with an event in the lifecycle of the resource 1961-06-10 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Apollo project Aerospace safety System safety Type The nature or genre of the resource Text Essays Source A related resource from which the described resource is derived Saturn V Collectin Box 26, Folder 27 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_000225_000249 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. <a href="http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17874"> View this item in ArchivesSpace </a> https://digitalprojects.uah.edu/files/original/20/11157/commbulkdraw.jpg.jpg 51307e395a223b9a504aebfc242aea61 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket. Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite. A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used. Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context commbulkdraw.jpg Title A name given to the resource "Common bulkhead drawing." Description An account of the resource 8 x 10 inch black and white photograph; This is a cutaway drawing of the bulkhead with information about the LH2 tank skin, insulation, Aft LOX bulkhead, 2014-T6 alum skin and fiberglass core. Part of an envelope with photos accompanying C. E. Cataldo paper "Materials in Space Exploration." Creator An entity primarily responsible for making the resource George C. Marshall Space Flight Center. Aero-Astrodynamics Laboratory United States. National Aeronautics and Space Administration Date A point or period of time associated with an event in the lifecycle of the resource 1960-01-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Spacecraft construction materials Liquid propellant engines Apollo project Type The nature or genre of the resource Still Image Illustrations 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_000200_000224 https://digitalprojects.uah.edu/files/original/20/11158/compflowcont.pdf.pdf 20bd0806b47e4b5378e9774a6b2f4d14 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket. Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite. A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used. Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context compflowcont.pdf Title A name given to the resource "A comparison of four control systems proposed for Saturn V launch vehicles." Alternative Title An alternative name for the resource. The distinction between titles and alternative titles is application-specific. X-53572 Description An account of the resource Presented are the results of a study comparing four proposed control systems for the first stage flight of Saturn V launch vehicles. The primary basis of comparison is the effect on structural loads, using the bending moments at three stations as load indicators. Two of the systems sense only the vehicle attitude and attitude rate, while the other two systems also sense the lateral acceleration. A yaw plane wind response analysis, including rigid body translation, rigid body rotation, four bending modes, five slosh modes, and a non ideal control system, was performed. The winds used in the study were the Marshall synthetic profile and three selected Jimsphere-measured real wind profiles. Load relief obtained from the addition of accelerometer feedback in the control loop amounted to about 10 percent at maximum bending moment station. In view of predicted structural capabilities of the vehicle, this reduction in loads was not considered sufficient to offset the added complexity and the slight reduction in rigid body stability . Creator An entity primarily responsible for making the resource Sumrall, Phil George C. Marshall Space Flight Center. Aero-Astrodynamics Laboratory Date A point or period of time associated with an event in the lifecycle of the resource 1967-02-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Saturn launch vehicles Saturn 5 launch vehicles Testing Spacecraft control Type The nature or genre of the resource Text Essays Source A related resource from which the described resource is derived Saturn V Collection Box 20, Folder 36 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_000200_000224 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. <a href="http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17619"> View this item in ArchivesSpace</a> https://digitalprojects.uah.edu/files/original/20/11159/conditions.jpg.jpg 71c1300017478802d3c7bdb631c22657 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket. Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite. A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used. Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context conditions.jpg spc_stnv_000209 Title A name given to the resource "Conditions contributing to stress corrosion [list] photograph." Description An account of the resource 8 x 10 inch black and white photograph. A photograph of a list of things contributing to stress corrosion. Referenced by "Materials in Space Exploration." Is part of envelope containing photos accompanying C. E. Cataldo paper "Materials in Space Exploration." Creator An entity primarily responsible for making the resource George C. Marshall Space Flight Center United States. National Aeronautics and Space Administration Date A point or period of time associated with an event in the lifecycle of the resource 1960-01-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Apollo project Liquid propellant rockets Spacecraft construction materials Stress corrosion Type The nature or genre of the resource Still Image Photographs 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_000200_000224 https://digitalprojects.uah.edu/files/original/20/11160/corrprobasso.pdf.pdf d1dab3427805e471b46848a2f1d6ca75 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket. Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite. A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used. Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context corrprobasso.pdf spc_stnv_000221 Title A name given to the resource "Corrosion problems associated with the Saturn space vehicles." Description An account of the resource Corrosion problems associated with space vehicles, in general, are discussed as contrasted to those problems experienced with structures in an earth atmosphere. Primary emphasis is placed on structural alloys in this discussion, although some corrosion failures experienced in various mechanical components are described. General corrosion prevention measures are indicated, and solutions to specific corrosion failures described. Major failures experienced have been attributed to stress corrosion cracking, rather than general or galvanic type corrosion. Most such failures have occurred with only five different materials: three aluminum alloys - 7075-T6, 7079-T6, and 2024-T6; and two precipitation hardening stainless steels - 17-7PH and AM 355. Corrective actions were different in each case, but involved either a complete change to another material, a change to a different temper of the same alloy, or a modification of the heat treatment and/or general processing techniques. General conclusions are that the types of failures described could be avoided by: a more suitable selection of alloys in the initial design, a realistic review of the environments that could be encountered in the service lifetime of the component, lowering stresses, improving process controls, and effecting better familiarization of design personnel with the with the overall stress corrosion problem in an effort to reduce human error.; Preprint 18e.; Materials for re-entry and spacecraft systems - spacecraft materials.; Materials Conference, Philadelphia, Pennsylvania, March 31 - April 4, 1968. Creator An entity primarily responsible for making the resource Williamson, J. G. Date A point or period of time associated with an event in the lifecycle of the resource 1962-02-20 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Spacecraft construction materials Saturn 5 launch vehicles Corrosion Type The nature or genre of the resource Text Essays Source A related resource from which the described resource is derived Saturn V Collection Box 26, Folder 20 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_000200_000224 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. <a href="http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17867">View this item at ArchivesSpace </a> https://digitalprojects.uah.edu/files/original/20/11161/Mastplanfordocu.pdf dbc995cb309c76cadf9d4e78c01d8dff Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket. Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite. A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used. Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context Mastplanfordocu.pdf Title A name given to the resource "Master plan for documentation management and use." Description An account of the resource The objective of this study is to describe a comprehensive plan for the development and full utilization of methods and means to be employed in the years prior to 1976 for the effective acquisition, collection, storage, retrieval, distribution, and use of engineering documentation. Because of the violently changing state of the art of data acquisition, storage, and retrieval the description of the plan does not embrace the details of a total decade of phased change. Rather it describes actions that can and should be taken in the relatively near future, and proposes a continuing series of later studies to keep this plan current for the full decade. Creator An entity primarily responsible for making the resource The Radio Corporation of America Date A point or period of time associated with an event in the lifecycle of the resource 1966-08-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Apollo project Aerospace industries--Information resources management Information resources management Documentation Type The nature or genre of the resource Text Essays 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_000425_000449 https://digitalprojects.uah.edu/files/original/20/14405/sdsp_skyl_000070_001.pdf 6f3336e8a030ae106ffaa691253d0a67 PDF Text Text n SPER^Y RAI\D EARTH ORBITAL WORKSHOP CAPABILITIES BROCHURE SPACE SUPPORT DIVISION ��=6= ^SPER^Y RAfSD SECTION I INTRODUCTION SPACE SUPPORT DIVISION �I I Hm •I . I I1 I I I �INTRODUCTION The Sperry Rand Space Support Division presents t h i s brochure t o depict a competence and capability in the area of large earth-orbita I workshops. Workshops that are: ® In fabrication (ATM) • Proposed for Saturn V Vehicles (B0 6 • Conceptually designed (Nuclear Power) for specific advanced applications Sperry's ability to offer a depth of experience in the orbital workshop area is directly attributable to the technical Division is technical Mx) support the Space Support p r o v i d i n g t o t h e MSFC A s t r i o n i c s L a b o r a t o r y . In this role a foundation and competence in design and deveIopment of orbital workshops has been established. The Apollo Telescope Mount provided the hardware, subsystem and system experience. Then follow-on studies developed the necessary mission analysis experience. Hence, an overall capability has evolved. The areas of demonstrated proficiency are: I. EXPERIMENTATION X-Ray Telescope Design X-Ray Camera Design Television System Design Laser Research I I . POWER Solar Array Design Nucleonics Analysis Fuel Cell Design I I I . COMMUNICATIONS Data Compression Studies Information Coding Techniques Studies Modulation Techniques Studies Phase lock Loop Analysis Phase Compensat ion Analysis Hardware Design Antenna Systems Pulse Code Modulated Data Acquisition Systems Telemetry Ground Station i workshop ��270-ChanneI Multiplexer Single Side Band Double Side Band Filters Airborne Telemetry Pouier Supplies IV. CONTROL Control Moment Gyro System Analysis Experiment Pointing Control Analysis Control System Analysis and Design ATM Orbital Workshop Reaction Control Jets Sizing Fuel Consumption Momentum Dumping Optimal Backup Star Tracker Anulysis A summary of ience the engineering effort related to orbital workshop exper is presented in the Capabilities tion there are four Section (Section II). In that sec s u b s e c t i o n s w h i c h a r e u n i q u e l y c a t e g o r i z e d by NASA's Phased Project Planning. The four steps of Phased Project Planning are Advanced Studies, Project Definition, Design. and DeueIopment and Ope rations Categorized as Phase A. B. C and D respectiueIy. The remainder of the brochure provides an insight background, organization makeup and manpower into the Division's level. The capabilities reported herein were developed by the Space Support Division under Contract NAS8-20055 t o the National Administration. George C. Marshall oratory. Huntsv i I le . Alabama. Aeronautics and Space Space Flight Center. Astrionics Lab ��II. WORKSHOP CAPABILITIES SUMMARY TABLE OF CONTENTS Phase Page A Advanced Studies 2-1 B Project Definition 2-0 C Design 2-/5 0 Deuelopment and Operations 2-23 iu ��WORKSHOP CAPABILITIES SUMMARY PHASE A - ADVANCED STUDIES In the Advanced Study Phase concept mission approaches are made. Requirements feasibility studies of for each are analyzed, engineer ing assessed and exper iment programs grossly defined. written detailing all various From t h i s a report analytical work, alternate solutions, tradeoff is cri teria and recommendations. The Phase A definition adequate I y defines the work Space Support Division's Advanced onics Studies Group Laboratory's Advanced Studies Office. performed by the in support of the Astri- The recent studies as docu mented by Sperry are: /I S t u d y o f Eq u i p m e n t s ' the Backup Saturn I Workshops Potential (AS2I0 Wet Launch) Astr ionic for use in an Austere Dry Launch Saturn V IVorbshop (B) An investigation into the system and sub-system modifications required t o ad a p t t h e S a t u r n I u Wet Launch" workshop's backup eauipment to an aus tere Saturn V "Dry Launch" workshop was performed. Convers ion time, cost and mission scheduling were traded off against versatiIity and l i f t capa bility. SP 590-0132 Completion date: Selected Studies of 9/68 Some Conceptual Earth-OrbitaI Workshops Systems analysis and trade-off studies were made on a number of con ceptual earth-orbital workshops in an effort t o size systems and obtain the best configuration. Areas studied tems. included experiment payload, instrumentation and communications, thermal power sys controls, control and display, and video imaging. SP 590-0098 Completion date: Attitude Control System Synthesis for Conceptual 7/68 Saturn V Launched Earth-Orbita I Workshop/Space Stations Identified Eight Conceptual Workshop/Space Station configurations and studied in detail four t o determine overall attitude control requirements to be expected. Then, using these requirements two potential attitude con trol systems are synthesized. 2-1 ��General concepts were derived from NASA's current Saturn V Earth-Orbital Workshop/Space Station planning a c t i v i t i e s . Disturbance torques considered are gravity gradient, aerodynamic, solar, magnetic and man motion. The c o n t r o l jets, control systems included reaction control moment gyros and various combinations of both. SP 590-0097 7 68 Completion date: Microwave Power Transmission Study for Space Applications Considered the feasibility of transmission of power by microwave beaming from a master s a t e l l i t e t o one or more smaller s a t e l l i t e s . Theoretical quantitative results are presented detailing the efficiency of and each sub system plus total system efficiency using either the e l l i p t i c or the para bolic reflector antenna. SP 590-0072 Completion date: 4/68 Signal-to-Noise Considerations for Orbiting Astronomical Presented data that helps provide fundamental X-Ray Telescope information on establish ment of c r i t e r i a t o postulate on the temperature, density and composition of matter in the galactic and intergaI act i c space, presence and strength of magnetic and electric fields in space, the origin and distribution of cosmic rays and the creation of matter. SP 599-0110 Completion date: 8 68 Large Aperture Telescope: Phase I , 2 , 3 . 4 and Summary Performed control system analysis on suggested high accuracy large aperture telescopes. The studies were confined t o the fine pointing control cf a one meter diameter large aperture telescope mounted on an SIVB type orbital workshop. The pointing accuracy of the systems analyzed is 0.01 arc second maintained for extended periods of time. A two body analog simulation was developed t o t e s t the various hardware configurations and evaluate the effects of disturbances, motion, on pointing accuracy. SP 5 9 0 - 0 0 3 4 - 0 . I . 2 . 3 . 4 Completion date: 2 - 3 including man 5/68 �H— O C <3 n. E — - —. *— *S. E 3 U CN 3 </L T3 <3 L. 3% 3> L. CM C 1 X 3* -a "«3 TU E E L. O I— O O M—. 4a E "3 CM V* 3 H—. O CM TCM A E <3 B V* <3 3> 3 U T3 4a 3> «- 3 Ci. C »— c o CM o o •> c o «/-> •— CN 4* —— 3 N—w 3 CM </» a. o L. o -C CM 3* — <M % 4a 2-4 �Phased Array Antenna Study - Phase A comprehensive study of I and II the characteristics of phased arrays was per formed. State-of-the-art information is presented from the literature on weight, s i z e . gain, number of elements, scan and efficiency. Also detailed is the pattern effect due to radiator mis location caused by manufacturing errors and thermal gradients. SP 590-0108 Completion date: 8 68 SP 590-0134 Completion date: 9/68 Boom Extended Nuclear (Orbiting) Reactor Control In suggesting nuclear reactors of vehicle control came t o the for Study large space stations the question forefront. This study endeavers to answer that question by considering the reactor mounted on a boom extended the side or end of from the vehicle. An investigation into the i n t e r r e l a t i o n s between the boom mounted re actor and the vehicle control system was performed. Analog and Digital s imulation programs were developed t o compute external disturbance torques, composite mass and inertia data. In addition, a complete two-body vehicle dynamic simulation containing a vehicle control verify analytical system was developed t o results. SP 209-01 Completion date: An investigat ion of Sensors S trapdown inertial stations of the 12/68 Redundancy Concepts Applied to Strapdown navigators appear to have a place in large put with the mean output of trade-offs <aturn sensor out all the sensors. program was developed t o study various approaches and evaluate in the detection and isolation of SP 590-C084 Mod i f i e d space future. A study input, t o system development, was a method to detect and isolate defective sensors by comparing individual A digital Inertial sensor ma I f u n c t i o n s . Completion date: IV Six Degree Dynamical Simulations with 7/68 Iterative Guidance for Advanced Vehicles and Missions Strap-on solid fuel e n g i n e s . and variable thrust liquid Saturn V vehicles without the SI I stage fuel engines are analyzed to determine impact on ��the present guidance modes. veloped utilizing the Full scale digital simulations haue been de l a t e s t MARVESS t r a j e c t o r y techniques making l i f t - o f f to injection studies possible. SP 209-TD-04 Completion date: I 69 ��W O R K S H O P C A P A B I L I T I E S SUMMARY PHASE 8 - PROJECT DEFINITION In the project defin i t ion phase selected concepts are refined, assess ments o f t o t a l miss ion requirements are made and a system analysis prepared. From the study results presented a project plan emerges which specifies a single concept, recommends a plan for phase C and presents a preliminary Project DeueIopment Plan. The Sperry Rand Space Support Diuision by supporting the Astrionics Laboratory on the Apollo Telescope Mount Vehicle (ATM) was an integral part of t h e ATM Phase B endeauor. T h i s produced e x p e r i e n c e by a s s o c i a t i o n w h i c h , in our opinion, gives a depth of knowledge in the area of large orbital space station technology obtainable only by day-to-day contact with the cognizant NASA o r g a n i z a t i o n s . A sampling of r e p o r t s a p p l i c a b l e t o the phase B planning process is presented below. Antenna Pattern Measurements Analyzed three methods of measuring antenna patterns in relation t o the antenna attitude in a 200 nautical m i l e o r b i t . The study was made t o e v a l uate a c o n t r a c t o r ' s proposal t o NASA f o r measuring the c h a r a c t e r i s t i c s of a large space erectable parabolic antenna. Comparison studies were conducted and recommendat ions submitted f o r the most accurate method of measuring antenna patterns. RL # 16-022 Discussion of Completion date: 5/66 t h e Torque R e c t i f i c a t i o n Dump Scheme Scrutinized contractor's proposal f o r a g r a v i t y gradient dump scheme designed f o r momentum r e l i e f of the Control Moment Gyros. The scheme u t i lized the rectification of the c y c l i c gravity gradient torques by changing signs of the commanded maneuver angles a t specified times in the orbit. T h e a t t r a c t i v e a n d u n a t t r a c t i v e f e a t u r e s o f t h e s c h e m e urns p r e s e n t e d a f t e r a detailed analytical and computer simulation study was performed. OWS-2-1 Completion date: Double Gimbal Control Moment Gryos The System for 4/67 in Vehicle Attitude Control I n e r t i a l Experiment P o i n t i n g a n d A t t i t u d e C o n t r o l PAC) os proposed by NASA (Langley F i e l d , V i r g i n i a ) 2-9 is investigated. (OIX- �T3 CD +-» 3 3> 3 o CD CD -3 *-• 3 O •a 3 vt CD 3 3" !_ O cn 3 i"3 CJ — E 3 3 31 "3 O l_ CD 3 O +- CD 3 "3 • cu —— o *— -C 3 o> a. 3> 4-» —N K« 4-* C 3 O CL o O CD «/» 3l cu 3 3 •C K— u O E —— 3 — o 3 n. CD •s: E Q ~ E a L. 3 — 3 c 2-10 o «/» *— X a �The fundamentals of the equations t h e CMG s y s t e m are for a space v e h i c l e using t h e SIXPAC conf iguration is devel oped. Along with this a block diagram of developed presented and the derivation of t h e CMG a n d u e h i c l e d y n a m i c s a r e for system study. The characterist ics of t h e CMG a s a n a t t i t u d e c o n t r o l d e v i c e a r e a l s o discussed and a comparison with other attitude control Then advantages of the various systems are SP 517-67-1 schemes is made. presented in cone I usion. Completion date: 1/67 Charaer-batteru Regulator Module - Prototupe Test Model 4n engineering a n a l y s i s was for the thermal, mechanical performed to establish design requirements and vibration prototype of battery - regu I ator -modu I e . The packaging design required compliance with MSFC Document 50M02408. E n v i r o n m e n t a l teria t h e ATM c h a r g e r - Design and Qualification Test Cri f o r ATM C o m p o n e n t s . T h e t h e r m a l and vibrational analysis of the prototype charger-battery regulator was conducted t o v e r i f y the packaging design per requirements of 50M02408. RF # 10-004 Completion date: Generation of Orbital 7/68 Coordinate Systems and Aerodunamic and Gravitu Gradient Torques T o e v a l u a t e and c o n f i r m t h e ATM c o n t r o l face a detailed soft mockup of system configuration and inter the vehicle pointing and control system was deve loped. The developed earth orbital program presents a complete MathematicaI Model space station. The Earth-sun-sate 11ite motion model lated along with all external of an is simu torques acting on the vehicle. The control system containing control moment gyros and reaction making i t possible to do detailed jets is also simulated fuel studies of any earth orbital control system. Presently this simulation digital and 8900 hybrid computers. SP 522-0058 is vehicle programmed on both the 7094 Completed: 4/67 Updated: 4/68 ATM Command a n d T e l e m e t r y A n t e n n a s Originated the design concept and types of ATM a n t e n n a s . fabricated scale models and proto The antennas are mounted on t h e solar wings. An edge-mounted scimitar antenna was used 2 - II for t h e 450 MHz command s y s t e m and �Q_ O O v» H > < cr o C a L_ o H—. E 3 4-» C E o E c a 4-* 3 v» u •3 C a 3 cu 3 3Lo 4-» Q +-» z - •— o o OJ 800 400 0 UJ 3 C cu T3 <3 L. <S> » UJ Z o / o UJ CO _ i x +- • a t- 01 w> —— « -e e y — -—s, * o s— o o o o to o o ID 03S-13W-M3N 13W-M3N 2-/2 ut +-> H- C Q 3 O a. �an edge-mounted dipole antenna was for t h e VHF t e l e m e t r y . The d e s i g n c o n c e p t formulated by building 1:20 scale models of the proposed antennas and checking the radiation characteristics on a 1:20 scale model of the Apollo Telescope Mount cluster. RL # 16-006 Completion date: A—Techn i que By use of If f o r S t a b i l i z i n g t h e ATM V e h i c l e 11/68 for Extended Time Periods Momentum Exchange Devices a n ATM r e u i s i t i s e n v i s i o n e d t h e r m a l supply thermal control a source of control will be necessary. To power will be required. If t h i s power is provided by solar cells facing the sun a control system will either active or inactive. If an active system is used the system described in this report be required is applicable. The study presents a momentum management scheme t o permit control t h e ATM w i t h c o n t r o l moment g y r o s d u r i n g t h e unmanned phase o f The momentum management scheme reverses the direction of of the mission. disturbance torque through simple CMG-controlled maneuvers, thus eliminating the requirement for reaction control jets to relieve the unidirectional stored momentum of the moment gyros. Presented to May 1967 American AstronauticaI National Society Symposium SIVB Stage Digital An al I-digital Filter flight controller detail. Several mechanizations of and comparisons made by means of for the SIVB stage is considered the digital in compensator are designed frequency response measurements and hybrid simulation. SP 551-0045 Completion date: 2-13 4/24/68 �2-14 �WORKSHOP CAPABILITIES SUMMARY PHASE C - DESIGN In this phase the final concepts are developed: designs are made t o required specifications: and a total system analysis made. From this an ana lytical report is assembled and the (PDP) released. finalized Project CeveIopment Plan The Apollo Telescope Mount (ATM), as the first large orbital workshop, has been through this phase. The Space Support Piuis ion's contribution in this phase, as documented, is presented ATM 50-56 X-Rau T e l e s c o p e : Final analysis of following paragraphs. Final Report the optical is presented. Analysis in the the SO-56 X-Ray Telescope includes ray tracing with special emphasis on ray diagrams, spot diagrams and properties of point spread functions. All aspects of the X-ray reflection dynamics were considered. 0BS-3-I Completion date: 3/69 ATM Conf_[quration Manaqement Established a system for configuration control for t h e ATM p r o g r a m . The c o n c e p t of plan and documentation control and documentation a workable configuration management plan was presented t o and approved by the MSFC ATM P r o j e c t O f f i c e ; t h e n d o c u m e n t e d and i m p l e m e n t e d . T e c h n i c a l mentation is generated determine a basic flow docu from research and data gathering, as required, t o for t h e ATM program. The c o n f i g u r a t i o n management keeps engineering management plan informed on the program status. RL # 18-002 Completion date: This i s a con tinuing program. ATM E x p e r i m e n t Interface Control Documents R e v i e w e d and a n a l y z e d e x p e r i m e n t e r a n d ATM e l e c t r i c a l c i r c u i t s , a n d maintained electrical systems c o m p a t i b i l i t y between experimenters. MSFC. and Manned Spacecraft Center by generating electrical documents and electrical interface control interface defining documents. Reviewed experi menter s proposed changes and recommended acceptance or refusal by the Con figuration Control Board. R L ft 0 9 - 0 1 2 Completion date: 2-15 4th Quarter/70 ��Cable and D i s t r i b u t i o n Sus tern A 700-cable distribution system control, power distribution. and data transmission a 52-rack. 260-panel ATM. is currentIy being designed electrical support An analysis has been made of interconnections between equipment checkout the entire cable and out system t o establish design goals and c r i t e r i a . 500FS system was made t o determine u s a b i l i t y o f continuing systems control is interface study is to provide system and the distribution check A study of cables for the Saturn V, the design. being performed and cable A interface being maintained. RL # 09-006 Comp l e t ion d a t e : 11/68 ATM D i s t r i b u t o r s Pre Iiminary studies of bution requirements ATM power, measuring, and command signal established the butors. The distributors route need commands, between the command capsule control and the electrical of the ATM. especially designed distri measurements, panel, and electrical t h e ATM experiment support equipment. both prior Designed the complete distributors and components. Thermal reduction for distri to power packages, and subsequent to include housing, launch cabling, uacuum tests are performed t o v e r i f y the design. i n the number of distributors required is A achieved through the u t i l i z a t i o n of TO-5 type relays. R L if 9 - 0 0 4 Optimal Completion date: Desaturation of Control Space vehicles on missions Moment Gyro Systems that u t i l i z e Control Moment Gyros (CMGs) require for a precise pointing capabiIity offered by systems. CMGs by do run out of CMG g i m b a l fuel tank) External gimbal angles). torques must angles. problem of CMG c o n t r o 1 1 e r s problem. in this application condition (analogous gimbal angles to the vehicle/CMG free "fuel" source available momentum desaturation of is cast into the The system model with a state and control has the format of form of independent, OWS-3-4 of the in the to an empty a minimal limits. reset the process is de gravity gradients. pointing control a linear is measured system to systems with energy optimization time-varying equation time-varying forcing function. Completion date: 2-17 perhaps approach their A systematic approach to this "refueling" scribed using the The pointing will a continuous controller. Like other The "saturated" be applied in Orbit long time t o come because "fuel" (which, i s r e a c h e d w h e n t h e CMG fine 8/68 1/69 �TELESCOPE TO WORKSHOP MAGNETIC SUSPENSION DYNAMICS /.TELESCOPE COUPLING FROM WORKSHOP TO TELESCOPE THRU SUSPENSION FORCE = K | i ( S ) K| [Ei(S)-(^jsd(S)] (TS+I) A magnetic an almost suspension of perfect this T= type can be isolator, expecially when L| A +R| feedback principles are applied. Coupled K|=I.47 force due t o workshop motion K2=l.65 open loop gain A. is reduced by In addition, the characteristics are essentially isolation frequency invariant. 2-18 A > 1000 �ATM C l o c k Designed the logic and stable time references of packaging of t h e ATM c l o c k t o p r o v i d e u l t r a - for u a r i o u s ATM e x p e r i m e n t s . The c l o c k prouiding time references days, with a stability of I in milliseconds, is capable seconds, minutes, hours, and x 10^ throughout the temperature range of -20 degrees to 85 degrees Celsius. The clock can be reset to any time period by ground command signals, and has a r e l i a b i l i t y of unit was fabricated and tested. RL # 17-008 0.99965. One prototype Completion date: 9 67 ATM S w i t c h S e l e c t o r Panel Prepared Class panel is required design of I documentation of t h e ATM s w i t c h s e l e c t o r p a n e l . T h e f o r ATM s e l e c t o r s w i t c h t e s t and c h e c k o u t . The the panel (component layout) was ments. Documentation was 00224A. completed Completion date: 12,67 System Networks The electrical circuitry to perform switching, control, interconnect all five control ATM s u b s y s t e m s a n d t o power distribution, and functions is currently being designed. distributors . prepared t o meet MSFC r e q u i r e i n accordance w i t h MSFC Drawing 40M- RL # 10-013 ATM E l e c t r i c a l packaging signal conditioning The system consists of three power d i stributors. three measuring distributors, a transfer assembly, a controls and display logic distributor, and approxi mately 500 interconnecting cables. The specifications. RL # 09-011 s u b s y s t e m s a r e d e s i g n e d t o ATM Completion date: 1/69 Time - Division Multiplexer A time-division multiplexer was designed to accept up t o 270 data inputs of 0 to 5 volts in amplitude, and to provide two parallel output wave trains. The multiplexer has 30 primary channels with a sampling 120 samples per second. Principal the dc dc converter and subassemblies of regulators that provide missile power grounds: an isolation amplifier rate of the multiplexer are: isolation of signal and for each output: main channel multiplexer cards: calibrator: ana clock and timing subassembly. One multi plexer was breadboarded and successfully tested. Documentation and type fabrication are used o n t h e second ATM RF # 16-025 in process. Several of these multiplexers flight. Completion date: 2-19 9/68 proto shall be ��Control Circuitry for Data Acquisition Sustem D e s i g n e d t h e a m p l i f i e r a n d s w i t c h a s s e m b l y t o b e u s e d o n t h e ATM t o amplify and select the proper output of r e d u n d a n t PCM d i g i t a l d a t a a c q u i s i t i o n s u b s y s t e m s . S w i t c h i n g b e t w e e n t h e t w o PCM s u b s y s t e m s is accomplished by commands to internal control c i r c u i t r y . These control c i r c u i t s employ electro-optical devices t o provide maximum isolation between the external command signal c i r c u i t r y and the control RL # 17-005 circuits. Completion date: 11/67 Charger-Batteru Regulator-Module Documentation This effort involves preparation of the specification. and the accept ance preliminary and qualification test procedures for the Apollo Telescope Mount (ATM) charger-battery-regu I ator module. A review of requirements and prototype circuitry provided detail three documents. The specif icat ion establishes requirements; the acceptance test procedure sets standards: and the qualifications test operating requirements t h e ATM requirements forth module acceptance procedure details environmental Completion date: 2-21 for the purchasing manufacturing for the modules. RL # 10-001 power 4/68 �Kft -3 3 »— 3 o *— •3 3 O O Cy V> O L. 3 m —. 4-» o "3 cw v. 4-* L_ —— •— •w 3 »— •3 »— 4-» 0 3 —— cu 0 E -3 iC 3> *— 3. —— 3» 3 -3 ITi -3 1 "3 3. O O u 3 "3 O L. 4-* 3 •— "3 3 3 -3 — +-» H—« O «/» 3 — •— +•> LO 4-» V* »— <3 X 3 —— Cy -3 4-* 4-» 3 Cy E cy 3 O • v> •— 3s 3 L. *— 2-22 </» <y Cy 3 «— 4-» O cy — "V^ cy u 3 O •— 4-» 3_ O Cy -3 4-* O 4-» 4U Cy 3. v> Cy L. -3 •w •— 3 �WORKSHOP CAPABILITIES SUMMARY PHASE D - DEVELOPMENT AND OPERATIONS In this final phase the tasks of developing. manufacturing, testing and operating the products designed to achieve the mission goals are carried out. The Space Support Division s capabiIity in this area is readily demon strated by presenting assigned tasks and describing the design deveIopment and testing effort put forth on each. The the Apollo Telescope Mount (ATM) following paragraphs describe Phase D effort. X-Rau Telescope - Camera and E lectronics Desian: The X-ray teIescope-camera and electronics S-056 Design for the S-056 X-ray telescope experiment which will measure soft X-ray radiation originating in the solar atmosphere has been designed, deve I oped. and produced. The X-ray telescope system comprises an X-ray telescope with film camera and an X-ray event analyzer (X-REA). The X-REA and teIescope-camera are two independent measuring systems w h i c h w i l l b e a t t a c h e d t o t h e ATM i n a m a n n e r w h i c h w i l l to measure radiation from the same source. The these two measuring systems will flares and the physical allow both systems information obtained provide a better understanding of processess which take place in the OBS-4-1 Complet ion date : from solar sun. I 69 ATM T e l e v i s i o n S y s t e m D e s i g n A television system for the Apollo Telescope Mount (ATM) has been de signed and developed. This naut viewing of system is installed solar activity telescopes and consists of i n t h e ATM t o e n a b l e a s t r o from earth orbit through several different two (2) Iow-light-1eve I TV cameras, two ( 2 ) v i d i c o n T V c a m e r a s , a n F. I A s y n c g e n e r a t o r , a n d t w o ( 2 ) w i d e b a n d v i d e o switches. The of low-light-level excellent usable t e l e v i s i o n camera u t i l i z e s a SEC v i d i c o n c a p a b l e picture quality p i c t u r e q u a l i t y ( 2 0 0 TV can be used as a candles . ( 6 0 0 TV lines) at 3 x 10'3 lines) at 5 x /0"5 footcandles and footcandles. The camera Iight-integrating device down t o levels below 10'7 2-23 foot ��T h e ATM v i d i c o n camera i s a h i g h r e s o l u t i o n ( 8 0 0 TV l i n e s ) s y s t e m u t i l i zing a standard 5403 ruggedized uidicon with excellent I x lO'l footcandles. Usable performance down t o pictures can be obtained down t o 5 x 10 footcandles. OBS-4-2 Completion date: E l e c t r i c a l Power Subsystem for Apollo Telescope Mount (ATM) This task comprised the design and deuelopment of power subsystem which I 69 furnishes the electrical t h e ATM e l e c t r i c a l power required by all other ATM s u b s y s t e m s a n d e x p e r i m e n t s . T h e ATM e l e c t r i c a l poiuer s u b s y s t e m c o n s i s t s o f energy conversion and the required sources. interface 18 18 photovoltaic direct power conditioning-energy storage groups. interface networks and power distribution c i r cuitry that provides remote system control capability, system monitoring, and power management information. OWS-4-3 Completion date: I 69 270 Channel Multiplexer The 270 multiplexer was designed t o accrue data and channel the data via 270 lines to the data acquisition system. The multiplexer utilizes the latest circuit configurations. including integrated circuits. To develop the multiplexer, the electromechanical grated circuits with weldable through the motherboard and leads. flexible package was designed using inte Interconnections were accomplished printed circuit cabling. The flight housing was designed utilizing three configurations-almag sand casting, aluminum sheet weldment and an aluminum dip brazed housing: of latter was selected for implementation. The multilayered circuit boards are attached in an accordion padding inserted fashion with flexcabling and with shock-resistant into a cavity configuration. The module is currently des ignated as backup for t h e second ATM for the f i r s t ATM flight and will maintain a prime status flight upon completion of RL # P4-008 AC DC which the prototype development. Completion date: 6/68 Power Suoolu An ac dc electronic d c power t o t h e ATM motor. The dc power supply was designed and platform modules and ac portion of the power supply fabricated to furnish power t o t h e 4TM g y r o s p i n is equipped with a step-up switching prereguIator. a dc-to-dc conuerter and a pulse regulator. The 2-25 �ACCEPTABLE S/N RATIO The performance a t t a i n a b i l i t y of brightness. as a function of a star tracker, for a particular guide s t a r the acceptable signal J-26 to noise ratio. �ac output is equipped with a crystal-control led oscillator, followed by a binary countdown. The dc input uoltage is required to remain between 24 to 32 volts to maintain a dc power output of 250 watts and 35 volts ac at 1600 Hz. RL # 22-009 Completion aate: Ground Support Electrical Power Sustem A power system is currently being designed t o solar bus and or load bus and t o the electrical forming ground checkout of 12 66 f u r n i s h power t o t h e ATM support equipment when per the ATM. The design e f f o r t includes an overall system analysis to establish design criteria, an evaluation of s y s t e m s t o d e t e r m i n e t h e i r a d a p t a b i l i t y t o t h e ATM comprehensive study of paration of existing requirements, and a each subsystem to provide details needed for pre the preliminary design drawings. Fabrication drawings and pre liminary early-order parts lists are also being prepared. R L # 09-009 Completion date: 11 68 Hudrogen-Oxuaen Fuel Cell Resign and Test Four years of detailed experience has operation and test of Hydrox fuel been obtained in the design, cells. Approximately 8000 hours of ope r a t i o n of 2-kilowatt A11 i s-ChaImers (AC) systems have been logged by d i v i sion personnel in the study and test of developments have resulted these power sources. Significant from research conducted on single sections on evaluation consoles developed and OWS-4-4 fuel cell fabricated by this Division. Completion date: A continuing effort Sun Sensor and Star Tracker Computer Simulator A computer simulator is currently being developed of the sun sensor and similar to that of star tracker. The simulator internal electronics of the the data. the direction and magnitude of solver zero, and tested when flight: function i t gene pulses, that are used fine sun sensor and star tracker purposes, gating, and shifting of data of performs a the on-board digital computer during rates an interrogate pulse, together with clock the for ground checkout for timing It also accepts serial binary the resolver rotation and the re- presents them to the display panel. The simulator will fabrication is completed. RL # 13-001 Completion date: 2-27 in Estimated 6 68 be �2-28 �P a c h ac l i n g P e s i g n _ f o r t h e C h a r g e r B a t t e r y _ R e g u l a t o r M o d u l e ( C P R M ) Performed the packaging design and documentation of t h e ATM C B R M . w h i c h included engineering design, drafting, and checking. The packaging design required compliance with the EnuironmentaI Criteria for ATM Components s p e c i f i c a t i o n . The purpose o f prouide regulation, conuersion. while and storage of solar-cell t h e CBRM is to power t o t h e ATM in an earth orbit. RL # 10-006 Completion date: S-Band Helical with a gain of 68 II Arrau Antenna Designed a S-band helical of Design and Dualif ication Test array. The array consists of a single helix, 8 db. mounted upon a common base p l a t e , adjacent t o an array four helices. The array has a gain of 12 db. The dual gain feature was utilized to prouide hemispheric earth coverage from an altitude of t o 2 3 . 0 0 0 s t a t u t e m i l e s . ,1 c o a x i a l antenna radiator. A four helical because of antenna height switch directs the rf signal 8.000 to either array was used for the high gain radiator restrictions on the Saturn V Instrument Unit. A laboratory model verified the design dimensions. A shop prototype was fabricated from design drawings. Qualif ication tests to flight certify the antenna were performed and the quaI i f i c a t i o n test report published. RL # I 6 - 0 I 2 Completion date: 10/66 Power Control and Monitor Panel A control panel, distribution of for monitoring and controlling the ATM e l e c t r i c a l support equipment power, generation and is currently in the preliminary stage of deuelopment. The subsystem w i l l s i m u l a t e t h e ATM s o l a r sources and control Modules (CBRM) during also has override control capabi I i t y for the Charger-Battery-ReguIator ground checkout. The control panel controlling the switch selector encoded assembly. RL # 09-003 Completion date: 2/68 Solar Simulator A solar simulator, gineered and designed simulator tube mw cm- i n t e n s i t y Celsius. for testing solar cell for use capable of performance, has been en i n t h e ATM q u a l i t y a s s u r a n c e program. illuminating a 24- by 26-inch area, has The a 100 capabiIity at any temperature setting between 100 and90° RL # 10-022 Completion date: ) - 70 II 67 �radiated power. 2-30 �Portable Solar Reflectometer A portable solar reflectometer for measuring reflective property of materials in space is currently under deueIopment. The instrument will make measurements over a wave-length range of bands. Data obtained from measurements tape recorder, which is an integral of 2500 A to 2.5 microns in eleuen is to be recorded on a magnetic part of the reflectometer. The the reflectometer is t o make refIectance measurements of paint purpose samples and or other materials which may be affected by the space environment. PL - 16-027 Completion date: 8 68 Advanced Optical Communications Systems Research and Development Research perimental in this area involves state-of-the-art theoretical studies of the eventual cluded visible and development of in this program are infrared and ex laser systems, with an aim to a deep-space laser communications projects that involve link. In laboratory photomixing experiments. beam steering and alignment technique studies, the design and testing of signal processing and information retrieval electronics, laser stability and control studies, and the development of transmitting optical systems. R L •• 0 1 - 0 0 1 Completion date: This is a con tinuing program. Aavanced Optical Tracking Systems Research and Development Under t h i s program, research and development is being conducted on a precision optical tracker that utilizes a visible laser transmitter for monitoring the elevation and azimuth angles, angular rates, range, and range rate of a spacecraft during the critical launch phase which occurs immediately after l i f t o f f . Current activity in this program involves the prototype development of laser amplitude modulations, modulator drivers, and diverse detection and demoduI ation eIectronics. RL •• 0 1 - 0 0 2 Completion date: 4th Quarter/68 Gas Laser Research This research and development program is directed parameters of gas laser photomixing systems at optimizing the for potential use in tracking and communication applications. Current program activities involved in the measurement of ment of include projects laser mode s t a b i l i t y , the prototype develop scanning interferometers for monitoring laser mode patterns, and the experimental and theoretical research on the dependence of photomixing on optical path length difference. RL # 0 1 - 0 0 3 . • r Completion date: This is a con tinuing program. 2-31 ��Laser Atmospheric Propagation Studies These studies involve the experimental and theoretical random phase variations in laser radiation during research on the Iong-distance atmospheric propagation. Activities are oriented to the design and development of laser system that is to be employed in the measurement of ations of an amp Iitude-moduIated a the phase vari laser beam as i t traverses various atmo spheric path lengths. RL " 01-005 Completion date: This is a con tinuing program. Optical Component Development This RSD e f f o r t i s organized to provide optical systems-components integration and correlation technology. The program consists of an optical systems design study that is being conducted in con j unction with an optical components design and development activity (mirrors. lenses): which in turn results tical in the integration of the individual components into complex op s y s t e m s . /I c u r r e n t d e s i g n a n d d e v e I o p m e n t p r o j e c t i s t o d e s i g n l a r g e f-number lenses with minimal low-order Seidel abberations. R L -- 0 1 - 0 0 4 Completion date: This is a con tinuing program. Advanced Semiconductor Memoru Devices Research Theoretical and experimental research studies into the use of a metal- insulator- semi conductor (MIS) device, as a bistable active memory element, were performed. The device utilizes the tunneling effect between the semi conductor and the insulator to store trapped charges. RL H 01-009 Completion date: This is a con tinuing program. Advanced Semiconductor Materials Research Research studies involve state-of-the-art epitaxial niques. Current research includes development of transistors, deposition of growth of and diffusion tech deep diffusion for power silicon nitrides and oxides, and epitaxial semiconductor materials. RL - 01-006 Completion date: This is a con tinuing program. 2-33 �The Zeta angle uersus time plot depicts the angular change the solar vector makes with its projection on t o the orbital plane during a one year period. The high frequency variations are caused by orbital regression while the I cycle per year - variation is caused by the earths inclination of degrees. the orbital journey about the sun. The plane referenced to the equator 2-34 low frequency - for this plot is 28.5 �Non-linear Magnetics Memory Research and Deuelopment This research effort is inuolued uiith state-of-the-art studies of mag netic t h i n - f i l m memory materials and deuice techniques. Areas researched include magnetic material properties, techniques of deposition, and the deuelopment of aduanced memory systems. RL ' 01-008 Completion date: This is a con tinuing program. 2 - 35 ��I I I . ORGANIZATION PROFILE The Space Support Division i s an operating unit of the Sperry Rand Corporation as illustrated in figure the Sperry Group of I . The division was founded in Huntsvi11e. Alabama in 1965 t o support the National and Space Administration. George C. Marshall trionics Laboratory, sion is in all Aeronaut i cs Space Flight Center. 4s- technical disciplines. The Space Support Divi fulfilling i t s mission by designing and producing, to the exacting requirements of the Astr ionics Laboratory. many complex systems in support of the Apollo Telescope Mount. Orbital Workshop and Saturn/Apo11o programs. The division is also furnishing spacecraft reliability and test engineering services to the Goddard Space Flight Center. recently signed with the Army Corps of cation of In addition, a contract UKJS Engineers that requires the appli aerospace technology to the tactical facilities of the SENTINEL Anti-ballistic Missile System. From July 1966 through June 1968 the Space Support Division engineering services to the Jet Propulsion Laboratory furnished for the design of spacecraft and spacecraft systems. FACILITIES AND STAFFING The staff of the Space Support Division is currently at the level of employees. This staff facilities of 840 includes 600 employees working in direct support in the Marshall Space Flight Center (MSFC) Astrionics Laboratory in Huntsville, Alabama. There are 235 employees working in direct support of the Goddard Space Flight Center portion of in Greenbelt. Maryland. 4 substantial our employees are housed in Space Support Division Huntsville, Alabama, consisting of facilities in three buildings containing 53.000 square feet of floor space. These facilities provide administrative, engineering. Iaboratory, and prototype manufacturing areas. T h e e n g i n e e r i n g a r e a i n c l u d e s a we1 1 - e q u i p p e d perimental laboratory in which ex and prototype models are developed and tested. A Sperry Rand Corporation computation Support Division engineering facility is located near the Space facilities. 4 Univac 1108 computer is avail able t o support simulation requirements. data reduction, and budget and payment records. 3-1 �I I I I I �SPERRY RAND CORPORATION SPEP.RY RAND RESEARCH CENTER UN I VAC D I V I S I O N SPERRY MARINE AND ELECTRONICS DIVISION SPERRY FLIGHT SYSTEMS DIVISION SPERRY SYSTEMS MANAGEMENT D I V I S I ON SPERRY MARINE SYSTEMS DIVISION SPERRY GYROSCOPE DI V131 ON REMINGTON. RAND DIVISION FORD INSTRUMENT DIVISION NEW HOLLAND GROUP SPACE SUPPORT DIVISION SPERRY ELECTRONIC TUBE DIVISION SPERRY MICROWAVE ELECTRONICS D I V I S I O N INTERNATIONAL OPERATIONS CHAPT S !O-25-:960 SPERRY RAND CORPORATION Figure 1 REMINGTON ELECTRIC SHAVER DIVISION ��-6nrSFER*Y RAND Figure 2 . Space Support Division �mBsSSm NHBRHBHH BBhBHHI �ENGINEERING Approximately half of our engineering employees Alabama are engaged in on-site support of remainder of of located in Huntsuille. the Astr i on i cs Laboratory. The the Engineering Department employees occury 23.SOD square the Space Support Division scientific employees facility. This staff responsible feet includes engineering and for study, deuelopment. t e s t and docu mentation work related to Space Support Diuision programs. In engineering design department provides design and drafting groups. The engineering staff fifty masters for development engineering includes two doctorate degrees, approximately degrees, over two hundred bachelor degrees and over one hundred associate degrees. PAST PERFORMANCE Sperry Rand Space Support Division a technical performance rating of management rating of for the past three years has achieved excellent or better, and a technical superior on support services contracts. COST REDUCTION AND CONTROL Sperry Rand Space Support Division i s currently involved in an effective cost reduction program (ORBIT) in which all employees are consistently urged to participate. This program meets the cost reduction guidelines as set f o r t h b y b o t h DOD a n d NASA. T h e program is coordinated by an assigned individual and is guided by an established procedural manual which complies with both government and corporative guidelines. its inception, a gross savings of In the 2 1/2 years since $1,170,134 has been reported. Through F e b r u a r y 2 8 . I 0 6 8 . 53 8 s u g g e s t i o n s h a v e b e e n s u b m i t t e d r e p r e s e n t i n g a n employee participation of 66%. PROJECT MANAGEMENT The Space Support Division has developed a project management point-ofview as the result of i t s three and a half years experience in support of aerospace agencies and has evolved an organization geared to the achieve ment of project goals on time, within budget, and within predetermined performance spec i f icat ions. The management techniques deueloped cover the planning, control, and supervision of engineering and design resources and include the whole range of systems engineering, project control, configu ration and data management t e s t , and procurement. The result is the inte gration of the several functional departments of management system. Each contracted task the division into a is assigned to a total project manager who assumes complete responsibility and accountabiIity t o divisional man agement ana to t h e customer for successful accomplishment of the program. 3-4 ��SECTION IV SUMMARY SPACE SUPPORT ��IV. SUMMARY The qualifications, f a c i l i t i e s , and capabiI i t i e s of Support Division may be summarized as PersonneI 840 total FaciI ities S p e r r y R a n d S pa c e follows: - of which 40 percent are engineers. S3.000 square feet of modern well equipped fa cilities. Qua I i t y Dedicated by pol icy and practice to the highest attainable level of quality control with the cost enced in aspects complying consistent of the program. Experi with DOD and N1SA q u a l i t y specifications. Control s A modern UNIVAC 1108 computer is utilized in the management of man-hours schedules and cost control. Experience Proven for success the Marshall on support Astrionics services Laboratory, Space Flight Center; Jet contracts George C. Propulsion Laboratory and Goddard Space F l i g h t Center. Security Secret facility Contract clearance aamin istratiue granted services by Defense region, At lanta, Georgia Cost Savings Gross savings of si,170,134 in 2 1/2 years with 66 percent employee participation. Additional ly, through the corporate policy of the Space Support Division can draw on a l l nical consuI t a t i o n . manpower, or synergistic operations corporate resources when tech equipment are needed. 4-1 ��•EBIQN . DEVELOPMENT* STUDIES • ENGINEERING RANGE SUPPORT INSTRUMENTATION AUTOMATIC CHECKOUT GUIDANCE AND CONTROL SYSTEMS TELEMETRY -0" ELECTRONIC POWER CONFIGURATION -$• SYSTEMS MANAGEMENT FLIGHT DYNAMICS AND SIMULATION ELECTRICAL AND ELECTRONIC SYSTEMS SPACE AND SATELLITE COMMUNICATIONS NAVIGATION SYSTEM ANALYSIS >$• RELIABILITY ANALYSIS FABRICATION °^SPER^Y RAND SPACE SUPPORT ixvson •<AWTSVLU!. � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket. Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite. A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used. Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context sdsp_skyl_000070 Title A name given to the resource "Sperry Rand Earth Orbital Workshop Capabilities" Brochure. Creator An entity primarily responsible for making the resource Sperry Rand (Corporation) Date A point or period of time associated with an event in the lifecycle of the resource 1969-02-01 Temporal Coverage Temporal characteristics of the resource. 1965-1970 Subject The topic of the resource Sperry Rand (Corporation) Skylab Program Apollo applications program Space habitats Saturn launch vehicles Apollo Telescope Mount Huntsville (Ala.) George C. Marshall Space Flight Center. Astrionics Laboratory Sperry Rand (Corporation). Space Support Division Type The nature or genre of the resource Brochures Still Image Source A related resource from which the described resource is derived Saturn V Collection Box 30, Folder 18 University of Alabama in Huntsville Archives and Special Collections, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource Skylab Document Scanning Project Metadata Skylab 50th Anniversary https://digitalprojects.uah.edu/files/original/20/14408/001.pdf 921170356ee20a1b14bfbade0ab86710 PDF Text Text ��ST/iTSSaST 07 WORK HAU/MVCBUST ACQJIVrriES - AIM SCOPE TMs^rvtccsMit of \Jovk. cjicoBroaasGs the oan/niaeMne effort reoulretl to optimize tho crew role cod the eysteas deslsn for the Apoilo Telescope Mouat (AT^!) erpcriaeat* OBJECrmS The objectives of the progrsia eret 1. To Id TiciCy the tcoho re®ilred to actuate, coir;i-ol and ncnitor the to rct.rl<Tve data casosttea ty EWl, end to ctov tlia cassettes aboard the AEl carri<ir. 2. To define cud cstabUsh apeclfiCGtlcns for the cquipE jiifc requited to support the crov dJtrlng EKA trcnslatlcai, do^.a retrieval. haadllDg and etovn^e. 3. To cpp3y huran casiaeerins criteria thru design outroort of those systems interfacing the orbital crew mcaibor. forj3lbimy of lr.tv.m p^rforannco on those tashs Identified ly caalj'Gia (inciud'jjs sittulatica) a£ crew variables and ccostralnts, equiprent UitViatloas, and alnsica roquircmsnfcs. 5. , To devadop a tradning program, Inclv.dlr-g coursti outlines, ^-quipmont description, personnel requirfiicnto, end fanllJ.ty utUlEaiion, to lEjiltBEnt indoctrinatlca of the crew to the ATIl, ASSUiPnOilS The follo»7lns esovurotious will be included emong thoca to be used in the performance of this prosrom. 1* The Apollo Elcch II suit shall be ;rtili2ed by the sstrcsmts. 2. Attitude stabilization, pointing and control el"'all be ccadr^rted by the nstrona'jtCc) within the AEi carrier. 3* The carrier configuration end flight profile shall be ccnoistcirb with the curitiatiy dsolgnated /-AP ccafiguratlozxs. �2 IV ERa'.RAIl OUTUES 1« 2. GeDcral a. Ka::irniax utlllT:t;tion vill l)is made of reaultn clrtaijiod from the G&*ainl and Apollo proc^ans. b. l^axlrai:! use shall -S hardware coiEpimeata and syeteans which oro either availnblo cosomQrciaUy or have teen developed uudior other rclr.tod prograias. c. The Ernsn Fac<:ors Ehciuorr.his Section shall fi-volop a de tailed progmu plan catega.'lsinc th? effort into a logical sequence cf outicireted tatla. Enoh task will ocntain obJ-.ctlvos, the Kcpected proiuet, allocated maa-hci;ro, relaticn to crthax' tasks, data rcxjuired from Gv-vamment scwraen; the plan shall also provida for mihistone event rcvicvs. d. CoaveJitlonal equlpiC'^ait, procedures, end tcehniyica \;j.ll be xrfcilizs.d ^dtenovcr possible-.' Crew/System Jtitecration a. The Eumon Feotcrs Enginccivlng Section shall idorttify critical system paramstci-s for both the ASIA and its carrie?.'. Such factors as pointing and Reciu'aciejj, motating character istics, tarcct nocuisition modes, cnvircnmiintal lijaitaticns, aoaitcring rccruirements, data rotrievol roouiremrnts (removal and/or rsTJlaceaoat, frequ:>ncy, inasscs), aoceoslbDity and interfaces will bo evaluntod for ccspatibmty with too htann opci'atcr. b. Those system rcguireincats which constitute a eonstraiat directly or indirectly on na interfacing system and which affect odrc-x'soly ths crew pcxrfommco will be identified, l/hcre possible Eltemato systems or procedures will bs x*econmcnd.cd which will clloviate the constx'aint or improve system cffcctivoncas« c. Identification will bo csdo of the varlcblns and constraints imposed ly crew mcaber plxis caadldiite crew support (IVA end EVA) equipaient, cixd incorporate this data into the task analyses and new equipment design specif1cations. d. All equlisEont with '.dilch tlxe crew will intorfaco ">>•^7) be analyzed and the opdratlixg and stowage rc^xlramsnts determined. This equirnx-at will include. ' �3 1) 2) 3) i;) 5) 6) 7) 0) « fSTA dioplay and ccatrol egjilpBent Gu-lflcnce and aaylgatlcn equipmant AE' data cassottas Datii hinadllng cq^alp22?nt (tools) D:j,ta atov.'aso crraj-prir^nt Li'Zo ciipport equlprant AlalocJca and nccossorlsa (hctch^a ond Ccmtro:^) Crav Bto.'billaeticc and traiislr.tion oquipiBunt (IVA artd eva) e. A dstallcd task aiS'Jyais iacludlng tinellns shall be conducted baosa on the follovins najor actlvitiea: 1) 2) 3) h) 5) 6) T) TciTcefc aeqtilsltion, otabiiization and control, Beta recording, Data rctrio%'al, Data Dtowego, E-q.u.'.pnint assembly, Crs-7 Qovcment to and frcaa the A2M work area* The enalyois shall bo updated basod on simulation results. f« Dwsicn opscifleatians will bs created for spnciol crf;w eqiJ-prc it and tools rcauirlng dovclopm-uat and vhnro rcoircsory modifi&itions will be rcec^snondcd for existing cduiui^at. AppUcablo hiwan englaeariag criteria wlU bo ro^crorced for boca now design and modifications. 3. Design Si^port % The principles of hunian factors cnginoerlng shall be applied to all related AKI eq^iisncnt to ensure the efficient inte^tioi of men into the design of the system. a. The EPS Inpirts shall con^l,y with system ena^sls regvli^ments as well as other appropriate inputs. Standard ^iS?'C-£TD-267 shall bo the basic jvcfereace doctnnsnt for the human €nginegring design features. b. Euirnn factors cri.teria end reccmmendatlons shall be fpplli.a to system and subsystem prelimiliary Ijycuts and related dratrings. The approval of Isyout drawings by the IF3 group shall verify that ths configuration end arrangamant of cqaipffo-'nt satisfy Esn/equipmcat perfomnnce rcguiremcnts, and that the design ccc^ilies with applicable criteria specified in Standcrd JBPC-STD-267. S �c. OsTrJi fnotora prJ.r^.ir--C3 rud proccdu-vcs cboll "be GxroHcxI, dVLTlac detail dc alfpa, -fco cquiinisnt di-avrlns3; sucli a;i pan<;l Inycuts, vorlaipccc I'v'oui^s, eon'trols, crew ciiuipTn-n-t oad •.•thcT dravinso <;japlofcirvs cqiii-prnDH-fc tiaccaBory for operation "by tho ABl caiTicr crow. d. nFB parsccmel sliall pjarfciclpi:to In dcalca rovicvo to enuvxe ccnalderatioa oi' crev oporationa and crew/eqjiiipra&nt intjractlons. SimtlAtioa a. Upon ccoiplotion of tho pxaHnicary task orolcrsls, e. airulatloa plzin vlll te vrittea and iiapl€n:ca:tod coverins the follcvdnc factors: 1) 2) Critical task? to he siaulcted, ?.2c:ar:-adcd a-.'le zf sl=;latlcn - aicohanical, SC-135, Itrt task, etc., 3) Sketches of noakeps required, k) Facilities required, 5) SiEulatloa schedule, h. The E-rrnn Factcrs Fa.-l2-~Sccticn skall write the .ietailed test prccedureo and suhnlt iioakup deslea xecpiirecents for the approved tasks to tie ajjprppriate doslGu s^^cups, c, 1F2 personnel ohrOl monitor the operation of all almlstitai tenting end participate in the dcelga evtOxvitions conducted on ccn^ncnt mockups which interface the Jaaaon ope rator, d. Prccc3ural changes end time iseasurcnients prodv.ccd oy sjarolrtion testing flhc.ll he incorporated into the detailed taok cna'^'sis, RcciBCzumdcd design changca rssidtlng from aiusulatioa rnd/OT lacckup drsloi evaluation shall be submitted by the Hunim Factors Eagineering Section to the appropriate design groups. Training a. The ATM task roqulrcs^rrts shall he evaluated and chose ckiU IsvcOa required to fulfill the oihital functions shall he presented. h. Prcm the detailed task analysis, H?3 porscmei sha^ldmtify those tasks vhsre training is neccssa^ end ^ dc^. of training xequirad to ensure their desired perfonrance, c. The Euman Factors Englnoerins Section shr^ training support personnel b? special-ty, traininc level «nd certiflcaticQ. �d. Training eqjilpncat and fanilitica shall be Iclentifici quantity, configuration, ntate of developEien-fc, location (if cxiatinc), and need date. e* ^ A trnlniDG pr Cfac outlintj shall be developed. This will include: f:ilGli-t crew. ^ w <)• rfJla ••cla3s:-u9a ir.";U:ri^il and equipacnt. 3) TraiDc?^s.> it) f p^racnnol and expcrlacnt c. ntrootcns. '4 "' Cvurse cutllnoa, frcquenc;' and duraticn, as vc.iJL as cquipasnt descriptions, iacludina sJffitchca, will be pro/ided with the traininc plan. ESPECTED rCBtJLiTS The fs-Uc^rlnc docuacntctitn will l>e submitted Saelneerins Section: the ffurnnri Factors 1. A listing f the syr^tems and/or prtcedures rolatad to ATi >4iich ara incoirpatiblo with bunaa p>.arfQraanoe crltej.*ia bti!? ov&r i^ch the contractor has no direct ccntr.1. 2, Related mission ccnstx'aints, A3S-I and corxder design constx'alnts, pers.nal equipment ccnstralats, and crew inrpi,i{ed constraints. ^3* A detailed task zinalysls and tiffiejlne conrncncing with th? pitspamtlon for iZA torcet cc<iuisition and cndinc with tha stLwace of the data cassettes within the AIM carrier ofter the final m. Design specificoticns f^r bcTth newly develvped crow sxQ^io-rt equipment end m. difIcatlon tt. existix^g e^ilxKoent. 5< The simulnticn plan and detal.Icd simulation results, concluslLns and recoBEcendatl ns* 6. Desl{pi cvaluatl n inputs ux related AT:-! subsystems requiring crew/equipment Interactions. 7* A training plan including course descripticn, material end eqpipBient requirements, skill levels and fcciU'ty rcccasnondstions. 8, A training irplementatlon plan containing a sched'alo of overall training events propcssd for .M!-!. 9. An outline and content description of an A33i flight crev training and familiarization manual. ��ATM FnOBI.TO AREAS 1« The general cost of EVA in ezcpendsblcSi crew end crew fotigiio. (See attnchceats 1 2). hours, oafoty, 2* The iJBpact of EVA whore vehicle configurations Involve crew traaafers by EVA. (See attachaent », 3* Other EVA consideratlono. h. The baeic everlond of the crew In reopect to nian hours nvailtible for expcrlrerts vorcus the can hours required by preaent experi-.;:ent dcfinitiona. On 211/2^ this chows 502 aaa hours avnilablo veraua 859 cian hours required. (Seo attachoem; 5). 5» Tho problea of dovolopinj and getting iraplcnentcd into exporinont dcaigno. basic principles of huaan factor cngineaj*ing and nlooioD oporation rcqu\rc-cnte. Thio io an cxtrc^caly tineGcnaitivo function. (Sea attGchoent 6 for a TOJV prolir-inary cot of the types of dntn that cuot get factored into the exporicent and carrior oquipnent designs). (See nttocfaj^ent 4). 6. Stabilization and Control requlrecents for ATM are the ooafc otringont ever attoapted in canned space fli^t. Consldorable study and cinulntion above that already ur.dertakon is probably required. (Soe attachncat 7 for eooe of the basic iteoo re quiring work in this area). 7« The I/EH io en extremely poor vehicle for extended habitation. Much huson factor effort nust be expended to provide reasonablo comfort to the crow. (See attaehnent 8 for oone considerations on this item. Also, refer to the section on crew habitabillty in attauhoent 5)* 8. See attacbxcent 9 for other AiOl Kan/^nchine Considerations. �/o �o 0 EVA CREW TIAU COST . vy CO 32 u CLOSE 12 5 REEVA « U2 u lUTCH O fj CH.^RGE S o w S 2 and o u BPLSS REPRES- O D O CO ^a and SURIZE kJ STOW u u CABIN "a STA®B'ir; b. -O k 3 u ec« 2s ce •••; ...'-v8 & u u H Q 0* 5 § 2 cu O b Q b. I','-"' CO CO ASIRCr^AUT f . CO R EST (2 lir) CO < CO •i.V CO 3VA.' As-rn(>""" HAUr CO CO CO CO h:,' - 9 •i.'i '' A';--' 0 *'. 'I • a™A /Ws}» ^ '"•"-l' '• • " •" .TiMS.. -(mlnutos) 8 .1. so X 60 X 70 X 80 90 K' •l-. Slv "-y-. ^rr ;.: £•'1--•'• •- "'-H • • •' *•• '•• * r- .*» • '> K . •A • J- r ••"•>'-"*':• '• .'•f'- , CO SVA -_yS•.•:-••. »V ' • - i.. •-•:- .?:.v'';-.--.I ..•••• „ •. -t- o : bV.' J. 100 TOTAL aiANHOvHS,® 0* .(3 X Period of Actual EVA) Attnchm^nt I �o O' •.» .2J ' ...• • .• ». :j: o ,:.;1;;-."V•.'-•»-> --'• ..~ > '• -. • OTHER EVA COSTS t fr •• • > • CONSUMABLES per EVA :r • •• ft-n *-» i- '1-^ ^ •< t—;• f^... •;» w:J.'. --jy lb Oxygen Cabin Loss 7.0+ Consumed by Astronauts (PLSS) 3.0+ Umbilical 6 IbAr Water I • • -.• •-. »=,• f-.-'. •' 14.66 LiOH (Contaminant Control Cartridge) Fuel (Stabll^e and Station Keeping) 7.2 ? SAFETY FACTORS Raciiation Exposure Meteoroid Exposure Astromut Fatigue Lo^v Systciii Safety .-V -.rv '- • -•"• ••-• ADDITIONAL REQUIREMENTS Wt (lb) PLSS Protective Oarments 64 Thermal 50 Meleorok1 15 Safety Tethers 10 EVA Astronaut Maneuvering System 10-140 PLSS Replaceables Battery Contaminant Control Cartridge Rescue Kit (est) TOTAL Vr rVol (ft^) Quantity 3 2 .5 1 2 2 f, .5 2 f- . 2 f" >>«- <1-9 ^' I »-- t_ - V- 5 .05 1 per 4 EVA 'S t 3,6 10 .04 .5 167-297 6.6-15.8 1 per EVA 1 i-r-: . - S'-.T ��'xHE g/A CO?g.TPTTm PPnarr^f Pcyhapo tho aoot olsiificeat diffeiwfo AV tionc lo a >oquirci=ent for rcEr.lsr comaytinn- toVork conflfpiraDr. MnoUcr and tho Altorrjtc /;a ccnfi-ajTc-tion S.^r.5^. i clic-.;a that ••.•hllo EVA caa bo RC'-canlioh"^ ia'iv-H-t' i i^^iperinent ha.9 l".bcrion3 to the crc-^. Ar.v clo^ig^ f-fficalt £«:cl nhould bo cnrofullo- aea3y=c;d and tho con;cqSSca PCrtcdlo EVA tho cafety foctoro and worlclcada Ir.volvod, every offo^ ^ ^ nxniniro tho qi-mtlty of m'o required., o^^^ort ebould bo ca(\o to D.. «to oori in tho l.:li/Ai;.. Ho oo-ola flea no' rtc-ro-rhir^f^^f =0 tfor.trbsp, cater the AL, ccciiro th-t j ^ the S-Iva veuld then AopTczav.^zo the AL and opcts fcha'^A^St°r Eo tfceeo aetlvltlcn tho r.otro"-auJ- ^,0 v,,, Wij.le .10 t-ao doing thocu-h a oiailnr cot of ooUi-ltioVin ^ prepared, tho firet aotrone.ut would then a ' ucro cuter the LEd and hook up ore of tho Dtsr£^va Iv^ ^'^5 Ea would then traacfor hlo Icrg urb^i^oal to K5?oilicalc to hio cuit. hock it up a-d diaooraoofc the .4ord:"j^fiMaeal ^^^roraut who would thou travoroe back to tho AL v.hile tho aatroraAtt would froa tho open hatch of tho Ii:i. Follcsr'-'^ procrecs ecouro tho LEj hatch, rcprcc-er'-e S^rVv S® as'crouaut would by the Chart, nfto? ah.a 5o the bSi: ^oo'sin^^SiSr& for short tora taslaj. Eowovo- the PLSS vould bo loncer. It is alco based ou^o dcvfi«n-.'^^^ ^^5 althoush tho tisa icfJiJuS'coSfbe ^tnntit. Of on,,. oon.«i .^rS; =-.t'rnSSt51S'?::o1^°Snnn. requeued. Due to'^voMclo^coSwrftiS^S^"^'^^'^^ ® sindlar EVA would bo r. desxrablo and the P15S vouid S S ? ®''^ rnbiUcal would be fiE •-ration woald be porhaaa 10-35 ^ probably ccnoiotius o* haadholde and riii Addittcnally, r. t^alkt.'sy, scroGo tho entire lorgth of tho coi^±s^lo^ developed of E/Ariri-iU So P-!>teo ri:;o Oithor tho Dr. MuoH^or « EOtivity is, orflcr to Ito root ohviof.s Kthed of aoins So iT^o j™ ".nfisoraiiono orootloal. nu tho noceocax^ natch rcouii-c^onto"^, ^^ZlZ Attachc;cat ^5 �/ . O • DEN OO6232 (11-62) ZVA 9 FOB SHIFT-CHANGEAUELLER COHFIGCRATION Hlnixnim Time Costs Activity Don and Check Out Suit " •4 filter and Secure long DnbiUcal AL, Connect ^2 Costs 20 10 Depressurize AL 3.5 lbs Open EVA Hatch Traverse to IM filter m. Switch to IM Umbilical Monitor #3 Traverse to AL Secure IM Hatch ID ' 5 12 lbs (DmbiUcal System loss) ID 2. Repressurize IM 15 Doff Suit and Stow 15 91 Dlnutea 6.9 lbs 22A lbs Developfflent Requirements: . • » . 150 foot DmbiUcal "Clothesline" Traverse Rig IM Hatches for Multiple Usage External Lighting CHART #1 ^ �o 0 ^ t66232,t1I-6Z,) CREW SCHSMJLE EXPERIMENTATIOH 1 1 WATCH NAP EVA n SLEEP SLEEP 0 2 ^ SLEEP EVA X 6 8 1 0 1 2 X X X 1d WATCH EXPERIMnfTATION WATCH ± L •4 tVA 1 KAP SLEEP X X X 1 ' » I 6 I 8 2 O 2 2 2 ^ X 2 6 2 8 3 0 J 3 2 3 4 J 6 Mueller Configuration and Alternative 1 (3'* hour cycle) - l8 Hour Exporinental Shift tXPERIMQITATION 2 SI.EEP ATCH E SLEEP ^ATCH EXPERIHENTATIOM SLEEP ATCH L X X X X 0 2 4 6 8 l 0 1 2 X X I I OPEN ATCfl WATCH^^SLEEP OPE» jEXPER. X X X WATCH X 1 i f l 6 l 8 2 0 2 2 2 % Alternative 2 (24 Hour Cycle) - 6-8 Hour Ibcperiaental Shift CHART #2 I �THE EVA COK^UTina PSDBLEH Pogo Z Md eiDlInr activitico. In fnjperiod the iiidivldiu 1 vdU ebtiiln Zh bouro of nlccp altho.n^ It would not be diatributcd 1 ^-hour baoio. ^ala cycle rey vcxy veil rot bo practical from a lloT ^ ®®'® ccaaideratioa cucfc as this ci;ot *? coafigurstiono r-ractical. The cocond of Clwrfc ^<2 soroly indlontos that la th® rblrt-oieoro ^ Altcr^to ilZ ccnfiguratioa, it is -pooaible to wori a ;iorBal o-hour day; 8-hour olcop cyclo. f^wbaj. Chart #3 providoa a r^r-aiy of opsrational differonccs botynoa the throo confasxiraticno for a 7-dry mission^ In ordor to nal-:o tho KncLler c^isuratiou and the Altorretc #1 corpotitivop tboy aro both barod on an Ib-hoi^ cxporincav vork cchcdulo as coapai-od to on B-hour work cchedulo for Altcmsio s^Z. Bf.ocd on tbia prsstce,- there ia no scrioua pa-ralty in t^e available for or-pcnrscnts between vaiilona config-jratioaa. Howctrer. thoro io a rajor difforccco ia tho aurbcr of EVA»3 aiid pr« est^isation cjclco required by the Altercate ij^ and tho othor two coalinuratlono..- If tho work schedule is changed to a 12-hour oicperli^sat duty cycle the iju-lbcr of EVA s Involved in the first t-wo configurations changos frca 18 to 28, and tha aur.oGr of prooourizatioa cyclca chrPees from 10 to 15. At tho onso tino. the amount of cino availrJjlo for experijcsnts crops to about SG hours. Althou^ tno txne available for AIH crpericoato io not greatly different for Altaraato ^Z, I Another feature choaii on tho eurcaaxy chart Is the feet that tho tins required for the crcv to rcatcfsblo into the CSH for ccGrgoncy abort is conoidcrobly loca for tho Alternate ^ corfigyrstioa. llhowieo, tho chart chouo an.orrdcp of ranking due to tho hazard of ETA. Bccavso of the fTcat ni^hor of EM'S required for tho first tuo ccnfigurations, there io a conoxdorablo spread b-t--.:r.a the number ono rating of Alternate j^S and the oocond and third ratings of tho other configurations. Another factor in this rating io the fact that the EVA at the cad of the work shift id.ll bo ficccoplich.-d by an. astronaut who nay already be hi^ly faticuod cud aoro prono to accidents. Ono pln.co on tho chart ropresento tho relative crow vorklcad for Mcccbl^g the basic configuration. Tho configunitica i?2 would be acconplicsc-d by a relative norcal Apollo dockljag maneuver. In both the Dr. Mueller wd Alternate #1 relatively complicated eijace erection techniqueo would bo involved. Horo again there is a wide spread between tho #1 rating and tho comparative evaluation of the second and third ratings. In GuiEmary, from a crow operation point of view, thore ia a caior bailee ia favor of Alternate ^ coafigurutionc Between tho Dr. tfuoUor Alternate j^^l there is little choice. It would appear that the ccmautxug problem is easier for the Dr. Mueller coafisuraticn- but the probloa of tho original structural build-up would be somewhat co«»' difficult. Attachment #3 ��OTHBR 17//. CO?:SI03?JVTXOIiS nVA cyclea and ducatloa To Reduce crcu workload to realistic level Insure conpatiblllcy with support equipment, I.e., life support ayatCD, caneuverins unit, A.L. hatch seal Reduce o.xygen required By Opclmltlng E?A procedures Eliniinatlng tasks not demandlns direct Vii,twiqTi input Siaq>lifylng required EVA tasks for mlnicaun crew e:;erticn Insurins cocpatlble hardware design, i.e., cascecce fartoncrs, iiandJ.es, tethers, controls Insuring optimum equipment Location for crev aecesstbllity Determine 5T7A support hardware requirements Including SLatilisatlon hardware IhuiGuvering oquipiscnt IUvrnlnaticn requireircnCs « Data cnsoette/crnw tethering harduare Data cassette protective equipmnnt Casratte attachment/detanhmcnt Cools Airlock hatch actuation toolc Sy Idoncifylng ajohility, dexterity, and visual acuity requirements for ea<:h task Simulating critical tasks to develop optlmua procedure and establish support requirements Analysing available support hardware far application and coEpatibillty Identifying AIM interfaces for crew tciherlng Dctcrtiinlag ATM data cassette envlrorjiintal lltaitations. �cj-vj-.z/oycCem By •• durlog EVA « E\-nluatln3 AT^l/carrier attitude stability oodoo Analyzing crew cquipcoafc failure wodeo Coternininc eonpliancc of AXH eyptora with applicable hiaaan enalncarinc critcfAa and avallablo Gcmini/Apollo data Siiaulatioa of critical casks to insure reaccnablc notabolic loads EctrbXiehins safety procedures to be undertaken in the event of an ejr.crgeacy Datrcnnlning ACS conotrainto on crewoan Insure crew/nisslon cosapatibility during EVA By Scheduling EVA for maximum operation during orbital light side Schcdiilias EVA during orbital perioda poesecsing mininun hazard, i.e., HKteorold shower activity. South Atlantic anomaly, solar radiation Scheduling EVA during periodu of minimum mieaioa operation ��AHAixsis OP csm camusmTnyss MlSSICai 2U/212 SEP 14 196S �TABTJS OP CCKTEiTrS BTTHOljirCSIOn Mission OETECTIVIS MISSION FUGEP PROFILE & 0PERAa?I(M3 EXPI21B5ZNP OPERATIOnS EVA E^UZE-IK® REQUIBESIEnrS CARRIER RECa-WEimATIOES CGRCLGSIonS 3s RECaM>-IBil!A!riOK3 �Sunxiry The anolysij of missico objectives, flicht profiles, spacecraft operations, cxpci-lmcait considerations end opcratioQS, and, carrier coapai-iscos for Liisoicn 211/212 is presented with ccnclus'lons and reca-asendntlons cs related to crcv c^naldoratioas end optratioas. The C3M/nc:'l/ATM offers crew advcntac«33 not available vrt,tMn the CSM/ LEl/AlIl confic:tu*ation. All ezipcrimeats con bo cccomplislicd with a reduction in the quantity but not the quality of desired infoxniaticci. The mission will bo trying and difficult for even the niO£;t MgMy motivotcd astronauts. Introduction The jiurposG of this study is to 03Cf;rtaln, in preliidnary form, the operational constraints end potential problems associated with crew participation during the mission. Fnctox-s considered aro mission oV jectivo, flight profiles, spacecraft opei*atlcns, experimnnta cparatlona and carrier considoratlcai. Conclusions and rccaumendatians are included for xiso by technical personnel. There ore many factors that can have an Influence on crev ciperaticaia during orbital or lunar missions. Some are very real, and can be evaluated, Willie many are qvdto nebulous and are a function of an individual crev member on a specific flight. Many in tliis category can only bs ovoluated at this time by Intuition and opinion, with little or no firm facts to substantiate the conclusion. Many of the opinionated iti^ms nust await actual Apollo flight experience before real answers are available. Therefore, this study will be revised and upgraded as more and better information becomes available. Basic crcv considerations must be evaluated for two categories, i.e., Intra-Vchiculor Activities including all spacecraft operations, hcusekceping, personal hygiene, and s:q>cTlniant operations; Extra-Vehicular activities. Including all preparations for external spacecraft cad experi ment operations, crew and cargo transfer, c:cternal maintenance and re pairs, and emergency operations including astronaut rescue and retrieval. The crew represents the most fleoible system contained In the space craft. It has a demonstrated capability of rapidly adjusting to the situation without severely effecting adjacent systems. Dual or triple redundancy Is incorporated depending upon the number of astronauts present. Adaptation to limited and restricted operating envircnmcnts has been rei>eatedly accCTplished with selected personnel in test flights for years. Eowcver, flights have been a relatively short duration limited to a few hours, or a fov days, in the cost extreme cases. Since the main objective of AAP Is the extcmsicn of luanned space flight function, eveiy effort must be exerted to increase tba ccanfort end working conditioas of the astronaut. �MISSION 0EJECT3VES crct; consideratiors �4 r Mtjjton O'o.lcc&lx'a The objective of Mission 211/212, as specified by HASA. is ns follows; ' 1. Conduct solnr astranotry observations using es^erlmezrt sensors. ircunted 2. Store cnrrler-AT2I in orbit for subsequent rcndc-avdo and reuse (see tUssion 213 - Lamch CSM into rendezvous orbit, coplnaor 'rfith carrier ATM from Mission 211/212), *3. Conduct rendezvous oxparimc-nts totveca CSM and corricy Vehicle for lunar rendezvous problem analysis early In flight program. Observation and zacnoureoent of extended duration space fUrJrt effects on crew mnmbors, *5. Conduct synoptic weather and mapping photogi^by cjcperlmeat using CSM as espsrliuent carrier. C » Objectives not supplied by HASA. ��A, Mission 211/212 - MISSION PROFILB AKALYSIS o A doecriptlon for 211/212 as deocribed In C-2-2n/212-2 9 «i>"3t 1906, forna the basis for theao ccmmeats as to obe relAtlve dcslmbillty of various possible miaslon profiles for Fllclits 211/212. TABLB I msslcn DeaerlPtloaa - 212 Firaf. launch Method I 212-LIi;i (ATM)-Dlr. inj. 200 n.ol. circular 211-03.1-Dlr» inJ. 120 n.mi, phuslnrt orbit 2L1-.CSM dock •.d.th 212 UM Ccnduot all e.^ei'icont8 In 200 a.mi. circular orbit Ccamonts; All ej:poi1m^ts vou-lcl be conducted at 200 n.ml. Altitude LF/ ^eter tb^ doslrGd. It may be neccssa.'y to separate LKi ^ 0^.1 durirs ATM experiment so that more than one exneria-at can be ccnaucted simultaascaisly. This method is rated #4 for crew ccnsideratlcn. Method II 212-LE-I (ATM)-Dlr. InJ. 200 n.ml. circular 2^-CoM (RQck)-Dlr. inj. 120 n.ml. circular phasing orhit 211-Conduct mapping expcrriments 2L1-Transfcr, rendezvous and doci with 212 lEM at 200 n.ml. Conduct AI2.I experiments Commits; This launch and orhitnl coquence is rated #2 and pcnnlts E^lmum utilisation of ths manned vt?hlclc at both the 120 n.mi, end 200 n.mi. orbits. Furthermore, If the LE-l must be separated frcm the CSM during the ATM cacpariinc.it, separation time fmd distance can be ^^mum (5 miles or less), This is required in the event the LE-I tt^t be abandoned or cn oi-bit short is required. It should bo rcalizea V Ii. ^snnod LE.J, when separated frca the OSM, brs no orbital rendezvous end crow transfer mist be acccmpUshed by ^,he CM prior to aborting the orbit. Therefore, a ciinned f c i r ^ d e s i r a b l e c c n f l g u r a t i o n e n d s h o u l d oc avoided. In the event this eonflguraticn is rcqvirod, the LEI crew is placed in a very hi^ risk situation. �I-tethod III 212-LE:I (A'.v:-L)-Dir.inJ. 200 n.ML. ci.rculQr 2L1-CSM (nr.elO-Dir. inj. 100 x 200 a.mi. 211-CuM i;i-2n3no30 rjid. dock to rack 211-COM (Rr.ck)-P,cadozvou3 witk 222 7JSd la 200 n.ml. clrculer orbit 2n-CSM imdcc]: rack 211-CSM deck to 212 LS-l cad troasfor two (2) crewmca 211-CSM vadock 2:2-LS-l 211-CSM dock to rock 211-CSM (Rcck)-Ti*an3fer to 120 n.ni. circulor CcEduct roappins o:qx»rlEent3 211-CEl (Rr^k)-Tj.'ca3fer ead readozvous with 212 LEM 212-Ln-l crow (IT/A) i*cGovcr rack data 2U-CS-I undcxk rack 211-CSII dock to 212 LEM Cczmcnts; SMa cequcacc Is nnich too con5)licated cad places oa uaac-cessory risk oa the 2-naa crc-w o? the LEI at 200 aoini. cad the CM at 120 aoml. This ssquencs is highly laiticceptable for crew ocfety la the event of a LK-l failure or orbi\>al abort. ^tcthcd IV 212-LE-: (AIM and MarFplns)-Dir.iBj. to 120 a.mi. circular 211-CSM-Dir.iaJ. 120 x 200 n.mi. phising orbit 211-Circularize, rendezvous and dock with 212 LSI At 120 a.mi. Conduct all experimcats CSM/ISI transfer to 200 n.mi. for LSI (AE^) storage « Corx^nts; This, method required lamcccssajy orbital changes by the manned vehicle, Sxiggest 211 CSI-I direct inject into 120 a.mi. phasing orbit with lE-I. Mochod V 212-LE'I (AS!d)-Dir. InJ. to 200 n.mi, circular 211-CSM (Eack)-Dir. Inj. to 100 x 200 n.mi. phrLq^-ng orbit 211-C^ transpose and dock to rack 211-CS!'! (Kack)-Readezvous with 212 LES'l in 200 n.ml. circular csrbit Transfer tvro (2) crewmen ty E7A from 211 CSM to 212 LEd Conduct ATM and mapping eaperimants 211-Cad undock rack dock to LEd Ccmrasnts; This method requires transfer of the craw by E/A and undcoking frca the rack by ths CM prior to dockdng with the LEd, Again, it veold appear that more time than is accessary would be spent ly the two cre^mien in the LEd with soparatlcm from the CSId, Not a desirable cocdition. �Mothcd VI (ATTO-Dlr. inj. 200 n.ffi. circular Sll-cni (Rcclcj-Dlr, InJ, 100 x 200 n.iai, 2ll-CG:i-TrQnspo3e and dccic to r:ick 2.U-CS-I rfadcrA-ouj with 212 LE-i zi 200 n.ol. Trsjiafcr two (2) ercwxa to LE-1 hy EVA an-CS-i (EccJ;)-Tr3n3fcr to 120 n.ai. circular Conduct uapiplnc c-^ipavliccnt "^o.^OO n.El. ond roadezvoua with 212 LEt-l LTL-I crew recover data (Fv'A) frca rack 211-CSM undcck froa rack 211-CS:-I dock to 212 LEM reecnreiy of tho two cwowtoii 4 5 I n.ai., CSM at 120 n.mi. Tb: method is not accejftable for safety reasons. Hlssloa PoaerlT^tlons - 211 First l-Icthod I ^ n.nO., itolns orbit (A!Ei'I)-Dir. laj, 200 n.mi, circular orbit n.mi. and rendezvous with 212 LSI 211-CSII-Dock with 212 LEI Conduct aU ci^crimcnts In 200 n.mi. circular orbit This sequence is acceptable for crew safety. However, tac 200 n.mi. mapplns orbit is not desirable when 120 n.nl. Is preferred. This method is rated #3. Mothcd II ^ ri.Toi. circular phasing orbit )^®*)-Ccnduct mapping and weather crocrimeirts oH**^ n.mi. circular orbit 211-CSIl-Transfor, rendezvous and dock with 212 LBI at 200 n.mi. Conount AIM esporlments Co^cnts: Tills seqv.eace is profcrrod from crew consideration and ^lers better utllizatim of e<^imezit than Method n - Table I. This seijuence Is rated from crew considemticn. �J'f.thccl III (Krj?ls)-Dir, Inj. 100 x SOO n*i!il* pbsslng crbll; ail-CSM-Tmnflpo?3 oad dock to ztick 212-IiEJ (A'iM)-Dlr, inj. 200 n»ai« circular orbit CU-CS!I-Uadcck r3ck 211-CS:!-Dcck to 2J5 LTSI and transfer two (2) crovcsa to LHI and conduct /.Ti'l c:ncriacnt5 m-CSM-Undcck 212 ISI 211-C3t-'-Dock to rack 211-CSM (Rr-clO-Tronsfcr to 120 n.ml. clrcxOor orbit 211-CSM-(Rr.cl:)-Conduct rcairpins experiments 211-CGI-!-(Rack)-Triia3fer and rendezvous 222 LSI 212-LE.I Crcv-Rccovc-r rack data by EVA , 211-CS-I-Undock rack 211-CSM-Dock to 222 LEM Cp^f.nto;_ Tills ssthod Is too cccipllcated end prefventa rapid racoveiy of the u^l crew by the COM, i.e., lEl at 200 n.ml. (SM at 120 n.ml. Totally unacccptablo for crow safety. Mathod IV 211-CSI-Dlr, inj. 120 x 200 n.ml. phasing orbit 212-LEI (AEI and Mapplag)-Dir. InJ. to 120 n.ml. circular orbit 21l-C3:l-ClrculGrlr.e, rendezvous and dock with 212 lE-C at 120 n.ml. Conduct all e^crlments CSM-Lni transfer to 200 n.ml, circular oiblt for lEJ! storage Co^T^onts: This scQjionce requires •unnccessaiy orbit changes the in order to rendezvous with the LDd, I.e., Cai 120 x 200 n.ml. LC-I 120 n.ml. This method Is more ccmpllcated than necessaxy. 2'Icthod V 211-CSM {Rack)-Dlr. InJ. to 100 x 200 n.ml. phasing orbit 212-IiIiM (ATM)-Dlr. InJ. 2C0 n.ml. circular orbit 211-CSI-Tran3po3C and dock to i*ack 211-C3M (Rcck)-F.eadGSVou3 with 212 LE-I in 200 n.ml. orbit Transfer two (2) crewxea by E/A from CSM to LBl Conduct AIM and mapping, and weather experlicents 211-CSK-ltodcck rack and dock to lEi CwEnents; Thin method requires jT/A transfer cf the crew from (^I to LSI, and undocMng from rack prior to docking with LS^. Appears to be unnccesseiy, conc'lic&'tc'd and time ccaisumlng If abort cf the L51 Is required. Sot a desirable sequence. �VI SU-Cfw'I (R?.cl£)-Diy» InJ* 3.00 x 200 phcolng orbll; 211-cr.l-Tro\ij3po3C» JiTKi do::!: to rack 212-U2I (ATi')-B1j*« IdJ. 200 n.iai, circulcs* orl>lt 211-C52! (Pv';rl:)-Rond02Vc-ao with 21S LEI at 200 n.iai. orbit (2) crcv.7.:.n to 212 LF^l by EVA and start A214 c::pcriacirto 211«CS!-I (Raok)-Tran3for to 120 a,ml. circular orbit 211-CS:i fRrok)-CcvnaE.ct mipplns csxpo-rlmcnto 2U.-CSM (Racl:)-Traasi'er to 200 a>mi<i cad readezrvouo with 212 LSI Lri crcv recover data from rack by EVA 23J.-CS'-Unclcck froia rack 211-CS:i-Dock to 212 LSI Cc-rr-ents; Totally unacceptable due to co.':c)l£Xity and orbital rci-m-aticai of manned LE-I cad CSM, i.e., LM at 200 n.mi,, CSM at 120 n.mi* Dot a deolrablo candltlcax. caicLUBicn Table 1 Method I Method n Method III Jlethod 17 Method 7 Method VI i?2 Dot aceeptablo Requires otra corbital cbt-i^es Rcquirco EWI and cornpllcatee emergency Dot acceptable TeCblo II #3 ^1 Dot c.ccaptable Rcauires extra orbiial chc'eges Pequirca EVA nr^d coaplicatos emergency Dcrc acceptable Table I lists tha 212 launch first folloircd "by 211 (manned). Table II lists 211 launch first foUowad by 212 (unmatmed). At this tino, uo cen state tiiat It is preferable to oeccroplish all rendezvous vith immnimsd vehicles having a passive rathc-r than sn active role. TfcGrefoi*a, the unmenncd 232 should be placed in orbit prior to launch of the mannad 211 80 tnat all Dnnojvcring is porfonncd end ccntrolled by the crevr vchi-clo (during its poxfcrcd phase). This is preferable frcm safety and pfcyclological reasons in that the crev is actually initiating and temlnaticg all povnred maneuvers and can tal:o abort action in tha event of a coHicion. Furthermore, the pilot has the plysiologlcal advcntaga of asoui'ing thTt he has ccn^plete control of the powered vehicle and con utilize his Judgment OS rcq\ilred. Therefore, ^AlsrQ the choice c::i3ts. It is always preferable �to plsce tho unEaonGd vehicle In or-bit prior to the Inunrh of the n enned vehicle? or In ths event the arjsiiGd veMclo is la orbit, to pla-- tl s ^ f .-nd P3rmit the tnsnn^d vgMcIo to Inltloto o povr3rca phase to accorTOlish the rcndcsvoia. 3aocd ou theea ^yr^.1^3, the first choice frcni sn operational poii; u Mctaod II of Table II as described belov: ^ circular phealns orbit mapplr^ and weather expcriiaerrfcs 200 n.jnl. circular orbit ? I ' rendezvous and dosk with 212 LBl at 200 n.ml. Conduct Ani ej^ierlaents B, OEERATIOHAI, MJIHEUVER RTIQUIRGIEnS (mssion 211/212) r.f ^ forcGolna elLosIcci profile, tha folloid.33 is an analvsls nancavera rcov_lred to perform the mLsslL ^iSS recard to ®^sriiSwat ccaisldezatlonad FnrOK; 21-1 1. Assinna velocity tilnmins and ffisncmvcrins is performed by S-r/B until separa-.ion. SMa includes orientation for tknspositiS Ld dcS^. 2. Tra^positlon and dwhins (starl; +X axis fcn.'oid and opprcximtely in the trajcotciy plane, +Z axla vp) ~ hO minutes. ^ a. b« c. d. e# f. g. 3« Add 2 FPS forvrard velocity to CSIi, Perform I80® pitch maneuver. Roll - 63°. Subtract 2 FPS forward velocity# For final docking, assume 15 mlnimtm pulse cyolaa of ECS control axes. Eotate mated I'chlcle 180° (place +X axis forward). Jottlsoa S-IVB using 3-IVB ECS. During the rack experiments operational phase of the mission at 120 n.mi., the following manemrcrs are performed m a basis: a, EttJ alignment cnce per day. (X axis unchanged, rotate +Z axis to +30" above horizon, maintain fine mode stability 20 minutes). �b. Uavleationcl clchtlnsa tvico poi» day, (X axis tnichoagccl, rotate +2 axis to local vortical mil por.ntcd toward aarl-h. Maintain fine node stability for 36 ninutco). c. Anoaiae the str-i-t up and stoi>plni» of alx barbecue nsncnvoro x>^r doy. Asauae c 90® yav or pitcli i-oallGav.rnt frcai nonral fll^ oUgnneat to the bai-bocuo at.&lt\\ile which orients the Y-Z plane tei^ard the sun (+20®), EstnbUsh a roU rate of 1 to 2,5 revo lutions per hcur obouc the }: axio. Aseur-.e driiil.iig mode oneo roll rate is obtained. On stoppjns, i-etum vehicle to original attitude. In preparing for the orbit chrnge, Uie *Z axis is fonrr.rd end appradLantcly parallel to the local horizcrrijal. Ihe -Z axis la down and epproxteateiy parrllcl to local vertical. Obtain required ^ V using SM idln CTiglne, luring orbit a. b. c. transfer perform the following; One aligon-.c-at (Ssc 3a). One navlGotlcnal sighting (See 3b). One midcourse corrtjction: Assuaj correction of 10 fps. Cli'cularlze orbit using main ffll engine. Adjust X axis about 10® In pitch. Brcrp RACX. Rendezvous with Plight 212. Use Qi-HCS for following maneuvers: a. Adjust velocity total of 60 ^>8. ,20 fps In fine incremants), b. Lateral translation of 3 miles» c. Vertical translation of 10 miles, (tO fps in coarse Incr^nents, d. Assume 30 mlnlsnna inpulsc Qrcles of each ccotrol axis. On a daily basis, the following maneuvers are reipjircd. (Same as item 3). If the I^/AIii is undecked fcr experiment purposes: a. Plight 211 will be tho target vehicle for subsequent dockings. Assume fine mode stability in normal flight attitude for 20 minutes for each docking. �n b. FHchfc 2U vlU ettttlon k.^op oa Flisht 212, i.e., a poaiticn abowi 1/2 rile below aoS vlthin 1 to 3 itiles aft. (Contiji«.o i*cciiilrer;c'-ts of Item 9 \^iilc 8ta{;ioBl::cplng), Poi» caeb imdocldas, subtract 2 fps oca then eajust tc achieve station position. H. At cccroleticn of fUcbt, rotate corablnad vehicle so +X axis Is forward and slow CSM (Plljj-it 211) h fps rjid translate down 1/2 mile to «-chlovo aeiorotlCBi from ths LH-I (Pll^^t 212). 12. Dui'ins the 8 hours prior to rc-entiy, cool tho fonara heat sliKld by rotating the -X axis tovrard tl«: sun. 13» For C-I/SM oepiration, the +X axis is rotated (50-70® above tho dJ.rEotloa fllj^t end in the trajectory plane. The +2 axis la oriented to upward local vertical. l^^. Entry starts vd,th the -X axis In the trajectory plans and rotatr'd epproxifxrtcly 26® carthvoitl frcm local horizontal cad with the +Z axis polnv-r-d awuy from earth. Bote; Winlmum RCS propellant at start of ro-rartiy will be pounds. Fllrht 212 1, Assume velocity trlDralng ond manf-urerlns is performocl ty S-rs?B vntU separation. This includes oricnrtatlcn for transposition end dorldng, 2, K tho tS'I remains docked there will be no maaeuvarlnj requirements (the.CSl of PUcht 211 will cOso provide maneuvcrinc for CKG unloading), 3» If LSI pperatcs undcclied: a. b. c. d. Assume one dally H-OJ aligcment (See 3a), Assume one dally navlgatlcml sighting (See 3b), There will be no barbecue requirement, For rcdccldag the LS-I will be the active vehicle, 1) Assume lateral translatica of one mile, vertical of cna mile, and longitudinal of three miles, 2) For final docklag, assume 15 minimum pulse ^cles of each control axis. �c. coTcifSKus concE-2ii;G Tins op^iy.iL'ioi'jLt. aspects (f Mirsica 2.u/2i2 Thl-s mioslon provides oovoral opblffial miosica proflloa, A rccomicndcd profile haa' been Given la paa-asraph. A. Bualc mission nnacnvcrs arc all slnilrj to Apollo reaulrcccato end will cnitall no nriW trainitiG cr cqvijsne-at revisions. IMs is on cltcimatc AAP missicn and the inlsoion as descirlbad, will ce-pler.-c-nt the dcvolopmeat of tlie basic Apollo miDGlon. The possible separation of the LS-I for csctendcd ptjrlod'j of c:^srlmont operations Is undesirable and will bo discussed lai^sr in this report. �o GF^9!\SI0k5 CREi-f cc3sm:niv?TfiTia C �t E^cpj'rjlracat Oporotloni sade: c Prior "to Mloslcm 211/212 analysis, tba Tollovin^ naansiptioas vare a. A CSII/Rack (211) in a 320 n«mi. circular orbit for a total of 13 "b. The l^Jth day sprint vlth the C3M trenoferrinG to a 200 ond rendezvouainfl and docldos vlth the carrier (232). c. Tho carrier (212) injected directly into a 200 n.mi. circular orbit after the launching of 211, d. The carrier spends 13 dtya in a 200 a.al. orhit. e. The 28th chiy spent in CoM-caxTier separation and CM re-cntrj' maneuvers. f. Six mcnlxours of <-:q)ci'iinental time avallahle on the first day of the 211/212 mission, orbit g« EiGht hours/day/mau are available for (3q)ei*i3neat3 (24 manhoura per day). h. The one astronaut in the CSM durij^ CSM-ccrrier eeparaticn, viU not be c:^ctcd to perform €:;^er3Jiionts, Tho preceding asaumptlons indicate thnt thcsre arc 294 coxhocra free for experiment time during Flight 211 (low orbit) and 208 ircnhcura arailable for carrier (based on 2 men) exqjcrlmjatatlon. This totals 502 nrnhcu's, A thorough onolyaio of the candidate cxpcric:.nt3 reveals a icivuireacat for 659 manhovcrs, including such expcriaeixt-rolatcd tasha as alicamciifej spocecraf-v attitude holds, un3toirf.ag and setting up cq.uipmi3it, EVA prepara tion, etc. It is obvlcvs that all these cxpcrim-ints cannot bo operated for the desired time because of the deficit of available time (859 desired cj^ierincnt time mirma 502 available eapcriment time = -357 manhours). T>i^ 055 cjgjcrimfnt times can bo brolan doun as follous in Tablx: I. V ' 3^ �TcbXo I All 3 crcwaen ncc(io<l ^Zwo erevmm ncsded One croua^n needed 1^50 maniainutee - 13th day 616 maaairnrtca - daily lot - 13th day 26 inamiiinc^ico - let, 7i;h & 13th dey c:onminutcs - dally, 15th - 27t;i day 600 Kfamlnutes - l^th & l£tb day 232 manmimrtcs - 17th • 25th day 367* - dally, 1st - 13th day 180' - and - 8th day 720 manminutcs - l6th day 900 maninlnutea - 27th day 170' - 3rd - 13th 903' - dally, 15th - 27th d;^ 10» - 17th - 25th cUy 120« - 15fch, 17th, 19th, 21st, aSrcl day 60' - 28th day Inr-'jrnueh do -three are avollahlc for & wpviTmiiT^ ctf 88O moainlaiites oa eny givtrn dry ( of -fiiGht 211 ), there appears to he no nausucl prohli^a in performing "of the oMperlircaifcii retpiirlnc three men. The ;jc?.vy ragjxlremcnto for all three ei-cvnrca on the 13th, l6th and 27th d-iys of the mission sharply cmtoil odditional c:qjer3.ma.itatlon on those drys- Ihc remainins tlir^ allocation oa thc^so three doys for the rcmainlns c-Aiv nzoabera io as follo-.ra, Txra msn available for a rmxlimrfl of 520 Daniuinutos. Eurins carrier operation vhcre only tvo men are c/arllable for c:q)srir.cnto, it Is estimated that there vlU be rrrsainutes available for two men and 200 nianteo available for one man. K can be seen that the 139ft manmlaute, doll-/ (l5th - 271;h day) requircmcato for two moa, cannot be net. Iloroover, the daily refi-iairciasnts of one for 903' per day (15th - 27th day) cannot be satisfied. It should be pointed out that e:q3criiK-nt3 l-Wll, 14022 and KQfjis have no In-flicht requircnonts. 14005 and MOO7 were combined for purposes of ecir tine study. ^-012 uas ccmbincd, in part, with MOI7. I-K>19 is also coribincd with iK)12. The FvA rcqulromcnts of S005 and SOOS were combined. rVA rcqulrcaBoats for S016, SOI7, S018, SOI9, S020, S052, S053, S05f^, end S056 were also combined. A total (rf 16 E7A's, requiring 97«2 uanhours were prescaitly required. Experiment SOI8 takes 5^ the manhcurs for EVA'a related to micrcmcteoroid collections. All these EVA hours Includa tbs pre and pcst-Fv'A eetivities OS well as the actual EVA tine; The longest period of ZJA outside the spacecraft is three hours. �(D rExpcr^nto SOO5 SOO6 vill bo flown on mebfc ru end wlU rcoulrs a I50 inlnufco EVA on oatronrcafc apendlcc 30 r'inu;:c3 ouiside tl^ c>rXt collcctlcs film ccnnlstois frcaa tbo raclc. liuc activity It ntjccaoniY to ccrry ono F13^3 for the EVA irorloir end 01,0 PISS for the Gtcndhy in tba cvoat It is nccosaaiy for him to rcscuo tho LVA wor:ser« There is ccricus donbt if the C/l-l can ctow tvo Pl-SS's, It mDy be aecesofuy vo pi'ovldc tlie stcndty an 'mbllicea., hooked into the C/il ECS lone cn^h to allow reccuc oporationo. Another desirable cpnrc-'a la to do the basic EVA by means of en unfblllcoa, Foi* EVA emcursioas tho carrier, it is ooomred that two PTSS's vrlU bo ovailable and that the carrier will have sufficient rcauprOy cranaoditlcs, Tho f EVA wherein all the iVE-I cJtperimsnt packecos ore to be rcti'iovcd (27th inissloa day) should not bo undertaken until the CSi has docked with the carrier, thus utllialns a full crew of throe aitroC&tluO« The followin£5 ei^crimcnts inrpose the greatest time diaipoT^/^c m tha Apollo crewEon: C M012 ^M020 ^005 esSOOo - 50h 270 180 170 Honnlnv.tca I'uuminutcs Kcnminutcs ilanicinutes per por per per toy cry day doy - drys deya dnys dcys 2-13 2-13 2-8 2-12 ) ) j ) Plight •*3018 - 270 I-iGnainutes per dry - days 15-27 (EVA) ) **3019 - 538 Manmimttes per dry - days 15-27 ) •*3053 - 193 Mauminutco per day - drys 15-27 ) SSA • iyi !f^ 15-27 «S05t> . 5i5 I-ianntnutes per day - days 15-27 ) ) Fllg^rt 212 « An additional factor which has a serious Impact on tho accctnpllohEsat of euoporirairts is the night and daytime experiment pperating requircaGnte. The e:^p^i-3;nt3 above, marked with can be done in deyllf^ only; •those marked ' con bo perfoimed only during the nl^rttime, A glance at the estsbiishad misoion timeline shora 90 manmlnutGS oU-CTtted of exercise time. Inasmuch as M012 requires e:'"ercising m the ergcmater, these allocated 90 manminvtes could be u-cillscd for performance of exportnant M012. Moreover, the set up time required for M012 is 60 ' menralnutes per day. If the ergometor can be left in an asscsiblcd poaition, this would save en additional hour of tixoc. 1! �c Ccn-t'rcJ. Ccnc.Tvnlon3 anfl Rogccxicndatlcma A typical" dry of lUsaioQ 211 ^ras timalined in texina of e:spei*lmontcl oporaticna and frm thlo tlmvline tho foUoulns conclofliona and roc cfor,gndntiona ware evolved; X, Periods of Watch xost be uf-ilizcd to occonrnlich the c:;porijacat8. Tho duration of »,'atch poric^ vhoroin tho crcCT.an can he e.wsy froa bio watch otation nrst ba ercbcndcd fra-a 15 to 20 minutes.# Otherwise, experiments reqtdrics I7 and 18 mimite continuous ciperatlano will have to be re-evoluated. 2. Astronauts miat give up po-tlans of ttelr sleep, nsps, nci-ocaial lygiciic and lunch hours in order to schedule the ej^jerlments. 3. Dally o::poplmcnt participaclOTi by crowmon will bo as follows; Pilot ITavigator Engineer - 319 minutes - 395 minvites - 36I minutes h. Eu^arlmznts requiring 30 continuous minutes of saqjeriment craoj.T'.tlon can be pcrforiKsd only during an astronaut's standly porlof.." Ihis means teat c:y crpcrimant i-cqulrine 30 successive minutes can bo pcrfor.r-^d only once per day per men \-nlcso it is all right to repeat the some eciperircnt within a men's 3 hour ctendTy period, Experimarcters should tiy to arr£mge c:<i!crlJn3nfco so that thmr can be porfonsed in 35-20 minute inororarrts. 5. Eccauso of the great demand on crowmen's tlma, it will be naccscniy to set up appoi-atus for cxpcrimairt "X" end do pert of that expcri* mantj while this apparatus is still set up, it will be ncccsoexy to se-t up apparatus for cuorerlzrent T" and then perform sera of that csq^oriciim.t., A complete caa3ysis of space problans need to be undcrtahca in connection with the csperimant timelines. (In other words, available craw time alone docs not give ics a realletic picture of \diat can be cpkimaUy nccccrolishcd within the C/li,) The value of simulation cannot be over-stressed. 6. Though the mlssion-sssigned experiments can be performod curing Plight 211 within the allocated tirus, the C/H will be a busy end crowdad laboratory. The aaditlon of e PCH to cany soas of the exp^icontal apparcrtus would significantly r3.Ueve this ccngestlon problem while saving a sizeable amount cxf time. The inclvalco of a EC2i on Flight 211 vcu3^ allow the crgjcrimcntnl aK?sratuc to he Initially set up and then left in an assembJad position. If experimsrrt apparatus for Ho. llOOk, WQ^, K012, MOlB and 1220 could remain assembled, the nstrcmauts would face a more realistic time schedule. c # 15 mimite watch period \33 rcccnnsnclod by I'Tcrtin CoBsajay m "Cre^Qperaticas Eequiremonta" dated 10 Aiypist 1965. �7* It l3 Intcrcotins to nots tiuit once tb© typical mission tl^rollne of events \ms ccnplctcd for FUx^lvb 211, there uerc a Diais!rm of 3^ hours for tbn three crcsnren por dcy on aa iiidlvichtal bnais. lOnly one icna free) Tliis cucsenta that O3>orim;ntcr3 should look very closely at the car^Erincnto to detonnino vcys la which e:-7/orlnents could bo cccdac-bcd by ctio person, rather than on a pair (subJcct-ezptriiKater) basis. ^ «, Jf«allx-d etperlmc-nt cpei-aticns data for mssion 211/212 con be found la Table I. The fcUoulns cocxeats ^ply to the Indlviaual espca-lmeate ^dilch present problems: 1. KOOl^ - This e^erimeat req.i^lre3 17 mlnube time Inorcccnts. HeccaECiia 17 minut-e avcy«fr(x>vorlc ollot.'ancc diurlnc astronaut's >ntch periods. 2. M012 - Thouch the annVsts have requested this experiment to be repeated three times a dry, it is reccmmonded tjrvt it bo done only tvice a dsy. Tho oajj' moans of scheduling it three times a Stbla ^0 ^1^ appuxatus scb up permnnontl;' - cn improbabllllgr 3. M020 - Bequlrcacnts for this 30 miaxite caroerimenfc incividr- its ®:c^tica tvrlcc per day on all astrcaau-ts. It io recoscrnded that it bo per*Oi-flcd only once per day. Otherwise, it inroosea serious schcouling proolems. 4. SOI8 - At tliis tine, this c:^parimsut reqj^ircs one 135' IVA per day fw the orientation of nicrccetcorlte detector plates for a total of twlve days. Reccmmand that: ' a. Tho number of FJA's be halved, or b. Means of rcmctcly reorienting the plates be devised, cr c. Detector plates be positioned so that visual inspection con be made from within the LEI, thus possibly cUninatlng the need for 12 EVA's. 5* SOI9 - Ccnpletely imreallstic rcquircnont for cons-taat sur/oillsnce ly on astrcaisut during all dark-sldo orbits. Reccanncnd tbjtthls tine demand bo reduced by 75^, Or develop an automatic device capable of meeting <u^>erlnieDt objectives. 6. SO55 - Requires two cstroaD.trts for a tottil of ^h6 minutes a d^. Reeenmead ttot this rsojiirciaent bo halved. 1, SO56 - Ells ei^^orlmcnt requires 320 hours of Plight 212 time, Incliiding spacecraft orientation. On a 12 day flight, this means ten hoars a dcy are to bo devoted to this one e:q>cilmsnt. Reccsmsead that the exporlmaafc be seriously analyzed to determine if it is worth this Each time. Reduce caqoerimeat time by at least 75^, �. / n c I>AP MrSStON- tim«um£ MJSSIOM- CVKV OF MISSION _ Day of . y of T events : JC 7A . .. • day mission DAY NIQHT 0<70UN0 -STATION-COS^fiASE ORfilT HOURS FROM K.Z /!?• V2 -V-»^ u < ?BC m w/^c EXPERIKIEWTS OPN ^ NS I EMM I M K M QMT 16 SO rroo laoo ^ifpi 11 [w^BC ^ I900 ./ t:aa-rc|%< ^)?N B B Iga!--""^TVYX g:!&gS^lfem»s fejv/g^cH •- 2000 a ^ ^ F-HI- EioQ eaoo : zaoo atoQ moo CBoo < 0300 oq oo isoo la oo DAY OF MISSION bAY NIQHT --^ROU NO•~a' STATION I -CO^AAOC- .' OR SIT HOORBFRONljC 10w ^ E IS < tu o <. . ^ 3 SLEEP WATCH- sleerN •WW V\\-\ \\ WATCH- - W V\A \ V\ \ \ \AA \ \ \ \ \ V\ CXPERlMBMTS r'XfipL^ H ^SW^i5^cs::^T -oyigg/rgtON QMT OSOO 0600 0700 <>soo 4- I *QOQ »">o 12CO isoo I Koo ^ �' MISSION 211/212 O A 4* B Q O o -H e .4-1 h rH I0 D U SXPERIHEICT ln»rilght HionocardlogrsD Blo-Aeeaye Body Flulda Calcium Balance Study In-Flight Sleep Analysis Human Otolith l^inction Cytogenie Study Bcercise Ergometer nioraclc Blood Flow Vector Cardiogram Hetabolic Bate Keasurement Pulmonary Function Red Blood Cell Survival Microbiological Assay Antl-Q riastic Qarment In-Flight Nephelometer Space Suits + Lunar Exp. Hardware Synoptic Terrain Photography Synoptic Weather Photography Trapped Particles Assyatetry X-Eay Astronocgr Hicrometeorite Collection OV Stellar Astronocy 0"/ X-tey Solar Photography Apollo Telescope Mount White Light Coronagrapb High Resnlutlon Photography of Solar Ataoaphere X-Ray Teleacope {21V215/216) Ultraviolet Spectrometer Intensity of Solar Flares gpectroheliogrephy in the EDV G O <> O ^O h ~ to M X X X X X X z X X z X X 'z T z X X X X X s- Xz X ZX X X X X z z X z z xz ZX Xz ZZ X Z Z X x.xx x x x x z XX z zz z zz X X X zzz X } z z .z z x.z X'X z_ xi X X X X z ZX X X zz X X X X X X z �•Mr -: ^-r--- - - • I. ' HffA/«pyiCj : . ff // "rv-Firw77—• , /•^PN-kakv/^^HTVI i ' '•// ff i/'il w_ I- ff'*'1/ /fYYi s • I" ^ I- v' ^ x'—.- Jtk^ 'i- •"' • /" -X V " ^ I m J/m . Ch^C^/^s.; J ; ff •: ay JA i ' c/4.L_ ' 1 .—i-_ *2iv..»6's v7; V -• MPP-f ,. , I S70AS3AYr apuy Ftujos.: I ... NOME /o^f NONC ANAiYSir i'.S_t„7 i Pfi RjpVAL'i-J V(> » .•A/f Ar'jtfC U«) £. yM. 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A 5 T f ^ y p V R £ T A T -T ' ? A * C T | " ' P « f V ^ A i s T ^ r - •:./^- - • " • s h r p r e 9 ^ f / T J ••IV - f : - I f J f ? t i e L 1 — . . I . . , . C.Wai I o t. c « ; i i c . 7 : A A y iLP • f - . t i A . ) k . . : : ? , 7 M / Y • t Q.^jLy.:£.-,- f. arc .P'M/} ycrj.. f2e.£Lri]j fA<£c M i M . . I 'I w i ; S v ' - - - : f - Ii . I : e i L : t b p . i Y l r iPPCl r C'yA r p M I 3 . J | f £ . D _ ^ . ; : i ^ ! . S >ik~. . I.,;. M I W ! ; • » • • , • i w ' h ; Wsp, J £>••? 0 1 h/tlW t • t - . 1 — E V ' ; v C T ' / ' ^ s t w r i j •. ..I.. 1- •. . . " V T H r A T f ' f r^:-p P R h V J 'K 1 i w j 7 = :i;;• H^.p '*)FEpr r/r- ts'-tia.vnS'n r^o- V^.rr j W ** f l ' i / i ) » H : ' i . E.-Y*x I V '. i l •i . • : I . . . — r - r i » f v ; • • : ) l£/}"Ct.j«isl B - - - • 1 — H - S h < H e C '3 n T 4 �i f C / X ' - • jr ;. juiy.Jvtr \Cr •. ' • —•— A * dtJirtkt^ J . 1. I .. r > ^ T o T /^ ! Sheet - ^ t>'P ��For o;-:p2rlnu-nt3 S005 Is ncodcd (In C/JI-Fllchfc 211); MOO6, tho following !27A e<iuipacrrt lunar SpiaCQ Suit Aaseabl^ (3) C'A (2) LCA (2) era (1*2) •PISS ( 2 ) and spores Al-dJ (i) and spares Aim P^iol Sijpport 20' Tcthor (2) EVA Visor (2) ) Boaed on ) iVDay Mission "^If only ono PLSS can "be sto"/ad in the C/M, the standby crowaon will need a twenty foot nmbillcal (hoohed into tho spacocraft ECS) to perform roooue nisoions if necescesy. It may also bo possible to substitute 75 foot itabilicolc for the PLSS'o. For experlcants SOI6 and SOI8, all the following EVA equlpoent vcwld bo transferred Into tho carrier (Fliglat 212): TI-IA (2) LCA (2) *C\'!Q (11*) FLS3 ( 2 ) and spares A^^J (1) and spai*cs Al'U j\xGl Sunport 20' Tethers (2) EVA Visors (2) *31och U Pressure Suits (2) •Portable Light )• ) ) ) ) ) ) ) ) ) Based ^ ll*-Day Missieu *19 additional C^vG's will be needed to "bo carried into orbit by the carrier. (2) Block II suits also to be carried by carrier. It should be noted that a handJiold system must be developed for crcwrnn stability at tho work locations. Morec/cr, if an AJS3 is not used, a handhold ^stcm will have to be developed for crewman transfer. �o CRsw con3r:rPMV.eio:3 CARRIER Ri:CO:.::-u-ro\TICTiS �Crev Ccnslflgratlcais - Mlsaica gl?./glS Tho cdcctlon of Q carric:.' tajod aololy c© crow con$idcra'lilons lo on cs^ircaaly dlfflcwll; •took. For c.-ftng>la, -fcha aMUly to iBa5.ntaln on otation for a pariod of two vcate ii tha Gcelnl has bean dcaonotratcd In a ain^jle flight by highly motivated astronavrts. this particular ease, tba accccmliohmant was a chaUcngo of e slncolar feat rathor than a routine occurrence. Tho tread today is to incrccae the vorKLoad ccd tho nisslca duration scvei*al fold in a spacecraft that is so/crly restricted end limited for a I'f-doy mission. Wo mart accept the rojulto of tto Gcsninl end tho initial threo nnn Apollo mlsslona as islnliim E;trada"da for crcv/ habltabillty and ccaaforb and attcagJt to iarprove thcsa standards for tho AAP missions. Habitability Environmental paramcrSors are not a consldsration for carrier tradeoff studios in tbat the cabin atniospherci idH be maintained at 5 + .2 p^i normal, 3^ cmnrgcney end prior to BVA egi^ss, 100^ orygonV relative humidity from hO to cabin toapc;rature 75 + 5*^ aad <5ebln dicoldc not to excc^ 5 millimeters of morcuzy for nOTngil operation end 7*6 mn. Eg maximum* Crew Comfort The LEi and AIEl rcpri>3cat3 a total iMressurizcd volnr:c of 8o0 with a vorldng space of 122 ft-^ for two ni'ai* Weiste disposal end storage, food and sleeping facilities are ninlmiaa end sized for o 2J<-~hcur mission with a reserve tlmj of 2k hours. Eor-iaii crew operation requires suited astronauts that may'or may not be prossurisod. Fccal collection with two cuit-id cramcn in tho LE'i would be very difficult. The ECM on the other bond, vlth 356 ft3 of pressurized volume with sepasrate waste focilisies, offers more privacy for waste collection. The cppoz'tunity to brcalc the routine ccn be tc3;en advantage of by utllizins the movements and tasks esscclated %7lth the food storage end preparation areas. In addition, the necessity for the astronauts to move around within the U".! is vciy liralting* TIis actual operation of the vehicle is acccngjlishcd from tho craw statlcais, Tho RCM could be designed to parciit mora moVGmmit of tho crow which is certalniy dcsixablG on missions of 2U hours or longer. The ability to r-aaovc the pressure suit for shirtsleeve cperatlon oiid for personal lyglene, is highly desirable for all Apollo Applications flights. Equipment and space for shaving and cleansing chcuid bo provided for dally use. The IE>I can be modified to provide this capcbillty for a two-man crow. Pressxxre suit opieratlcao, including EVA, will require suit storage, and ability for crew to inspect, clean, and diy each suit 53 �prior to storcoo end use. iluy siilt<:d opf^rafcion vill require both oxiw moT-jbcra to be la prereviro otdta so tho dressing ond denning of the salt, rcaovol and drj'ins, will probnbiy ;-ciiuirQ the utlli-Eatioa of all avallablo free prcssurited apace. I;o other taalts, ecporimcats, or pro cedures nofually will ba ecconqjllohcid imivll the suits nr« stored. Internal arrnngoiLcnto, Includirg proturberancos or £:harp edges, must be ccOTr.tlblo with tl-jy ncveatsnts oact aotlcoa rcqplrcd for two astroaeirts to adequately accomplish all cperatioas regplred with th.'> auits, ModlfIcatlcma ore required for alsoJ.ons that require separation a£ the U::-! from the Ccrmend Modulo for periods in excess of Sh hou.i-s, A seven day rcnnned Lul separated from the Ccancmd Module wz^.th a t\ro-ir2n crow, requires fccal collection and ston^go# vxine collection and storage/ dump. It is rcccavrcnded that (sclnting food storcge end juaparatica bo cnlnrced to include a preparation a:v^. Perocjial hygiene f^ilitics should be modified to Include provisicms for body and dojital clcannlng and shr.vlcg. Shirtsleeve should be normal operating modt;. Chnnge of clothing cvoiy other day, or threo changos for the seven day mlooioa are minimal roquircncnto. The LEI has ao^ provision for sleeplTig other than napping on stations during the normal 2h hcnu' mission, hhca awry from the OoTsend Module during a basic Apollo mission, tbo nrsw is crrpcctcd to falrlv BCtlve for the 2ij. hcji.u' period. no-«T.vor, on a ssven dry nlGcion with the existing ci-ew station restraints, napping on statlcn-c cannot be ex pected to suffice for sleeping faci:'J,tle9. Provlslcas for uninterrupted sleep for a miainrun of seven hours for each crew member la^at bs provided. Similarly, this feature mast bn retained in its existing form In the EC31, or suitable facilities provided. The Conmnnd Module aoncally provides the crow caaforfc reqoiremonts including a "gallsy" for food pi'sparation, and separated waste col lection and storage facilities. It would appear ot this time that the IttM cculd have at least the same capabilily as tho CM. In fact, depending upon the •Ission, the available facilltlGs could be euqpondcd to provide additional crew comfort. Craw Safety The separation of the experiment carrier. I.e., either the lEI and AIM or the ECIl and ZiE-I from the Command Module, represents an extremely high risk sitv.atlcsa In that the ability to abort from orbit is delayed until the crcv is aboard the Ccmmssd Module. �6) Ths ability to ecrcso froa the Lr:i tlira;3h tho batchss In tho eiroat two mm ore conaif.tia^ eiqiorliucats, la (UiTicult end tiying ^indnr noriLtJl coadltlocs. Es-jreoncy cgi-cos of two {Vitroniuto Siid trcnsfc:.' to" to the ^ preferred to roadozToaoing end docldLng, providing the Cli is ^-oondicg iry, Sio ECJI eoiUpped VTlth the airloc"':, cpprrers to offer M crislcr egress than thrcn-ii the tmmol aystoB on the Ul-l, Tm airlcc.: can ccccr--aodato only one astroaa-rt at a time; ho-^evcr, the opening dimensions aro considerably Inrger end more accocioodatln'j to the evltod ootroaaut. Escrgcacy egrcoe should bo quicker and less to tho astronaut. ability to provide assistance to a dlstreasad astronaut dm-ins or crcv transfer appeni-a to bo easier and milcker fToa the RC4 airlock in preference to tho LEi hatches. Retrieval of tho disabled astrcnaut through the airlock probably can bo ccc^Uoh^d with less difficulty and capenditure of energy than through the hatch on tho IS.I derivatives. " Conclusions n».ri I-S . conilr:^n.-Qtion for tho noraiaL 2h hour mloslon, and tho abinty wO incorporate addicloc-al crov hnbitabillty, confoit, and s^c.y rccalrod ^or a seven dry misolon, a revised LG-I cnn be dcsifncd to ^ccmplish the i^sslon. On the cthrr hand, the fcatur-es alrerdy available w Module, nodlficd end cxpsndcd in the ECM, ccabined vith the 3 an ^rlock, certainly pi-ovldes a safer, more hnbltabillty and coaiforfceblo configuration for a two-man crew on a seven day mission. « Carrier Chice - Ist, ECU; 2nd, LEI �c^cmrasj™ E^>?.fimy?ron3 CRBtf CCE3IPKRATI033 �V 4 Connliislono cind Reenwwi/;^^3^.^^ons mont ccjnaidoStioaa^ Sa°cSrl2'coS^°^ spscccrcft operations, cxpcri~ Prccnt^ OS relate to ^ LE!/Aa:i configuration.'^ CS^VJ^CM/Aril or with the CSt-1/ cecoii^lisbed i,^tlUn the mlosiok Pi^oscntly defined ccnaot be times and rcpoatabiHt^ ^ opezatlng the niosloa could preuce voluaWo oxporlmcnts, me^s,^^Quantlty of o::perlmental-dntf^f- ^.^^-1- inrtopoildait f ^riSSS™- ssi? LT? —-s ssSi~'/•~ \. presents a vc^ siSiS^'^rthQ^ caiTlc-r for seven d^ys event of nn emei^eS^ Invoi^rn^^^i^S^ abL^ ^ ^•psnmcnt comer roust soai-hw tiansSr ^ crewa=fl,.ln the Cororond Modulo before ro-entuy Prcccd^Ss^aJ'SliSrS''''^ ^ alccpiyat'S^^vS^^' iJito tho LHM and are asaiKscd part of the ROI. «incorporated •££'?^.iSSSS-.s?S~=-^i~ O s-? ��CRE'.v C:":V.T*Oi^S IJD l'-3b"IE^TS 'KE^lMJNAir •1 A-VjTJiiT if-6 Approwed (i. A» fiotUji,' / f^r9M Operas .ons, AAP �CKD/ (iPBoATJO^;? R£.;"^^;7^S^-TS YAHLE Oi CON" :nTS Human Factor SoqulrciBcrta Cperational Scqutreraeffis Astronaut Training Crow Equijauent Data �a. Miacion AS-2C'jA, fjC-012 Cpacf?raft Oijorauioa Ri es b» Aosusip fc '*.oin,3« c. Espcriaent Tallot Opp'-a^Aonal Conat.-.ilnt, fi5-3/?!AA; d. NASA Jftttort P0H/0]3VL~l3« datfd j5 L -Tairjajry .19£;6» e. NAA tntercal latter, 692-80't ^50-66-')17, dated 2 Fob;.'uai7 L^6, t. NAA internal Jitter, 692-3cA-050-66-020. dated g. Design Reference Kxetnotic LE7)~M0-l2., QAEC, dated 50 C.tober 196'». h. Apollo E.;i.a.ncioa Syeteaa - LC-5 Phass- D Fxae.1 Se,,or:-.. Vol. 3V, dated S 1965« i. Apollo S-;t£-ns3on Systems - LSI Hiasfj B Final Remrt. Vol, TTI, dated 8 Deccrrber 1965« J. Desj-gn CritorJa and Reference Data Jfcindbook for Uv>ar- Stpleration Systeasf Vol- II, NASA, li'ir.tsvllle. k, Systea A'^alysis Sxtnmary, Part II, Na\ SID-65-15;1>-.2, dated 29 Dcoeaber 1955, KOTS: HAA« !C101 Febi-Uery 1966. bliore appropriate, the l«iutf'- de »igcatiwi of tb© souree reference is placed by the psi'agraph nuBflsev", �r X.O HUMAN FACTOR PS^UIR>^-?}TS 1.1 Scop** Theco requ-trnraents applj to cqui.pfj»cit and warl: p.i.n^o which dlrcctlj affect the flight cre< durtn^ Intr?veh1ruJ-ar Ar tivUJos (IVA) and Extravehicular A:5tlvit5ea (BIX), 1-.2 Purpopo The primary purpose is to eptabldoo spcclficacionc for the equlpsenv ouppLiftr and AAP design and tticsios plaanlng g"o"o.t, Tu is an ohjoc bivB to tnaintai-T. st.nndordizer-i.on with the cr.le .ir.g Apoiio svotem hardware, 1-3 General Reqti^"roT.anta 1,3Ipplementatlon iBplcaeu^at-ioA will be ucrorplichod through decdgn roviowcioterfac© docuocrtation, oni -confiyirtttion copvrol. l,3-»2 f- _Equ'prerit. Slandqrdtz^At'on EquipRonl coaf'.guraticn ehojld be sini:ar to certstieg Apollo flight eqalpmcnt BO thti ere.- will require minlinal special trainingc 1«3®3 Equtp«>ent. Deslgrstioa / ' Bquipe-ent will be named for case of Idnitif-iration by the .crow rather than no confom with sciectt.o.r custom or academic precision. 1,3>^ Exceptiop-s to Specific Regvirrpcnta Exception to specific requlcements will be made by reference to the general requJrci'.ente, la3»3 Supplenonte to Sreclflc Beg ji rcmentg Vhen a des5gn requirement is not spccif.cdc typical Upoan 2hglneeriag practicfs will no followed, Tho following docunentB are recogrlzed as authoritative in coating good Euman Eogineering dfoigas a, KtL-ifn>-13036 Zk April 1962» (rriL-STD identification Marking of U.n,- FP.'.tn , P.roperly. G b. KT]>STD»^3A 1. c, HII-SIi>-803A-2 (US/if)j 1 Dcrcenhcr .I96'i; Rirt 2. d. HIL-£1».12B, 18 Kay 1959^ (AhbrcvJal ionc for use oi. drawings and technical type j.yb Ucnfcion.n). (£>•?- �NPC-^CO~lj 18 RTid ^{SC S-ofp" wont i^l, :?ev . B, 26 April 196i», (Ap')Llo Con^Jsun-Jlo" iiir-imi). MC-999-00'J7. 15 Septcraijer 1952. KAA, (Grrcr.il CpcclfiCQUoHtiaan ahcincering Seelgo nrltexlo fo;* Sfooecraft Syst©a3),. �'• • •* Ami PtfYSlU/iL PJKTGii HPXfJ^ !.-^?4r:r."".'^ - ''•1 P^ro-il Cr-.'-ti-.a 3jyi» Crr^ir'a Cj) Tfie 6£bo cf -be cr^wrar ahalJ. be wdfhii: the tpj'jjc froi 5» to pc?)i-.'aMon ac ^iven bei.ov.- y^GTRONAin' STZE Clfr'fI::n'A Mcnonreracnte* IIS.TGUT Fn02l FLCOR Stn,ure LVo Holghtj Standing t.cr.-it-ale Crcrch Foot Length Foot Braodth bpper Anu Langth Forparo-IIand Icagrh Hand Lnngih Cheat Braadth Wa.'-St Bri adth Hip Breadth Wrlot Brcodt-h Forc-nro to Grip Lcngih FuQciional Reach Eibow VJrioc teagth B"ihev;-Raot Height 66,30—70.9'3 62,1/V.6?.O5 56,'? —6'4.„25 30.31--33.79 lO.C:-11.25 5,70- i?..52 11.85—15-59 17.i?—20.39 7.2:— 7..83 n.3-'—12 80 10.53--12.'?8 12.7':--:'A.33 2,2?-. 2.'I8 13.1 >-1'? .56 29a:-.5J^,.hi? 10.8 j—11,96 7.51—iiooa 69.25 59.19 32,92 10.-56 h.07 •5.57 .'8.'t9 7-'?7 12-33 12.36 13.88 2 <35 -?3-67 31 ;i2 8,99 DEFras Ccc-ot Depth Waiet Depth Bj-^cok Depth 8.3?—• 7.M«— 9,92 8,«»2-^aD,55 8,95 9-2? SEATTD nEASBREHENTS ^ Sitting Height £?© Height^ Sitting Head Height Kr'ee Height E2bow«EUbow K'^ce-K&co Shoulder Breadth Rip Breadth Buttock-Knee Length 35,00—37,67 29,21—33.5'» 83—5.6? 20,r .—22-83 16,97-~20;20 13,31^-15^51 17 51 ••-I9.IK) 15^30 22.03—25.63 ?6.il Jl. 36 5,29 21,8.5 13,90 lV,8S 18-91 ;iij-58 23.9-9 �'"A •• ' c?r"r • i-) Kccijiureae'i le* HEAP lOEgth Bro-vcii-.h Cli^unforcnce 8.35 5.71— 6.1'f aa.Ofi—25.70 7.^3 r>.26 22.7A 55.3f»—'!l-53 28,8f.—3i?.''0 36.2(>'~38..'f6 21,0^^—2^ 15..2>-18.07 13-.9'' -.16.77 .Qif l2.0'/.-.i5„27 30.7f^-ll.8l 6,5"-.- 7.52 9.13 12.00-13.5<» -I'f,5'.'--16„06 J3.5^ 5U93 CIKGUMFiSEHCE Choal: Wnis" H^.p Opppr Th '.gh ij>wor Thjgh Calf Arvkic Bictpa (Flexed) Foitaro Wl-l3t KatJd WaisI; Front Haf.et Back =,0 vilie 1'>,1j6 .).o8 15,10 IL,39 7,03 8.7/ y,i.S3 isj<5 LlfIiV3 % Vertex to Seat *A1X ficasureacnta >.8a-59,oi 37„7i» ia Inches Dloplr»y and Coatrol IcnM'.lon (J) Control pot^ets and £i.iop".ays shall be so located An respect to tho cre*<?can''o restrained oponttiag oto'-Jon that they are wltWn the noriial reach dint-ance of a 5tt to 95'^ percentile Pnn, This fucctioral ans rca'-b dietaacp \a defined 5p tho foliowlcs tahle, PfiOoX Xnyorte should be constrained betveea tiere Units but noiT'.illy clo.^er to •:iat defined by the 5a percrntile cret7r:.->:^. All controls will bo adapteblo to efricicoi. opora^'ofl Jjj eifjor c)i»r»s of preecr.tro of esilt, PraleiKlnary Ita-tJi-- Cfper^aertol tiata indicntos n tKsxinuro forvard rea-?fc of a 5>2 pereentiJo cian in a epnce cruit Is lens than 17,0 inrhfis. (of �nsiGHT A30VE SF^T IW -_jNCHEs_ mmi 0 15 30 'if. et) V5 90 105 u>c 17.^! 23.9 2?..6 29-3 23.9 2S.3 25-1 20.3 IC.5 23.5 23.0 30.0 30.0 29.3 2S.9 21, :t 19^2 25.8 28,S 30.8 3U1 30,0 2G,9 22.2 19.2 25.3 29,1 30.7 31.2 29„i 25.7 ZO.k 21.0 26.5 29.5 31a 31.5 30.5 29.0 24,5 16,8 21.0 27.0 ro .0 32.0 32,5 31.5 29.0 25.>5 18,0 22 „0 28,0 53-0 " • T 22.0 27,5 50.5 2if.5 29.6 >a,i Zk,S Sib I-'arrr>zt.! !•» (Tr,) «6 0 6 12 18 24 30 56 42 48 • . 17,0 19-4 21.3 21,6 20a 17.4 12,7 * 21.5 22.9 23.4 22,0 18,7 13.2 25-5 25.4 24.9 25,7 20.2 13»6 16-0 22.4 24. 9 26.0 26,4 26 >4 22.4 36.0 17.9 25»3 27,0 28a 28.0 27,4 23c9 19a SOjbPorcflnfclle fin.) . % 23,5 25.8 26,0 25.2 25o0 .19,0 iao3 3.7.5 23.0 26,0 27.0 27,5 26,9 24.5 19.5 13.5 •19,0 24.5 27,5 29..0 29,5 28.4 25.5 22,0 15,0 20.0 26-0 28,5 30.1 30.5 29-5 27,0 23>0 16,0 33,0 32.2 30-.0 26.5 19o5 • r 19,5 22.5 24,0 24.5 25,6 21,0 17.0 11,0 0 ^6 0 6 12 18 24 50 56 42 48 32.4 30=0 26.0 19,0 PnrccntlTe (In.) S 0 6 12 18 24 30 >5 ^•2 48 22.7 25.1 26.6 26.3 25.9 24.5 20.8 .35,4 21.6 27.2 28.7 28,7 28-1 25.7 25.5 3i;..3 ?.l„2 Z2A 25.5 28,7 29..8 .30.1 29.4 28.1 24,6 18.3 27-3 29.7 31.2 31..L 50,6 28.1 24,5 ..8.2 2? 5 2B,6 3\a 32 5 53.0 31-9 29.5 26,5 20.> 34.0. 33.3 31a 27,5 " 30,3 33,.2 5'»<6 35.0 3U,-'i 32.0 29-0 21-9 25.5 30.5 33,5. 35.0 5s,:i 54.6 52.7 29,7 24.^<f. 35.1 25.2 >0.5 33,5 5sa y,,e >5,2 55.1 >0,0 �PrcL'r-.ry i j 1 tv Th- eq.j*i)0.;nt «. f I !)» il'- j)gnycJ pr^•8a•i^^ ctfit The fflt-Ml-i.iy e-^V.ecvjvliof jjiy ea-'Apollo do-a not pi-OJid;? fM'fldof The raflge of raovonnnt ar.d fr gure 2-1., v.-^ i-ju.a'v. *i;,;, ,b- pr«s«ntnd of -i : Fiiiinri- H-l. nir,r.k.'l', pjoTomeji in «nic!<iar'.scd a6i.) In all asco. In Table RRiDTREMENTS ^'OR THE mrE^™Y flODT >.OVmE?iTo IfiTRAVERICUIjlK AW) £.XTRA\ vfllCULAR VDH. AT 3,7 PSIQ A« NSIK M0311.TTY Flex-:on 'forward-! ackwsrd ) ' <^0 Flexlca (loft-r.Vgh-) ^ Rotation (AbdU'-tion) B, SHOHLDER 1KBT1.TTT Adduntlen ^3 Adbuctlon 225 Lateral - Medial jjO FlpjdorEKlencion Dcwn-up lateral Rotation 55 Medial Ro'-ation C, 1 ELBOW KC«rLTTT Fjexion - Ettenoion D. J55 FOREARM K0BTLTT7 Supination (pairs up) 150 Prooation (pains down) E. 75 WRIST KOBILiry Flexion (Adduction) Sxtoaaion Flexion (Ai)d'ict:ion) (Barkward) Extenoio.n (Forward) 55 • . 35 50 (x>1 �scvf mohilit: OF J50VEMEHTS ( fN Dro«EES) HOV&iEJ'TrS 'J?RUKK •• TORSO KOSfiLTTV Trunk Torso Torso Torso a» Rota^'Jon CAdbuci: lon^Ad^luction ' Flexion (Ini-.oral " Modlai) Flexion (For^'iard'^ Flexion (Bs'^kward) HIP MCETITTY Adbuftlon ;leg s^' cai.^l) Addnction (knea beat) AbducMon (knos beat) Rotation ^SitUjig) lateral Rotation (Sitting) Hadial F.loxioti Extonoion H, 'O 30 35 30 30 V3 35 KHEE kOBTLITY Flexion (striadlng) Rotov/'on (oedial) Ro^,?.-..lra (lateral) Flexion (kneeling) J. . 70 50 80 25 120 55 35 160 AFKL'-; riOSTLTTY Etctenelon F'jexioD Abduction Adduction kO 50 y) �• SPACE SUIT ASSEMBLY MOBJUTV PRESSUSlzeO. TO , ^ FOlO ' �Any f.rca rrjqulrius any iBinlrul.-.ttion ?rd/or r<>adou^. of an InatruTcnt by a crew racbor vrl l.,i bo provided with poi«l' vrt n-aos of crew restraint that will cctirol both trojie-(atlonal nnd r;>ratl9nal Biovrmenrla^o2.2 R* t,rr :tr.in<^ Drvji-oo Rt.r.tminloj; devleeo will be provided at 2WA work areao aod Jn Qro.vo ro.-juJring -.-row troasDntioBal no/enwii. Acceptab\ dcvie cf 1nr bide• "" developed EVCT haoclholdbe added).. (Ujegraa to b. Velcro Pads - Conditions to be oidcd. c« P/indHolda •• Gritert i to be added. d. P;l.j,3n " Pr<»l 1 CI 1 naiy ••?artin data indl-rato that rigid ral)T ut.lH;'.»d for longitudinal tracslatlooal should have .i re^rtaiigulvr crossosection 7/8" wide X l-l/'J * deep and be olovated 3" above tao .•Jd^accut yvrfare. e. Tc-'hors •• Conditioa.i to be added. S 1«4«3 AeseroibiV ty fi-ncl Openings - (P-reU'iinary Ke.r'.in Data) Ihe else of any op'jnlPg reiuli-lng the mut'»d sntronaut to rrnoh in wi.th oo^ bnnd ipint be nt le-^rt >>'/-•' «; v<t>' ivi handa« at Iflinl BY/^ high x 25" v>Mo, art! if visual viewing is neces isry, t'li opooing w.sv b t 8" wide x 11" big' for one am and 23" wldo x tl" high for -mo atns. SJoce the suited aoti-onsut h.-s li ;;le feel rapsbil'.ty, vis»iBl capobll.ti;, will gansraHy be required at any accoGO panel- All edgoa f h projoctlona near the op-riing must be rc-'-ided eo ao not to puncture the ^a'te cuit l.-4»3»2 Typo of Dcorn or Ponela A door OP ]«asel optnirg outwnrd should hive a a. ilhcd for 8eeur.ing ir the open po'iltlon. Lnvmrd opecing coors oust not trap the 3m 03 sfvii ....ocft during rr-at-ival.. Freo v.ypo panels rauet be provided rfith a positive 'Jraao of s^-owase adjacent to the area and located so ec not to intefere wlVii srboequent work activity. lclf.3,3 E/A Pntch Sizes (To be added)* �Is'j.-'to1 G .•';•• t", 1 1 w linttc which nun! hf tfio% «t1 rJjcll he 'rrovlded wUh lift poAnxe In T.ine v/itli thf crntci of rarr,, Tiie wricht of the ujj.lt " chslL be ffarkfd on the •'Jiit and tho ccntor of nana shall tr Ador,;.-;fied if it it. noi coinddent uith tho goffietrlcel cpn-T. lioto ,-ba7.l bf hnajoned to poinit Ttr,joval and r-- • ri:->i; wi'lh one hoi''d ur-df i- .TJmJ.tod vl;jibiUty coodiUons. i aboli aJJdo into pooifci C'U and be concfcrwotod no that nliyr. • mem is icpoasib le, Ur ;to chall slide ovt of position to • • Um tc and rhall be ret rved froffl til'.* sujijoriiafj panel or b.y .1 ranof- in tho dirt ftioa of reanval at the ritop. Dnl. fhil., be prca'ided vdth ritanda or rR.-.ls J'or moc »/hrai out opond or aclc. The uui i will have no piojoctioBOc coble/; r other tr.onrfcprap-ces whj th Ts--3\ b© v.'afivcd whl.l& the unit x-j. belli Thr. syeten "ufil; Tot present j:!jorp <«!ss.o or protrud.? boyord lh<? surface of t ho panel or rack whoa tho unit is ro'. in xhe operating positi c r . l.kA^2 U n i f G<iyv>r6 ly •?"""*?" "• «> 'owe ':hcy «. b, or r^oveo Kithout iootrurUon or tool.-, out oSall be p-ovlded With a method of Btor&yt . C f'iont! f 'rrj*ipt> To p-evont confkcten, f c-nponenta to be removed rhould be rd.or rcdod or othrruder oLiirly IdatiHfied d.tff>reatly f en the c«!|icnent:? usee as repliice;.:cnft".. Sau pmpnt S:-ae /-nd W e ' y h t Hsximum s.\se for novoable cqu'i'saent is »fci.! t--.jr.i Bf.sjn O r b i t a l TVA Oibiiral EVA Lutar TVA I?jnar SVA Voif^ht (TO BE ADDS3) Fasteners Grnc--ai Mount .ing faateTfTft ahal ? rrquirr r.o too)o and shall be op^^n-V tb either batid. When a fastener io net see^ircd, th-io Bacu.l.d be obviars on JrspcTEion^ Fasteners to be latchcJ •ualatobod ditrior S!k sb<'.fld not require an opcn.-i.ooo rpac-- v xorcce De/fl ^yr.cv faolv ccs art uufatiefar.rory siace ihey cquirc rluward and rotaiJcnol Tir®'S/-TTtj srrh'''oh cioo'; b<> r^nct,.? i ccthcrao ' O l-^o5®2 Fr.e-c.nor Pfrriorj T- 1 �O 1-5 TI.U'filtlATTO'.The estcnwl r-blonr Ught co^di. Ic-ns f >r the AAP ttlaaicA «vll vorr frota apnroxi«atoly rcro ro 12.2^0 foot t.vndi ,5, Secauao of the colllmted'notrrof thd Tishtv excfine contxa^n between Urec.f.ty ngl-.tort -traae end iboea 1ciLauov 07<]Rt be exfjcotcdo 1.5 =1 - Cn^lndlns aroaa .jc^aaslble oy EfA la u> whuh data recovery. «qulp,w;H c'lmgea, adjiiccrawCc, etc.. are com cnplatod) a. AabionJ lllumtna>.ion 'ox-els .i al.l arsao requlrins ary visual re.oronce by the aatronaut sHtll be adjucmb?./! wlthta the ran:r< of 25 to 50 focn -.tQad Leo, b. '.•.'here cabin windous are prov ..ted the jnrontRl bt-ightaess ratio eball be nontrollnble to ra* vos ?paB than lOrl. c. Light sources shall be of a 'li.ffuso type. d. All inrifcotora and panel are,..e ehnll have nn form nmbieat 1j gbt coveragu. ©.. L'ghc Gonrces ehaU bs e^ran,;-.d so thoc che vieidjig acglo of the vicaial worlc ar^ja is n-.t equal to the onglo of indidence f.roa the oouroft» C la5"2 <j) •> Work StcT-lcn tHuaufTvitlon Tho general requirements for the mumlnation of wrk stations ai-e; a. ' le5»3 (j) O No light aoureoB visible to 'he operator ( i v noraal worlting pooltioas)o b. Anti.-gl^re coatod iae'^nnjent <-over8.. c. Bulb rcplacoiBoni. froo the fr-jit of diisp1.!iy ptjielf no apocJai tools r.5quired» dn Sharply defined irmatllnolD :ed narkings ret'U-ible vhen vlevcd at any angle up to 60^? froo noraal of the display panel, Brirhtncse L9re.ls ard Ad1 <str!enf.<i Bo For map and obnrt reading: n diffuse scitrce. oontinnouoly adjustable to produce a hrig'-.tness level of 15 to 50 foot latrborlSo bo For inetrunent. jiantls; foofc'-levber^.B, whether Co Controls: allowance of nd.Ji>*_-;-caat "for saparene ponel light eoM.T-a to achieve apparent squa.i b.r-.ghtnesc. do £VA work areas: brig . .peso level adji-jtable froi*. 0 to 200 .J.rated from external or iotcmal oo?irce/: (To bo added) 7^ �!• I'lk'h(r.ep» ?.ii vcH f frrr tc< within: a., 5sl b/'lVA.'n ti,- h. 7^1 belwcf" the '• ' • >«< ,n.'« r, io» Jhould h, control j ;..ri3o«lat(^ :r..r>-»vr,.-;^hss. .i/id i - jfliti'sr ini-tr-Jiiola.. c. 20;1 befw?ei5 Ihe '.it-jk jrct stj.. reraotei our:';jceit, do '»0:1 befwseu a o-ui-® .i, :! the oui'Viife adjaceat "io Ifc. �c 1-.6 (J) C07.0R CODTKCJ '• .-houlj bo c.oiiip{it5*>;i.c ^llh U^/AdoIIo The appUcuble Tablon i-l acd 2-2 docuj.iin:-.ed in LlN " 5'iO-OOU of Z/WA, .»s changed c.t 6/3/64. are ohown in the foUowing tables: Ml..cd/,rds. COLOR CODCNO (C0> PONIJWl'S) Ttf|TC Tau 30227 Internal Kovoblo Stnicturr (balch.s, access panela) Ito Brown 5o:-.'to Brown 20099 •live Gray 35189 31'Je Gray 351S9 Gray 35189 Restraint Straps Restraint Structure Kcstraint Upholstry PLSS (Pa^lqvock) Harness Straps PLSS o Fed. Std Wal3a. Coiling^ Internal Stnict'ire Floor. Steps, Wori S'^rlac* c Color «bi te 37875 *bi te 37875 Cabling, Dixts, Internal oajse as Background Controlss Emergency OpEi!g*~yellov» <• Black Striped 25553 27058 Docking Ring I^nnel naite 27673 Glare Shield 'J iack 37058 Hand Grips Tellow 25793 Hand end Foot LoTcrs, Knobs» Control H-^jidlea- Son Illiua. Push But fcono Lt- Gray Handles* Assist latch Jatin Chrome HCPR Hardware* Instrunent Penel -ray 36a31 Inotru'ioct, Indicator Hezole Old Casct; Gray 56231 Instrument and Indicator Faces btitft or Black 37375-57058 �1.-6 "c-'Jrri.'irED Color Panola y^l- S?d, 50^ 'J .-ay ^231 tottering; Wsite 37375 Sw.-.tch, Icvera, Toggle Hatln Chroao Koae TeloB'opc and IMU It-- Grcea Z'iklO COLOS COHiXSNlIfTS (SYSTE3I?) xtrm Color Crow PJCTleions -t,.. Bll'rt Fed- Sl.d, CosiRu n ir a t i ona 1J;«. Gray 26132 EPS (Elocti*lcnl Pousr Syaton) Orange ZZZk6 N & 0 (Navigation 8t Guldarce) Lc„ Gracn Operat to.'ial TflGtniiDontatio'i iJlne Green 25195 S & C (£ ch?.lization & Control) 'ellow 23793 Ecpert::c".t Hardware -?<' �CptiBua panel ev.rfaco srenn r.houid be unj displays., ur.-H\ for prloiity 3vbtj*s!.ea contrelj With that enctpt^on, roD-.-N)lR ehculd bo 1) £aoo of Operation 2) Gequenee of Opera'ior. 3) Fr'rqueacy of Operntion k) CoatroVOlsplay Rclatirn^'jin.-^ 3) Minimal Hnnd/lJiro Excuri'io-: AecaLed for: Autonotie flyatoms with functlooa critical to crev safety shall have audibl and vicaal warning sigcals ajid n-mwil o 'lrridea.. Controls shall bo decigued to prevent; 1) Ircdverfcont Opera'-lon 2) CrewTnaa Tojuz^ 3) Dofrage to Syaieci All controls other than r.u..nd<rd Apollo tcu.ipmen« strata freedom from control --eve-ssl er<-sre and nl'all be tested to d&TO alia I t neot the system precisioa requlr.-mer.ts with no more tha i one overahcot error and rwo unde^ shoot errorsg l'7-l Gor'-rnl IbOcr. "or Controls (k) The direciio" of norextat of the -control will ho corsJstert with tb aovemcnt of rho conirjlied objec: or moving rortion of di^play^ Controls Bust be easily idc-ntifi.Viie by both^visinl scC 'actile ten Because vleual cues are pr^inary^ iowovort the control arr.rklngc are* ni?ot important coding method for ooaf:;^ol id^rtifioahioa.. % All eoDi.rGi.s will iiave two types of Inforoation Xaeatod px-oxinate r the control —• idsntiflcaf-loa of the control funrl ion and raethod control operat'on, vh-re r-«quirpl> Crebioed hmd two controls on concentric shaft i for g'-ocs >.nd flco 'nlj'.i be naod only when cjiace limMati )>s prohibit controls and accidental oovcmant hazardous cor/i.iUon. of coTf-^iV, s'^ the use of ludlvidoal >r the controls will xot create a When manual ixrfoxmanco rcqalrem:3ts are ouch t'm.t the rcni!;rollod object can be adjusted in a lioi ted number of dis-rrete stops, dncea controls will be uood.. When hlg'i-precirjlon iikTiu'pl ectflngc arc- rc quired over a wide 'range, assitirc-tationel cor.fc'-ols should he ueade All controls will be distributed so that no ^n© burdened. ll»Bb will be over All controls will be ieBigned, ori.cntcd. and located so that they ore in acoottlsE:? .-iti. lonrol vrork habit patLoruo, cusiomaiy reactions and hvnuo reflexes. It is des-.rable to recog nise the goneralised oovrcss of human error in t-he orer-vtioo of controls in order thi rh* .-say prKciurlo then.. for human error exlats in the foJ.lowiag ercamplrs: The potential �a Sim.l larity of control csvlcfiii, cauclng tl.R wi^ong coatrol to bt octiintrd borauflf. of ro\ftiMiijj; Lt vritli oi>t,}.hor, b. locatio*^ of controls t„o eaoc.ly rojsthcr 'r.nsln? ».nad»arteat operation of adjno^ot '-ontro:.. and iatoxf'x'ii.p; with eaco of . operation^ c. Improper aequonrj.i.ij, :n«o ofj.Jiatment, one orerly complicated adjuatmenta mutiny a',oUtkes .a coatro.1 cperotlon- d. l«ng oBd involved prorodupes dlffieuit tc oomnit ko oonoiy, Xa7t2 o. Operation of cont^^3la in a d;v'cctlon conlp.ix^ to normal novcme of the operator (}wrt.\cu\apl> tnibject to human error during tJof otresR or enerr;.3icy), f. location of coatrolfl .u mich positions that t]ie oporator can bruch or kcock againol theu, i;au3ing inrirJvcrleat opemtionp g« Arrangf r.ient of I ho ln:;t >'ii'3oa* panel 1n is'ch s. v/ay that It is .Impoosible or very dirficult c reach for one control vihilo operating another^ Gcnc'a'l S-sfsini.';!'^ rri- .»p^r» <k) Bcoanoo of the confjnc^l q- n.-^ ern .tad tho djf Crl v.-l, v of controlled Bovcmenr by the astronauts, in 2eix> g>'aviJ;y -•a-.'lrcjw»ni., safeguards iTiot be adhered to in tho d^nign -tf control? ixnd In/out of tho console bo prc-lude toadvcr net. (..ctuaiion .of coniroiso Recooaee Will be used for toggle ewitchos ^f it aprraro thau the rontrol olght bo acTn^aiod ir-advertcntly, Guarde-l'p«oljhnt';oas. toggle ewitrh ... ^or levcT-lock-t.ypa tv,Uoh.-3 are •.•.^:^ulred for'iVncticns that are ^irreversible.. They wl 11 nnv.; re' ->n3 installation depending the po tion, or> tho .main disp^uiy coraoXe ,)rovlously etlpulakedl,..7-3 (k) Toggle r.s-Jtr.hf^a Toggle or lever^typr j.-it hc.u ma.- be two^ or «-hr{-«-peollicn, tab handle,, or lei[er-lork "-.anile an 1 isotrentary cr Da;.rt3inirg in thai, switching action- Total ..hrow d .itaneoc of iogglo .aad J.;ve--lo'ri£ switchc.9 should be f 8 dcgree.'i. The force r.'cit'red to change poGitien should be ^jO-IOO ouiiccg Ad axial pill of 'fO • 30 oJUJces is rccoamended to release the lev.jr-lork switch f.-om a iorked pos-ltior:. Tho m.iaicaiin allov/eb.le spscing be^'^een log'jle switches grouped in hori.noDtai rows sliouid be oc« in i on centers- Vlien xi.vtd in locaticaa whore the baodle could po-'e n -ta /icd to «:r«v r'crb ^rs or be subje-icfd to inadvertent actuavicn, tho sw..t;ch should be sc-aireccssod and pro vided i.lth barrier guacdl -u rbo 'i in Figur? l-J.. distanctbocyocn barrier guards .?h-'uid ro- be Rorc than or,.. Jjvch. t>ierg:-a:-y s'/itchea or switches whose iiuidv<srteDt actuation would create a hazardoua condition rn.ist iiave a '.evor-lcrk handle or be pro»;ectcd by a guardc nl �RECESSED liVERLOCK TOGGLE Figure 1-5 Toggle SwitchcB - 112 STD 65-1534-2 �-ogg-/^-sw.Mch 0]ie.-atioii is varS-icol iv foBltloa jalrB sS=oa<i b. ,„ ac=< 7^ * -DOrfh _ . rgi»ARY BACKUP gj, Oif eit?':. Ctoi;; tl.b xc L'bv,ins brtbari , TMOK'•A^^s DJSAcm'm _ D.-.i'ipy dwoi.auinr Brc£s;»3B /ijjo JiT'LvrC Where a thlni position Jr added for OPi;, v;-e-oiild h« in «•»,« center position orrept. .tore thjr «ouW perforonnco.. In „h:r,. mrr OFF .tonM be In the litSr!'^Sunn. l.-7oA (k) Rotary Switrhc/ notary swi^ohoe (with not oore \hon - 12 floior-rohi. ^ * •. • \ ^oJeM'" ''"If "• "«»« l-*~ *li roia^^LThen I - ..ctpblc pocLtlonc Pbou.Xd be detnited. Eioh swJ tch ohould oy a detent cao, to hc»d the .rliva.ins nhaft ia ZToAZ nd.vldual ^Jtch positicne., A itop will be i>rovXC.TTl "he ^cnee of the actuatir,5 rkaft's cotation exooot. in oases reouirinr Joa-degree rotation, , . -""juA-riniT . ^csTj switch throw distc-ir.:a bttwaca poait.loaR chould be 30 dee'with a torquo required to change positions of .12 - 100 inch-ouacee of ^sitiona will be sjch that rleclcwJao ooveoent ie on , ascecdijig order", "incroaasd perforuiance", etc. I«7n5 (k) Rheostots l^ea the th^gtat 3.^ ncw.d rro^r. U« knob side, the maxi'M resir;. tnnce should be in the OFP diroc Uoo ^c^t-h d4--r<-a«Jr,. jvr.tw.n-- ™ dire.-t!.oa„ The ront-ol should .royatr, throui:a so a:^„. of 300 oegrers plus or mj.nun 5 d j^raes, A B:«p..n-}tion OFF positio . .B recommended to opaf the rhoos:ar. rircuit and should occur j stas the contact passes beyond the i<a5;in!nm ropj.Btanse polntb Depending on the ^st;allation rejuired. al;. -heoststa should to the rotary Knob nesign as shc#o in Fxgure V4. 1j7o6 ^nmhwheels .• PotentioKaterH (k.) contact nm should rotate throy.-h an arof 300 degrees plus or ai.-us ID degro^rs. Tf the poteatiora^ter is to be mo-Mtsd riush on th-s control ranel bf the tl„,nb»bb,l bh,uld �RANGSS A 8 C 0 E F G H MINIMUM -MAXIMUM 2. i2r. I.W a687 - a 812 asoo -0.678 0.31? - a 437 a 43? - 0.56? ao»3 - a 156 a093 - a 156 1.08 - 1.20 ROTARY KNOBS AND RHEOSTATS ri^ur-i 1-5 Thumbwheel and Rotar/-Knob Switches - 113 Sir �c Tho r'.arTclfjrd r trhb" ..i-:n 0. '/;0 jrch-?« nad •'onill iijiiaatud, < •'; J>r i 75 owucfte thnsusToul tl.? dw>r«sejoi5 v-n-.^pf. i'AS/iMv. toTi Si'-u-hry Sjy hM (i(.-jr:Kji rti or iiorl/.onhelly oa ons-inc'j ccr,tcT.-„ ^^c.-js i>-e to bs n'ourvcd fJus^h wj in the r^-Dcl nnd bavr- a mljtlr-in sf C, 125 '"nrh. S-;•^-~lte(l p»sh. b'iilontt Rhould iooorpcrotrr gvard » (P'y.fa j :.o p-.n-^nt Inadvart' ijctuatson . h o rolor of tho ilJuTin-i «cJ pufiiiattro sirf^cc. I'-pc^v.^of; on opplieatlon. wJLbo ^viaw .a yolLow. ni, or jn nccordar.cs wlh eho-11 ;v on H::.C-2505A. Vhen sot OluMira^^ed, ».he 'on facti or ca.-> ::ovf!T bA o ilcrcp^ruUr white with n 1:7 r-r gr^a^ ar '-an'-fasl r.nf jo !face to i««gcnd> and ir^e of tint, '.pon viaua-L 3r3pectloOB C 1,7.8 (k) ^i';y'jlt Breeker CJi'^uit breaker dori.gi should coifonn to dst.-.ilc of Fir;aro i~6. Circuit broekerH! gMieralJ;' iii-s o.f the pop-on: rolco.oa. puah-co^ rc5et-.type. Circuit V.ros ,r-n uiW be nordnf-nUns ho.-jilng thf? krob in the r -s«t jsoiiMon wjli rot oferi-tdt? (>.& r rcui ^-^brcak-tng fur-t ion . The -rri.ppod r.ooditioa of h- p'oi • .jer-t.yp- .--iicu-.? breaker la i.r.d.vc3''•d. by a white bcrJ whicr. is . nltiLina of f, ••.5/-..inc:h w.'de. The b.renk'jr body aid head vili b*' h? -Ir, r',-t.d«r.- |r ,^...,,.,-,.1 .,i,r.v *• Ii.T.itod to tbf to? .-vJcfaca of »;/ • virru'^t e-- ake,^ s roqn'r«d to re?i?1 a ph'vg.T- t.Tpe Aircjit bre..ker •rill i«>t exceed '2 pounds, and the forc-e rcqj-.rr» ic '-rip a c i nniLt brenker Battiei i u'ii.1 tiofc excefl 3 p->'.;cdBThe mioiaoiB a7.i'-vatle spare between rirrujt. trealjers g"cjuped tc. horizontal rows wl.li. bo 0- 8 ?.B!}x on center s.nd hhe dio*'oj>f-p.a bo'wfon rows a miri-j.; of o;:p o 31 �o rr* ;a ^•nG» < A XLUV. O'-v 'j:iO UG/ii : • 9.tir, P ttov • • • -A. 875 r.Oi; •K •*A<T'- . -KANOr. Ml>l A 0 " ON'.'*' A - i'<..\.'iv., .'J'0.«7 • 17$ - 0.8A3 r». •• - 0.156 c 0 E PUS E'JTTON SWITCH G RANOCS A B c 0 MINIMUM • M/ 0.W - 1.967 1.975 - 1. OCO 0.943 • 0.4t« 0.3IB - a 711 va•. - >-v. O' 3 ISHBUTTON :OVE! GUARD (TY»:C4 FigjUrs 1-5 1." • - /-?>>•*•» '• Pu^button Sv'itches �KANGCS MINIMUM-MAXIMUM A t a37S 0.«J7 a093 0. 156 0.167 0.250 0.37S a AS? a 281. asAS a 375 u. ISA lo® — a J/3 a «s »i - a 0 . 5593 93 « ».A I «t a 730 _ I.OOt c 0 t ff O o H o — — RESn CONDITION -> — — fJ Nw* — TRIPPED CONDITION r Figure 1-6 Circuit Breaker - 116 - SIC �In tt? dosign of a n y Uco thr.i ,!..-olv=£ op^mvor.-^ o- K,r ccn3-6' y r ^ i i o a t i i s th^r a ^ t h c d b y i-H.vch . t - r M n e n i \ u r r > " ^ 5 v i o n w i l l а. Display irfomif:i,.a wiU be limited to the desree of accuracy actoall^ -dovstandablo. Identified eo aa U, ot.-/i«te undue 5 •"• E.-=.p=d.»,, to . б. lDfomat...on will be prceenttcd in ouih a manner tbot any frilnre or apparent 7- All displays will be prorerly illuair^tel-• c-'V- --•> fureti-^r.. "' .. . •• lobol ^Keters <k) Tho opooir.tc,viion of aet.ro, InolodJog polutor loMtlon. oovomoot display scale,, and penersl frrm factor character-,ties, v-iii nrn^-. to tse fcl.is-/ir.2 'y.-*23 (r-^-rec '.•? a-;! !•£)• " ' 1 8-2 (k) O lo Single boriaontal moytng pol;ttar displayed 2o Single vertical moving iKJint.jx- displays. 3e Dual vertical ffioviag *»« Fc-u* vertical ajoving pointer diepiays. 5® Single circular diGplays. 6« Dual circular dleplayT- pointer displays. Meter Scale. linear ocaTes ara gene.rally prei-r^d., Idien accuracy r^-ouiranentn exceed there that can be at^alnM usi^tg a Uncnr .cSc SSS! "f e-pa=clcd to acquire the -Drdcd accuracv, rc;pi;'rc(', to b? f>r.'-ri;v,7,j trc.'i -i .-.(ij-j . -^ , --• �i. EL. n JL DUAL VERTICAL MOVING POINTERS SINGLE VERTICAL MOVING POINTER FOUR VERTICAL MOVING POINTERS Figure 1-7 Vertical Meters - I2r. - sr: �% DUAL CIRCULAR MOVING POINTER i figure 1-8 Circular Meters - 12" - € ( • '••o �rRANOrS MINIMUM - MAXIMUM .300 . .500 .187 .391 .093 A » c 0 ..362 .562 .250 .343 .156 - :C7 DRUM INDICATORS RANOCS A t C MINIMUM - MAXIMUM .718 .425 .093 . - .?«' .856 .156 DISC INDICATOR Figure Electromechanical Event Indicators 'O- 1?.7 SID A'>-lS34-2 �1>8 3 (k) D'np'i/'-- rcrr' 1 J A.Tnf>j?frt.'!n ' — >.ncr'.c <.t:aM.3 y rv»sdwto. d.gi'j l or Oa.nlos. nhonlC b« Doni^Uy-ea to read i n vr of »a* Mi-a !t«ihlo f.Uild t, 'olupw or walgh): as rer>prJ. V'r.;?'-Q.l eoalc indlcnt.or (Tiaup" for r-'bsyatea condltiou raeti.l toring ::ho. *<1 bw orrorged by aycteni fyj Jtloii ihon by displ-'jyod iv-.rn'i-jterv Chen by alpl.iibftt.Vc or Dusiftflc scc^itisnces 5c deoccaJJng o-dftr of fT>bgro«i.M. i'.n- typlr-oi ri„td syctctns, chc profcrrccl ord.-^r of dtspl/iy sf rongoutjitf rtadicg froci left to right O'r ffoo top to boiioo la pi.lol. Hxes Is cs follnvcJ In Gyafon fua- lion: Preo.Ttr 1 fOel., oxjilizor "a 2a ^ D.6p,.ay;d r^rAmetors: Plov., toiip'ratovo# prresnre, >ii.'antlty» TQlcot aaperes# 3® Alphabetic or ounoric rfquenco; S.Tst.e-3 A • Syvjten B or TcnU 1. 1<>8.4 (k) T&jik 2 DJcpVv pointsr Location nod NoT/nrnt Jbo pnlJitcr In vertica I single-'p< tnter diepL-iye fclll bo located to the right of t.he scale. Jointer 'loveinent- io na up direction indicaVea inrreasfch values® Tho pointer i a horizontal oinglc- oipter dl.nl'iyf c- <; ?. I above the ijcale (there isay be .lo/:U.taate exccptloJisJa f^'inter neve went to the right indl'-at?y itirri't.eed valueu.. lbs {rd..lvidvial peictcre on dunl-pclater •.ndl'-etors .'ihonld he lor.ifed oi'thoard of thalr rosp^•cttve scales (Ue., b--:el, po.'nler 1; icftle J., scale 2, pointer 2, berol). Pointer (aover-ient upward Indicates Iniroased values.. The individual pointers on four»i)ointer lndicctor.3 will be ao ohow'^ in Flg'jrc 1-7 flrC,, bezel- poin^^er 1, scale I, piintor 2, pointer _• pointer k, bezel)® The pointers In dual elrc-jlar io' lcetors shovild pVvot about the extrsaiitics of the horizoat?. I ex s- The lef- cfvxle cocuicrcea at nl.i i33=degr«''c point from the -.op cc-n er point end oonclMdee countercloclcvise o t t h e ^5* degree p»iiit The right scale co-itrcncea a t the 225''dGgroo poln' froa the top cc:\i.ftr point aad ronclude? clockwln at the 315'dflgree point.. Pointers for both circular arc vori'lcei dial fares should be close to the dial fr.ue and c^ale to reduce �parai-Vix to a o»Piou4. for c.cpro7«d tieisee, tha pointer h^^ad wi.ll be triar.|i«Ur m d the a i d s t of the pointer shaft, where required, vdU ha parallel (n.g'.reo 1-7 actl 1-8), 1.8-.5 (k) DlnclS"? Mni-kinera . , When oporationnlly useful., eolorel renije tear!' in.'is wet be used on vortical, borlaontal, and circular diopla:,-3 to Indieat.o operating ranges, "Kiree oporatiog rooge marl-rtngo arc recommendod to indicate the following oouditionsj 1, Nora.al 2, Marginal 1 Prohibited or limit mark 3- "" I Rargo Pirkireo ehould be 0. 05-loch mde and extend to the Umite of tlK; uiuile factor reprcscrted, Range mrkings vail bo imposed over Lbe scale index tnirklnga to enhance reRdnbllity and visual cue rcGTion.ce, Idmit ra-ixkaar: should be 0, 07'ln«ii wide end equal la Icngih to the loag graduation of the scale in qvestioa, Diraplaj* cover face© will ba coated wj.th an artiroflectlvs trans parent materials l.-8a6 (k) Alpiinr.'-V'erlc Roadouls " A.lphanuncric readouts should be ocmposod of dcctroluMaescent eoven-line characters that have :>ie following deaign details: Slant- - 14-2/2 degrees + 1/2 degree tc the right frw» the vcr. Height - 0. 500 Jnoh + 0, t>05 inch Width • - 0. 375 Inch i; 0, <>>5 inch Stroke Width - 0, 625 inch • 0, «>15 inch Spacing boiwecn nxwEorala - 0, IXy) inch ^ 0, C05 Inch DimlBsuiB Iraeasyrcd at the bace of the num-jml 1.8.7 (k) Elc t'-oirechanical Eo-eat. Trdlcaioca Blectronschanlcal event indicators are rocomtiandod for use when highly reliable go^no-go '!or two•oogition) iiTdicaoion^ o.r® r e q u i r e d a n d when e l e c t r i c a l p o w e r n v a l l j i b i l i t y i s o e v c r l y v e strtcted. These Indicators are recommended for use as go-no-go (opcrational/nonoperatloa.il! s{e .2s iad:'cator6 oni for vwo-positio'* positioning Indlcatorn, e.g. , no'^'mal-naxia-.ia and norrr.al-rtfiii.lawa poGitious, 1.8.8 (k) Two-Pos'ltion Dmia Xrd.lcators " ™ "• Two-position, electroncchanlcal dnia indicators will be need for status "indicators 1-8), The Mark (gray) poaitien of th? �drtia vrtll i-jTor tr« ^•^ane^^Te-J l e in or oi>Rrt«tJo'ial node or o r o t inhibited i i o n oneratic*?. rho baohcr poiw (n'U rmnie b 1 : . . / . n i v.1alr) position o," tio rirvrii iadlcntocs Kill Infer tint .!;c 'r.. •no-led pyatesc «>aiint lo i.ihibilsdl frto operation or 'in l:olflrnc05 -03<iLtirr., • A pair of »•:. ^etr^e-hvclcci.l dru.t iai'.cators t.'ill be uoed ao por.i >. . •>> i- icdieatore for eomo jsycteit <iericea« Ono will Indicate th .if:; ir.d c-3;d.itur. yt-sitjonB of the dt9vlce. second will i i i -ifi: : he r.omal std eiimtmiBi vasitlon of the dcvicoTbo pair of dr n ii.d -cotorB will t e referenced to a switoh pooitiori The dleplay face of th.* two-poottlon event Inilcoloro ohould ba Pcrtongular vi.-h a dleplay sine 3o Joss-?han D, 187 by Go 2Cl Inob ard iho lon^ nxla nourted horlzot1,nll,y„ Z'i<-< I-c^icch-nioal f:fatiJo t-d^cntorc tj/rinlly t i l l be localod above the nfjnooiatcd r o r t r o l cwAtohoa^ Rleetrooechsnlcal position in.'l.;eatr.rn vfii: be located with r.-'ference to aw.tcb positions1<&«9 (k) D.-f.r Irvl.''".TO"*. Eiectrononhana'al dJaf event i a d l ' a t o r s eay be uoed t o diaply cbacges onalofrora to a speceiu device poni^on, "nieec indicators are used In ttucoaatic syct/ns and.are rot dii'ic-tly asaociated vdth a ev;xt.oh opcrationa Th'y iT'xy t o Ufied for riystcm devlrr operational position BxatU3'. ir-d'. ;otor will tlispljiy the poaJ' J a of the i^sterj devic.from ore exlrc-iTie la the other wains a rotatablo biack pointer. Thorc should be two black indices on a white baclfgrovnd to indicate the extreraecs (?'ig-jre .1-8)'The display face of the electronfohanlcal di'.c e»cat ir.dl-:afcoro val be c.lrcular bavin,;.- a dtsp'sy dioircter no lees than O. 625 Inches. Tha Indices ffiy-ct be f j ted lisving a leegth of 0.. CIO and wldrh of O- 093 inches. Tho winter Aengvh ahould be 0- M ',m ':,c 0 . 093 inch. 'Tlie pointer opncinc from an index uhould be no sreatf than 0 . 016 inch 'Fisiire .1—S)» 1-8.10 Alarn S y s t n Any e>:porJ.rcent that has any oper.-jr.ins characteristic which can pro duce a ti'se-critical liasardous c<«iditioa requirin.g laasdiate corrective action will ba desagned with an i.ntcrfaoe Ine-trunantataor output ccapatible vd-th the CH Master Aiazwi Systca. (Additional crlteriii to be addnd) 1,8.11 VaJldation Tas^irq Kooslandard or intoerated displays which coobine related Inforaatlcn in a single display uni t , s h a l l be subjected t o huiraQ cngiv.eezliig t e s t s to dcterraine the effect of the lategrEcion on pyst era perfojTBaDce. Units which produce pcrfo:-nani'r equal to or batter thsn single purpose indicators are flccsptable. �_FHY.-JIOlonTCAl i T,T|i^mCW3 i-O'L Cr«>w Ont-Ta' Icn.-il ry.-:; . -.jij |,» Rygu^romcit./i (See Table i; (1) tor H.i'Vnrj) Food Pood quar.lity vill bp based <>a on Hndivjcual calorie intake of 3000K caloi -OB par tnon p«r d-if^ Cnc-ron dayo' food rrqoirca 179 cu. Irpbos nforcd volumo at 3.3 ponacs vfelslit. 2. (i> Wnter Water con)?-.itipc-or. .3 .10 folL-Jwai" 2,.6 ili-iiikf.Qjj aod food proparation 5.0 Ai/c:-.c dry,, ^aolcatioa and hygiene 3» ConotnTil" '-.'par C'ln^ente Each crew r.crbcr .-sr^ulrca a jjsw co-irtan'; i.ear garsent, (C^Q) r.'cry two dnyn., .Nuober of milte >-'iTU>r^d fnvr^cr of crow) X ' o | 2 ) where r -n m i z s t o n deration i n days. Wliare p. . 3 an odd nvcibp" 'ice the ne:ct afBal.ler p«»iri>er,^ •13 cu. ft- and pounda par auife, Stored volua® ie Pc^sopol HvffioPo (To be added) *5' EVA Opcrat-orval ror^nnptiofi a. (h) One PiSS UOH ar.-^dgo )»Qr wofgs; dlisena-lon * IV*, weight ^i->3 ^h}. Store 5 Lntera:illy, rf3.T,?»ii-r «.•- i« s t o r e d exte ?*nn l l y . b» (h) The PUiS lie: 3 'K rechnrgerililo battery that nrist be recbarccci for 10 hours per uaago. Allow '1 ysagen per battery- Dimcnrdon 3^* x VyA" x 6H", weight 3 ibs., store Jnternaliy, c. A full PISS oxygea c»iarge J.a pounds. tion Will average pounds per hour, Csyg-'O rtononpu- d. (1) During iWA the standby D'A acfronaut wil?. cperete frcw th-^ sMlt loop of the tCS, requiring operation of the suit loop fan at '52 watts ?ri* hoc • powar romrjoption! e. An additioDfll Constant Wnar Gament. (CV.^) iflll be included for each €re\-.3-n on ^iVA :»r EVA afsndby duty. (ThJa is in addition to the callout of pai^agraph 1-,2.5,1 (5^. �C?.Zv! OL'IvRATTON.H C0tvSiJM.*i3I.E Kf-vUIIiSHENTS Wir, C-^wi'ioclv f'j f 1 ECKMARi) V<» l'>mo Pcyer Ci'.. Xn. Watts . . . . Ar i I'er Msn Per Dcy Is Food 2a Water 3o Oaggen 2 Va CoQstanl' V/^ar Garrao,;iL ( 2-3 r.'9 7.6 2-a . \ 1 > (based on i ovoij? other day*) 4 (" ) Perooruel Iiyj^lene -• chowiji,3 5' gu.t tooth ijieanera M C - ) deodorant t OtCa 6~ < •^ Bo Per Kan Per IT/A • 1» PLSS LIOH cartridge 2a Battery a, after Uut ueage < - ) • ». 0 Constant Wear GnnaQnt Oxygen "'per hour) 5e fio Ecohargfl a.fter Jisaga bo fioplnce 3o * Coolicg Water 1.9"2 1J9 225 0..25 .1.83 Crnw Wor?fcc' Ppcf^nrnioB 1# i tJjitrented bloi.ogiral waatij eh.,11 not be allc-wed to bccoaa free residue in spnco. .J �2, (i) yao'c Vaslo Production Vol, .1, 3 Orino 3^2 Feces 0-3 Water Vnpo.r 5-3 Carbon Dioxide 2.3 There are additioDsl oinor-itcos of hyM-^a -.fci-.l;® that can be ignored frois a weight staadpoitit att total jn'odeetion for a i-isan crew for 30 doye is cbovt 1,25 pouod:?- Iheoe ilffluo i-ic.\ydo flavusr hairv naiJs,. n-j rrocrcani&'Jn, aliiia cells, a'"id mucins, 1,9-3 Radinti qp LIti;', rntlooo (To bo added) r": �FiTJiT or-:-:\'AT:rGi:AL 2.-01 Thopo requirerannwj cl«?faaa i-);o.';e «>ud oanotrBlats that •ffpcl the m ..ri.oic'i op'^ratloiia of A/a', 2«02 gnrpog-i T}ie priiicry r .vpoa" -f. i.o d. fice tlnr.^ rrqulr«:r>flata r-ncl rr\t-7rla 6.lth«»r pocuJp.-ii- to A/J" ->1' def?)icd by tho Anollo wlosion cor/ljuratlon tha.t five nc-'.-onary for nlaslon pli=,r.aiQg or l^ffect cquxpneat doaign, Tt 13 nn obrif.tivs to e>aint«:«ji the saria functioeai in-flighffilsalon p'-occiwresv t c-hnlquoa, and planning ti ar. oharactari ae the atacdsrd Apollo i-i}.6a5c:> �2 - 1 cr;^rf ArsiGT>7;:-:.vT.: •• nun stati<m>T7 j Crew Arr.'i. It ic findelpo^ .jQ that aXl <• ri^y wt-niboi-a \.lll recelvo a d'^grce of trA.';nlni; porro^ ts total later^hangcabi llty of crow dutJos on en oa<>r;tnry hcoiis, 'fhs onlsr of priori iy of crow ntiliaotiott in: a* ^kliatonarJCc of flight eafo^y h* Condvict of hasio c. Exploi-arion of natural phonoaeoa d« S;;hedulod pi?c:sureaents oBd eboervatioBe of natural pehnoneaa e. Repair. •^ali.braUoo and codifloation of olssJon-epcclflo cqu-lpcient.. oporations For the p-.r^cacn of rrov s'e.U^T. salei':tlou„ tvaicing plans, arid nora?al oloB*.en planning, the following ground rul9.-5 ehall apply: a» • "^c eoomnd asiron^ut viil nflrrFo'ti all major spacacraft taar.'iuvars froa the left haad poaiiloa of cither the CM or LS-lj He will also be the bacioip navigalor on the CM. responsible for Q}\ naYlgatler. a-^d cperailcTi of the CH Iccluding docking khea the XifJl io sinarated. E-n'recr -• Is pr5.raarily re.'iponslhl? for all experloent act-irltieo pins backnp operation and rarigatioa of the LEH, Aaoi (Tr"fnt l^'-iorlttes - The follo'dnc tab i o lioi B acslgnaeat priorities for the rorlo-.in crew meai'ei's. For purpoees of mission plaanlng no noroul oasLgacfflento will bo oatie where the crew n^tnher .Is listed as type 'in In t-hr va<" of CK 'v^,. ,»>;•» pcrlceni-s the ccr-snnder I3 lifted as bdh typo j5 and - *ypo > for repel (.••.!ve axpariB cnfcs or 'hoso otnou^ly requiring all or«u cecibsr.s such as most bio-oed» r.od type ^ for highly speoisl' typo of experluieata ewh as a 'clescciw prigrara, , Crrw Hersber CoaaiaTider lani-'ch 1 CM or OK Dochcd to VO'. or J iXri & I Experintn*- Carrier Operatioi'B J Orerniic^e Recovery i^larc 'ivers "^Javi'^Vica' h;^erire^t6»"^'.accu» erb liavT' t J i t 1 i 1 1 j 1 •i Navigator 2 1 2 1 2 Syecen Efegr. 3 1 ^ h 1 ' 2 c ' 1 2 Q - �priisc fi-r'.poti8; bJ li ty a-ileP i=>iU tmjjiina and capabiUty a- SocoQdery F.ecpoPclblll»-y - fjill tralulns 5> Operating CepaoiLlty -• S'jftl.c-venc. vr-aiuta^ to dfCQnabratf; capability o£ Bor.iial oporation Boorgency Capobil!.^ - Tj»do'2';riaQVioi> aad Xlaitcd praetice- Duty StnnlonB (To ba added) C « r-apabiUty �6, AL\ri>f zh bo*.' 'r between hVA'a fo;' <Tur-h crevmaii, 7« Maxur.,i!a hours c. o'Jtslds Hno for owo .^A operation Is thr^e 8-. Provlslosa w 31 be sisde to penult Ev'A d»4ring darkBeHa,, 2.2<.5 t»nd 'a'e^Con.ytrainfcs Jiard s'j-'.; 3!A oo ."urcr ourfe-ce vl H be 'Limltec to aix contlsuous hours per daj., (This reiju-.r-;r a .^'ISS char^ge) ;.:>r �n i l t h r ' f c .'ir-t r.-tri.;i ; • l i f y r.: An y'or • ; iVA ?'!- • i • r i v.->(111 j : j ; ;-r' v.-th ti* .i-f t h e atar'jb.^- ••• ';, kjjuo**" >N' cosimunitfatiena .».J .linllons of . r virau iticinr* j,"3ivT« rhe nur > f;ht L\A £.11 fliK?:*. ci« '-rev tjtlitl :5stl«:«3UL i y efaal". ..ivifr or « ' c h l c l i » . iOi bcv '-a •.in>l,o.or/ ;>• r ; . . e . - r , • ; ^' -ndby T/J: nnd rrv • • . . n - . - n v v o i , ' ? • t . . .i o r i fi'.u blinij epotp are the > " ii't be oroHab'' ^•inH .11' i - f l , , mo lo be'WttaR w1 'J. hnvs TnlroaanJ entetua vthiclea tvo-wey h-y v o i r e r o v e - - , •' '• .-rc-" ^j-atrcysnr' jon: '.n roqutrcd e c lollowst 3- AIJ C i f! b u r n ; ; bo Once p,>- oj'h'.' ni' v.,I lavr " ban .J-hou.v inioi ' a'l6> Deorblfc T/Mt voice, radar; i e required aa a* Xaoucii,. t>« Major Si'S burr^^ t o •iRci Cf Aoy cn : • • . .rin;j c - ' v a r - t j e f o l ':•••• i"oLT.ir»wi oijj3if:tri,nt n it-nft ctnl mJK ' atH'u'orial • cos.plf'tloit Jtars'j'jvor' i»airo two ;»f b j m (i5X«'ej;».if.a roOwOi:'- p r i o r Jg doorb?.t sijneitwc-r) �G:--'-: r-i. ON Er.'snr-jii' Ort:..ArMi<s } 1, llvtl-r.- 'n I.! j U.r.itlon of the cr<-"v lor n-dumjancy TPtiootcrlng tiod r?i.il»irp. stotJo coi-rro'.ion.T/otor-tiono ol «>;perJrt:a*«G viil tc sjp««d» ?. Gxpcrijn.^n'; (*atn oet-up, pr«- or i*03t«« nJjbrarion asi ooRratlon Mill bp 0'n-bo!*i\i rcjitrollcd sad will &ot roqu-xe ory groind upllnit euoporh sapabl\j. Ci-spo 3- Tao rcrrd , dunp or ."oGufi p reqii wiV. be h crsM roBponeibili'y aod will not requiro c.ny ground upliiJ: controls 4c It ie clsr lr-;blc not to hare "• PoUviiien oi'rtng major Jliglit ffipneu 'ero — iaunch- tra'isiLatinn and iloi , 'sa^oi* Sj^^S burns, deotbit, lun*r '-.adinij md aooenc^ .md rc--onti:' If roqu- rc.d., il will not. utili:;.' moro tlian or>e cx-nw m/t.bcr pef'ornliig Troi^i lis rtf^xhr duty otat jo.i. 5, Ibcpor-;:,! >;it .int.lri»lc8 xfil'. be co'rplo--i at Jr-ast togUt hours prior to dso.'bit ond ao notrd in a'jotion ?.. • �2,5 riTOfis T-T-'B T.if?2-,5-i Gefe'-al "»ro-;ad Puiilfrg Tho question of u prcpe.r worc/re^t dniy r y d e in b cpinloitat.rd variable., A fjj>aL ocovox- will not maalt x.\ a.L'. probablbty until after ccvaral .long period Arollo UlgSits have bees r.osipleUd. In th oioartlr.fi, a re.-jsonable rye l.e rrast be nelf.-ctad to p.^nnit inUi^ion analysis of celfvrtcd erperlR^nt granp.ngs- TIds ejr J.r will be used to anuljzo the bnslr arceptai'"! vt ty .of vrrious ex-jerimer.t groupings with tho ucderstijiidius tlmt whore i t beoocxja a .litn ! lug factor, a specif --r aoalysir. of altoraaSo GOlutlo«i3 will be madd- The cyclo eelected t based on the foilowing geDcral pre^'soss 4 1« One rreura.-iii -.iill always be awake rjid in rtiBrge of roiGoion lai:r/.;rity, i„e.M v.'stch duty. 2« The woi-iyrest cyc.le will be orUnted to itnlutain a nornal Uving i-coitine phased to coSn;idc with thu eastern U.S. t.imc zone, 3» i:,arh astronaut ul.ll have one sl?ep period of approximatej,y serec houro augjneated, wlien p;soltlft( by >• rap of not moro than one hour.. h.. Persem?l Triaha - cr.tirg hygLsne, exei-t-iae v/iil not be rigidly sch-duL'^dt and fo.r olsc.U'r p.>j-»nl;.'g p»'rpo.«.es ii^e allocatiODS for 'Ae.fe tasks will be ts^de by duty poriol. 5. Koutice micG'oa and for will be 1 ^ . 6. ml.':.3ica houflelc^ejiing :?.sks - stot .a checkc, LiOH changcsc log raa:lr.t.enaj)or, will ?!ot b€ rigidly rchodulsd, mis«non plrfoning f'urpor.os lima al'.c<atlonB for these ta. . • rsiy-c i by duty perJ.id- For prellBlaaiy AAP misft'on aiulysis i t wall ba asnu'^cd tSxat elgbl C8) hours p*>r day per or o tot-.-l of ?i» a-r.bourj» per day in aeailable for experitpeu actfvity. 2 * 5 S t a n d a r d ".U'rnjeft Cr-uw Duty Cycle -ind Ttnig Avtr-ilaliLe la Three^iwn operation with C.S o - GH docked <6 other vehicle. •20 24 D8 'v/T«--h Glean katch Ocea 1 1 V.'ei r.h 1 Oncn 1 ;,'al:<h Sleip i Si e .12 1,6- 1 ; Wa!;ch 1 Or .Iv'atvh •All tinea ere Eastern Standard Tines and the s t a r t of f i r s t d e e p period may be established for any given niseion f?*on i600 t o 20C0. . �^' Crev Tlac for gHtKiriT-ont Cirjoi-attooo (See sections and 1»3»5 iof derivation of tioec) ;jiii;;i>cr of Crev Avpi.loble jSpcn Tin ? 3 a UikO « ikskO 2 8 ?:X0 - 8:'fO 1 8 2:^-0 f nuiiours Avali&ble .for Z^poclmfoto 2>.:30 - 2S:00 (hrs.) 2* Thrc-'ngn Operation • one In (2M« TKO in uraocl-.gd II5H a> Pvtj Cycle 8 T^na: Doy/Niglit (x) XXX XXX XXX LE« n XXX Tx\ :oa i U3i HZ '••/atrh CM Ik rxx 18 16 xxx xxx 20 XXX XXX > i 1 V/p.tch na?' »>p#vn DUvv Watc'i end On'-r, l'u«y This duty cyolc ia based «a the folioving araolsoa: • 1) Kln-itaizlDj the tiipo aH.! three creii' 'fiC-'jero are asleep, simiiltaiseously. Ta tJ-.ls crisc- It le only for about 2 boura since ibc lac: ho»r of tbif sloop period la actually invdlvcc In personnel hy&iene and eating. 2) Kininieirg the niTJibcr of day u<-rlcdc »'jdc un.-ivnlLih)*for opers>::ions dc? to the LB4 rrsy bei-ug asleop. In this cas" only ore even day psrio'^ is lost. 3) This cycle Is based ai a 2-hour oibib- period for gro;utd scheduling purposes. Rjc actual cycle should be adjMsved to the tru-» orbit period tha*. vi.!! be closer to 1,9 hours for 'lO-tsile and 2.1 hi»urs for S-nile l»nor orbitn. 'PhiH will result Ir. ;u.-nor variations to the tine allotraeats available. 2.5.5 Zk Vatfh end Cofai D'*l v Cleeo Sloen 12 3U Watch Duty Period 2.5.3'1 Three lLm Operation vith 0" or CM JJoc"ifcd^co_0^ior V shlc le One crowr:aa vlU. be awake and oa vatch duty osslgcment at al': times. Durin-j these porlcda he v,lll be rsspensibir for the EMintentince of spacf'Crafo syGccr.S; roxauuicatioue. position and flight records or logs, and geaci-al operational actli'iti- —1 f I �Ta CHPo of rnei-fjcncy ?•© -illL f fcrt -wpilrle CowmadariEach cjcw (r'.'ti'.»er wt II v-'or^i two four-hour wa^ch duty aasSgnaicPta per d.ty, •>• cdt3tpl,y i'oliov.ng tbn sl«ep cycl# cod tiiQ ,'n':;';d.UteTy n.-ccosin,'^ t?i3 olifop cycla^ During each four-hoor vfTfi'b the roliotjojj aclirit.'.f.p 'jill ba perforseds 1. SJxteca (i6) n'cut.oq cut of every hour will he upcd for vehicle :sor ;.torJ loi: •V2"*ntoaanc.». Q. Stfl-up cbe-^k of ZfG hovvly (6 win.) recharge batter.' ae required. b. Statue ch-^rk of ECS hourly (1 mln.). e. Vo«ce oontnct vitt MSfS every 2 houru or once per orbit (5 atn.). d. Pi)r,^e fuel ct lle - al.i.ernate 3^ ard ©2 purgea every 5o5 hor.re (j.2 nie.), $ e. Si^-SCS eteluc check prsfcrftbi/ ulthln T/h range of HSFh every b houti' (3 mio.). f. Status check-of SES evsiy ^ haws (2 tnlo.). g. nritery check evsiy 7 hcurs (1 Bin.). h. S ii'^s check of CK-BCS in unpreseurLzed state every '2 Isoiu's (I ntn.) I, Alternate replacing the CK Id5H filter eloasata ever 12 hoMrs (5 ain,). J, Staiun chock of ryro batteri.es every k* Data aoBip to 11577 oa eocft (2 nxii- rj-aw tloci. Zh hours (1 oia na 2. Twcrty-i'l.t i .otn' teo fo,i. i-anco of poaiticm logs and bneir is'sc-icJ. rccrric, ; i-iboh crevoan wii. be expected to Raintsin cifficlert eppcecrair. pasdtioo ortenraf.-'on to be able to in\t.l«t! «d>o'-t pj-o-rlures at aoy tlae., 3" Twenty (20) aisiites for eating (gancrally enacka) during each wstob^ llils is ao arerage valiio that will be wprki'd on nn "as «*^'ai-Lable" baaio ly the crsu. Fifteen (15) MJ JI - tec .or exei'clse. This provides oni>half hour of cxerrlce during watch doty wliich will be added to one-half hour additional duriitg the open d»ity period. Tills • I cc- ^-orlced on e.n "ae available" basi-e by the crew,flo exert iso will be perfomed oa the da;, that a crevsan EKhea an £t;tra Vehicalsr operaiioa. « �5. 6. Tv/s»Dtj < 2 0 ) ffllPi:'.-op J*">r a i ' o i a p i ? v n l u e t o frs t h e ttSt.roiuiuJ , in^d c;i nu "hu ^bchty jKir \ M l c h ^ 8 o i o 1 n a t n.7 »*xp:!rioi''ni.nl the rptPro?-y hysrt«nt>. TbAs i n an rfquiiod" baale by : o u v a l l o b l o foT- 3 e r o n d o . r y 'ilicnc fliouifl prsmarlly f a l l into of nanlfujuf; ii; b<o-iied experiments or i f l l t - i a t j i i j ; an<J/o)* a e j . >;or:n.'* ' • o c k j . U c o n t r o i l o c l e x p o r t . ciPAte,. Gcnpp.all;- it-e :n'j -o t h a n ; 5 m.l.nntec e o n t l r i i c ^ ' M con-^ r-i r a . o'-« .'.i mental du-,..«o should l e c^a^•c!-•a. DurJivt frc.r: the eonKr-odi-r's f. or.'.- ported on oxperl** A' : c d i t i e d f o r the vatr^h d u ^ : h e i f a t c h d>i : y e r e w / ; s B w i l l o p e r a t e 'IJa) ' • 7» Thin c n v r ; j e'v^r<>D ( •>.> tjr'- t o a o n a e p i ^ n e d p e r w i t c h \rx i ; geeevolly ) o o r additional e::jjei-ltioPt 2.50»2 :-or rovljiatAonnl fjjcea T h r c - l i a e O p « i r a t ^ o •• o n r cian I4 i a Cll, iwo DCD In Lat '4'alrh Dfof Op3 l/ot in CM a» The ciagl? iituj i i Add'.n: onally, of b, t h e CI-! v i i l p a r f o T i n n l . l t h e f u c c t - i < in ntti ionc cal.icd ou'. 2..50-!. CD and 2,5.3.1 (2), h e w i l l c h e c k i i w i t h t h o I S i o n a niJji: r v ? ouce per hour ( 1 ci5.n.)» Tbr ouo-h^l.f O J ) >ioi:r •• i r i n s i i R t p l y p r i o r t o a n d lencirdi.? "c't foUovrtr.g tbo olr'-p poi-iod wiJl t o utfliaed to aco'icrilated s. • d. ooctionn .?»5.3ol < .\) and 2.5»3'>l (2) accoapLiRhod due 'O '?e,.nl«flp period. that ware not T h o s e prJ.iT'Erj- vo'Sch f u a c t i o n e w i l l a r e r a g e a b o u t Th.c r<'.v<iAain[; c o t . t r i t j o a eectioii notel In sactljuo 2-5-3.1 v m I I h-i l i s t e d u n d e r O p o n D u t y 2x3'^* ^ a t c h ^ Pti'-.; 0 3 o f ':Vo n-;n 1/ '.ig^ *• '-very C ) n i n u t e o on* of hour Hill, be iiard for vehlolo aonltoriri^ and salntorancei ^ chec): r,f ppg hourly (6 sin ), batteTdco, an roqutrsd, if capcbllity t. I. . ^fO cinutoo per hour. Ihrc'-ij;!! 2 . 5 "> 1 ..." pe.rfoi-3 t ' and Bainter-fineo functions of recharge e*ists, » O 2) 5) S t i t u i c>*eck 'f 0:^5 h o u r l y ( I t a i o . ) , V o i c e c o n t a c t w i t l i CK a o i a - l n u a o f c n c c h c u r l ? O fflin.) Voice centaol with y.STii per oriTit (5 niji,). every two hours o r onct �5^ i' j Og 6) 2-.5.'* '-f.abl'i - ait.fr-nnlB Hg . (12 n^C,), rep.\fl-'n ..f'M I. 01: niter elflttonto evory '5 »jn^). ho'irs Open t>L;ty Pt rir^r 2 . 5 . 4 T h r e r > ! : » a O r - - i v r ^ j a n W t U i T M r.•• C M Poe'tcd no tm Durlnr ari.y S'uUoiir perlcS K V H will bAve O'A© contlruoar oaf'T duly Il^rlod. D;:;-jrr.* thio period cortjjin houe'?ke3pir,7 r.:'^ nuai te p.;f i\-.r-scd hut the ren-eind^r of t';tl5c" ie tan> lible for cr.'r-. r.t acti'/ltj «»rd rc-quJrcd Pav^fjatlon.'il fAxca or .9pTf;aor.v.ft. jaiineivaro. Tho foliowing act:'.Ham ore iurludti jurieg thi.i psrlod: 1. "fciko ^.'ip (i hour), rhic ot-a bo eoho-Julyd by tho crew o "as cvoUabic" baoio r.nji be eUsipatod oi.crxionally 2. 3» OOP hot Baol (I 5our;. 'fbio le aohedu.lcd for one }>• v pli^'W cotae tvae fir rolavation or recreation. oxorriS'"; fox* I/? hosW' I'.xie vfou.ld riortnftlly bo broken Into tbra" 'n- C'-O) Hiaout-e parl.cic nnd cr.a be niuiJp.-xcoi cep jiona lly. J'O exercise in i t-nuirfd on vba day a ore-.msin piirforu? rn cxtrn rehicular operation# Perform waste e.llmlrntioa and body oloooins (1 hour)# 5c ' k 2c5»^t.2 'ITjo rcBiining tlfle i s avaUrsble for other activities to. o hours) . a. Flight optmtloa; - r-oe section.3.0 for required fit;!.' openitloa f»inctl>33- b. Bcfpriaent Three-Man 0:><-ratlon - on r In - to be dete/KinfJ» two in tBI. (To be added)# 2»5e5 Sleop Period 2«5->5«-l Three-»Man Oppratloa V.i1h TH or CH Docked •*<> L3i The sleep p«rl-od for escn nen will be eif;ht (8) hours. It anticipated that about eu^cn (?) bouro of this lice will be o f f e c t l v c e.'.n";-. Tt • r» -.-fria^ t l c e w i l l b-? ntlV;.'':.! t c p r a pait tin £.l^>p ca risixj, cl-v-ninr cp clxe ar.al1on, parf.vrraing pcrsuciicl irrglone, and earing b.ranktasl , T5ic iQ'Uviduals eigh.rh hour of deep will bo in the fora of a nap during the opea «!uty period, (Sao 1,5.5.1.1), / O 2, �J - One in CH. T^ Q Th- flc-p IVnr.i fry.' eacfc ooc uiU be 6c-7fn (7) hour3, n • a n t i c l r . » t ' : d tf., -. M?oct si:- ("S) heuro of t h i s t l a e i f i l l b e efro-rtiv.? Tljp roirinijis tiino rfili he uttliiod to pr.-. paro t h e alu'p otj^tuo aoc. o n riftios, cloanlng up the oloep BtatioQ. pevic-mJn^ F-eroci-nel K yfj I ousc. nncl sating brcakfosr. Depe..<jlng oil tl;s iength OJ' chis type vC operatiun a tuip of ono to two h;. -rs dwratlot ehOKld bo o^;hc€tulod durJac tho opc^ poricd- \v. 10^ �o^f:i?ATicNAL coNoTRAiNT.; 2<6^1 Kii;src;« c Tjiipch O.-'c"n". Io;:« to Liftoff 1, Inunrh cuUoff time io IfjCO hours Iccal t^me b^<-.PUoe of recovery (a) rcqulrcQcntg.. 2« Ho cxpcrjnent activity w^Xt r-s-iuire crcv tariicipatlon itore tfacJi (b) 90 minutes, or loss than I nluite prior, tc .dftoff. 3» lixpnrlijient uotivit-lea during "fie coi'Dtdowj* are iimitRd to those (b) that can bo perforned by the ayoteme ensinacr from his counh pooltlon. 266'.2 Pone Vi'iT'ch and Sa-rth Crbit 1« J'roa Liftoff to confirmation of orbit experlraeat activity is (b) u-ndruirablo.. It required, it should bo Itinitud to lha capabllliy of the .vycitoaa on^lnocr from hLs couch poeition. 2B A ctntun check of all systems wil-l bo pei*foni'.ei after insertion, (g) Aosume ^5 minutea with all BoiabArs occupied except as oote<'. above, 3' Eftttcrj-ca will bo recharged after .tj-'oertiru, Hcniml span is (a) 100 oln-'tes but crew loading :,a 2 nlautcs for jyeteca engineer, 4, There shall be a mloim'jra of o!ij orbit piicr to S--IVB/CSM (a) tioparatlon. 5, The S-IVB G&C and PCS shall b*? uaed for all aaJieuvers prior to (c) S^r/B/CSM Eoparation. I?iU fine alignment vill be required once per day for normal <c) epaccrraft raquirenents f20 ns.-mte), 7o IJTO alipanent requ'res hiving the '•X axis cj-.; i-•*'i- r?, '.1 (c) local horizontal^ pointed in -Ho direction of flight and aalntnliuvH within + JO' of the plane of • le orbit. The axis nict re-ajr. r least yj'* above the local hor ioo, 8, During near earth orbit cperav.ioas navigational sl^tiago will i>' (b) token 00 loss than twice per day (3^ urinates per set of three sightings). 9B Oribral navigational eightlnga require having the •••X axis in thn (c) dlrectioa of flight anl the +;• axis n-var iocal vertical and pointed toward earthB 2.6,3 Transluugr Tn.jectloa 1, The S-TV3 provides G?;C and thi^ust for the vraaslurar Icjsction. (c) The -j-X cxls is for-i.-arc rnJ approxiPiatcly parallel to local horisoatalft The *-3 axis la down aad appro^J-o-etcly pajvillcl to Jocol vortical. �& 2 <b) 5. (g) battcrjca 20 niratea Prejvrtmlioii crev tlrae l l o down, arlor to d « r b i t bum (20 siautoe) for tranalumir icjcctic® incbidee eyotsas IHU c o n r o e a n d f i n e a L i g a a ' . n t chcc'rr. — ^2 mljiut-es iOTOiv . - a l l crew acKboro» 2,oJt Trpr-.npoc-lllon npd Docjfln^ 1, (c) 2. <c) The i a tho active vohicle diirinj tmniposition and docking* Tl}r S—IVB l a l a The f.-l'VB o c p n P s M o n tranrpeoition noaeuver ol«rla with within + JO" of tho trajectory pleucs the 3* (g) r o l l i a order to s-.llgn +X a x i s f o r w a r d a n d *2. ^xla frofT t h e S - J V B t h o CSM p o r f o m j a + 1 8 0 " a --63° ' tfaa a t t i t u d e IiaLd n o d e - -Jp. After eeparation p'tch maneuver follovicd by for docking, Tioo for tranepoottlon anif decking including preparation, jettison o f SIA<. a n d p e r f o n v a n c e o f b a r v l d o c k i n g p r o c e d u r e o i s 4 0 m i n u t e s Inrolving a l l crcwucn. 4. (g) 2-6«5 Time f o r S-IVB ceparation including preparatoiy procedures i s 5 minutes. T r n n s l H c y . r Co.-5j^ 1(c) 2» (d) Tno coast period iacluiofi o mariruQ of nine nrdcourse Rovigaticr . c i g h t i n g a , f o u r THU a i i g n m o n t n a n d t h r o o d c i t n V c o r r e c t i o n s . Passjye Hiermnl Control (ITC) io required during cooct except a s Jnternipted by i'TC t h e Cf-H mte of ' \ axis. the j'equircmonts of y-Z phase l e pointed toward This Periods of nor ratio ITC o j u r a t i o n e r e I t i l ^ - - ? contlnucie f o r a long a t t l t i - d e hold t i n e , t.hs PTl*. the 7 aud ••cf The "nile-oi'''thUaE." iratlo of For ehort attitude hold tlnco (l';6e roll to hold ic than 15 minutes), tkf i s 7 to 1« Attttndff Eold 5 oin* Hequlrcd Roll Tine 55 15 laln. X'.75 h o u r n 30 min. 2.5 3 hrs (esx.) 3. i t s initial oi*lontation, if s,pp:-oviBatoly ^20" about must bo follovcd by 15 hc-sre of i s that the rollLog cictioa ^-onbines with vehicle residual d r i f t ra'-fto causing the X a r i a ro pi'^cees about 5 to lo Duri.-. tho tnm (•20") end a r o l I t o 2*5 rovolvi Jons ]v?r hour I s coteMlshcd about precession creating rocotiooe Z cscs. periods itrfo 1 abo-^e. hoars 15 hrs. Tine period for navigBtiocal ei^^tiugs i s 36 Bin. InyolTss one c m . (g) 10^ �P®rio^> Tor oid-courc? rcrr^^tion involvt>« oil thx-fy crewmea, includeo ri^noutfcr C/K to dooirM atUhide^ syatea en-up acd (g) checkout, firixij; of aj-uv.'> for tillnpc, SPS firing, rci-ifl'-etiou of doUa V cl'tnlapd (requ'rce contact vUh Wr-FtO^ poot ilrina eyoteia checkn, 25 oUa. j" 5 vg) 2.6 6 TXtno poriod for an TKU ocanfle oUgnriCit. £c:ji)onco is IL nlnutos, 6 min'itcs additiorjil for fine .lUEftmrnt, oad ? wlnutos for a finn allgninont cneck. lAxnur Or'olf Tn>;"vtJ on 1. (c) 2o (g) The X axis is appro^rlnvjtoljr pn-allcl to with -X forrfnrd. Y cr Z axes. th? limar local borizorr ' Ho reotriction ia placed on the direction of • TiiBO for lunar orbit inj&cticn Jjiclndcc sy-^teoi chorlca. lOT eoar, ollgnaeatp IMU fine alignnant. manouver C/H to decirjA alignfflent^ eet-«p lOI navigation pamneters, ullage firing, SFC firing, poo-: fire syetea checka - 1 hr. 5 oin. 2. 6^7 I.uner Orh: t 1. Co) Orbital aav5gr.~iorj.al. iiighcliign wil.l bo requ.ii^d durJ.og rbo first, two orbits for orbit coaC: nnatlon.. CSM aititudc will fc? with the During thin period the general cad +Z -X cxsa jwlateci below the local horJronfcal plane and the X ax-ls will .'io wlth.iu 6'J® of tha orbit p.i-.no;. C 2, (c) A Blnlojum of thros cib'tal car gotio-al s'.ghtlnge (iitiliaiiig IHO alignment of 'lO a.-lni-tea) will he x*ca«.tred daily. See itea ebove for atl.ttUfic3% 3. Proper ECS oporatioa in Invar >>rbtt la dejj.rndent upon the orien* (d) tioo of a plane which b.is'jcts (c) and which p^.rnlloi the X ttxia. .he CSK withjn 25" of th:i swbpoir-r po^it dxrertloa of i.-.a- rr . Devl.a'-.ior froa thia require- ortilts every two days. IKIJ aligaiaoiit ."cccasita«ea pli-.eliig the (c) i.h.f.e plr.r.? a-;iet; rtmi- < the r.str.t at vMc!i t-.c iise intersects the .lun.ar (rjrj".»<-e). Bent Is aIloj:;ed a n-uciM'.'ni of +Z/'"f and -Z/+T quadranta The edge of vX ax.ia in the general and wiiatcinirg it witnln 6o* of the oihit planelihe -fX axis susfc ^etEa^n at least 35® BJ»cve the IcK^al hori-zontal. 5, (g) Tlae fox in;-tl-al rotry ici o LfJi-fiq'iaLiac CSM c:\d .lor?: prcpsure.; roQove and etow CH preaeure aid thonsal fcatchear puTforvi CM eyotpm checks? diecoaaar t and blow probe and c-4*o.^e, cheek for Lffl pressure equal!tat loo. op-ri LBl hatch, tranafer unbiU.cnl O 6. <s) Time for initial ro trsnsfer tc 155'. - It. tiiin. rh-rkc.it activate and chocjcout •jo-oiunica-' tlona, control aed v.-^tning sysven, power ayatca, SXiSj ARS, fanB.^ transfer of PISS and other eei:..'.i:nca! to LEr!? suit transfer serond oan, d-:^ploy landing g?ar, checkout propuliUon r^ystcae? coarss and fine allgmjcnt of liEM TIPJ. set wp rarisation ia L£K, close up I~; -- 2 hro, -17 .?5n. jOfe �2n6.8 lii'/nv Trrnnfor and Uindtug lo Tho 1 hour pr.'.or to I£K e^^pnration frao tlin CM, all three CTv^ («) cc-j;hor3 will be totally' occupied w.Ub Ration nnd other ispaceoraft xreparatory aetivitias, Z . -Kroa lEM cop^ratron to ton-hdo-n, ao o.rperi.montQ will bo porforC' ' Ch) oithoT on-bcard LEM or CM, • 3# "^he two LEN trrt'vnflQ will have "•erapi.ritfd a ulcep cycle no store thcc <b) 6 hours prior to start of litoar trr.anfpr. 2..6,9 Lio.ar Surface 1. After landlns,. prallol.nary LSM cecxirtng and checlrout tiote Is 15 eiu. (g) 2.. Preparation tim? for initial Ivr-ar egress •• -^x^^llne .r>rface, (g) photograffti, review exploration plans ia light of actual conditions, check out ond don suits and PLT-S equ^poent., check out cconunlos* tions, get ocicntlflc oqulpmenl ready - 1 )jr,. 8 oin<c) Duoo lEH preosuro - 5 oin, U, Erf.t Lai, get scientific equipaent and 3ow.»r to gro'ind, oliBb dc.'o (g) loddcT to lunar surface, chock nobility cum iru"fnce coaditions 12 Din. 5. Conduct external inspection of LEW - 5 dn. (r) 6. Erect and align lunar surface S-band dish aotonna - 20 Bin. ^b-) 7. Climb ladder, transfer equlpfflcit into LW, enter Lra • 2 sin, (g) 50 sec, S 8. Repressuzdso LE31 - l8 nin. 50 <ee. (eirgie oysten) (g) 1 Bin. 20 £«, (both'eyctcr.6) 9. No biological waste shall be disposed on the lunar sarfsce withou (g) sterilization, • 10, The LBi is designed so that it con bo left unoccupied with the (g) cabin unpreaeurlzed on the lurar aorfnce. Etqic-rlment design should conform, or posnlble eil'ects be properly defined* # 11, Figure shows tkf- c-xim* disteaeo for E/A froa the I£K as a function of the duration cf the EI ertiwily, TlJo ig based on the amount of oxyger. available to provida purging of ^he SI ffJit in case of pressure stiit rcvitalizatlon syeteBi failure. 10-1 �2.6,10 T.i;inr 1 r:-.-? ZVOU8 f-rc.-^jror:.-'. fo-^ J.^-^ach - L t r - I = xE. 2. (b) Tl-.ore uj.li be r.o exi>9rici.iat activity dvwin? L5J1 iunor return, doekir-s, ="d period throu..^ trausearth a.iiJftCfc:;.on.. JJ. (g) Tft't I.TI vfl be "enof.derni the neiive dni^kJn^ "ncaber on th® roMiru fcr.irtzroua. .9 2f6«l.l Trencrifi'-tb T^jrcttoa 1. (c) 2- (c) (c) k, (b) C 5, (g) >2i.6vl2 1- FolloHiPg TI'U alignTBept the +:i lucla in dJ.r<ictod approx^natoly pnr.illel to rhe local bor-',zont;al prior to jr-Untiog transearth in.ief.ticr . Hocharge b:i>-tQrir-3 20 oiontea prior to dooiblt burn • 20 ain. Prcperat ion iinte for traeooanJi injectioa 3 hrso pr'or to engine ignltlo. xrill take approrltcatoJj -gnd TH/SM $*n^3rn_t loa 98 Trnr'.oluner Coaut '2,6r5'*l) 2e <c) Saoe as Tv;jnaluri.nr Coaat ''2.6.''-2) 5.. (c) Tn addition to tho .-TC ratiulrc.sants of Iterei 2 aboTe, It ia necoasary to provide pre- re'er.-;ry coolirg j!or the for,<ard heat 3l!i9ld> Tliio is acccaplifihcd by keeping the -X axis cumM sun-.T-aT^J i/itn,ln ^o lioitg specified for PTf*. 4. (a, b 8f c) * IflU allgr.r.er'j; io tJie aftnc as Innar orbit (2.6-7), Trrrn'-trth Co<^n (b & c) (a LSTH Jattlrcn orruro prior to oll^^ncDt ejkI la acooupllahod With tbf -X axis in the dircctLon of riJgbl. msd Uie *Z arts pointed tovmrdo the liiv'nr f.urfvjc. tt No e.-nJoriccntnl or .•3peri,n.l ope-.-atlooil activity rcoulring crrw attenticn e.-mll be echcJulcd during the final hours of the Ti'arcear'h Coast period dug to the cr.ltioality of «ct«blJ.shlng a cafe on'-ry corridor, liiui-pueat etownge bo rooplotGd during this period. 5. c) For CM/EM e rnr^^-e.tioe tho »X s.tis is rotated 60-70® nbovo the dlrectloo of flight and ti the trs.Jectory plane. The +Z axis baa s 'zcii.-.iTs prnjcctlcr. ra np-wr.rd l?c-^l Tartl'r.l. 6. (a) The zy^'"-- s-:-arE':i,:: a-i ;;re-sf:7y s.aiavTer r-j>t ce r: ::a-ci Its less thxn 5 clautas prior to reaeliiSr; ^O.CCO fee' entry altitude. i ICS. �7. ferforr iPS statu© clieck prior fo CH/SM c^pcratioo (6 mln.) and .n) © Bain bus status checlt eftar separation nr.d prior to ro-eatrr (5 nlQ,). • 8. Check pyro br.ttcriss prior to C.V5M esparstlon (1 ailoO, (a) 9« Disconnect fuot colla froo CM bnoses orlor to CH/5H aaparatioa (o) (Icda.), • 10. Porforra oTatuo check of ClVSCS tvo houro prior to CM/CM aeaaratlo . (a) (1 Din.), ' U, Preheat C^/RCS wigine vaivns 10-15 atnutes, to be corjplcte 10 ola'.tca (n) prior to ri-I/JSi saparaticn-. 2.6 15 Rg'-ertry nrri Piecoy.^ry 1- CM landing shall be planc^-d no earlier thsn one hour prior to (A) Eunriae, or later than three bo'.'ra prior to ouacet* 2. The longitude of entry for both the CH and .Ti ojuat bo such that (a) the GM doon not endanaer any lend raaaes., 5* Sitry stares vlth the —X axis In the trajectory p32me aod rotatr-' (c) appro::lnvite3y 26* earTh>fard from local horizontal and vd-th the *Z nsia pointed avay from earth. A, (fi) E^orin'-dta or data roturned In the CH. mu^t eorvivo a aaxiBua of two dayo aftor landing. % ((A �2.7 op.•^ATTO^?/.L 2 ^ 7 1 gns 1. (a) i n vattcr.,; •'^.^.-•,?(».- J-.o ;<.on." '. C?yr. - ra l"v« Tne ndiator inifti; toapL>^i-ntnrc r-ua^; ba i*A*3tr.ia:i r.bov® 75®F fo prevont frcftriiia and b-jl^v "F to prevoni bnlHua- 1'h« - folL- ving .nr® operational ••ni?.^of-thuB'a" ron-itrolata. Where expor. riai raquiremcata roquir-a rioUition .>r these rules, & d^tai.V-i vhffirmal balnnoe onaljats ohoald ba ci-.ie. •* 2.7,2 2®7»3 b(a) The apa-'.-ecraft attltvde ahould not be .-'cr.Btralned In an ir-crtlai or earth relftive orientation fc-r longer than 3 h-'-G .. C, (a) Eleetrieal loads of loss tlias l68o»l65K3'vatto require periodic oxpoctira of the radietor to tho sun to picvent freezing, Routiaa Ovi-Tn tlon.?! Coaatrglnts SPG prc.p ;llant O'lsi be rsintniiied clove 'tO®F, Alihongh no fixed rule if poGjiiblo, attitude bo:d? grc^t-er t-uir 3 hours in curatior without uoLrc incidence on the £»•! aft end should be avoided, bhoro cxpcrlrtent cctlvitJes exrresd this tiue, ti theroal aaaljalr should be conducted to check propellant tc«porr.tari?6, PCS fSM) routine Opcrattooal roGgt;-g.intq 1,. (a) 2»7«'f' Tha radiator ourfoc'j'nliould not be ercporad to ao^ar radlatlc. Incidenrro angles of for mora thar 20 clautss por orbit cn vhe n-emge to p.i-event boiling, Jln-:inuB expocurc of theo<' rnslao tor any one tine ifj one orbit, Service Pre'M! J'l i c.:t Syin c-n 1. (a) C a, (a) /'ny f pe quad of the ECS (SM) ihall not b® pclnted towards deep cpace for prrlode exceeding 6* "jO hours. S—IVB Po^itj.re ^'eratipoul^CquKV-raiuj-g i, (a) 'Hie S^TVB propellmt tar.k« oatv be veutod parittdlcally, probably about evnry 'i boors on aa avenig®. 2(a) The S-1V3 ofabie pJatfora in tha lb has a ::».dd!.e gimbnl restrlfttion of +45® about the X^dxis vehicle yaw at luunch, roll la. flight. 2.7.5 Ouidence end Jfevigatioo Syntem RovHoe Opftiational Con^t.'rslnta 1. (a) O The S-lb'S stable platform in ii.e 10 has a slddie glsfiai rectrlctiVon of ^5® about the X-ex<a vehicle ji-w at lauochs roll in flight,*' �2 8 Rr,^UIRg!ir.'iTg 2.8.1 1. SPS propolLs^t chctll b* kiiatainod above lift c^rnbutloa (a) Inatabl'Llt/ iovoi during any d<orbit ironeu^rr, (OX Yoot Iba.). 2 . Contiuuo':a iii'G abort capability will be ea'At-ntalacd. (o) 3. Tbo nicaloa rhall be aborted a® eoon aa i>038lblc after (a)- wnoontroliacl lo^3 of cabin prec^urizaltca. U- SK-KCS dcorbit capability chnll be provided during ary? portica (a) of near-earth orbital flight. 5« In-fl.''-ght contingency octious eb&ll b© initiated prircarily by Cg) oanual Rcr-an utilesn cfflorgsncy corditlon rc-iuirestcata ars cuch that c!.anual opo ation Is incoaelsteat with crew oafety. C - ��r- ATH Sfcr.MHzr.tior ai>:I Ccjcvn1 T ..— . •» t>i.«»-or-«v ^*^..4—-,—^-^- ui:;hia Coicr>'nc<&8 of huspa cr.pablllty By Anolyzina crow cfipability to acquire target within 10 oinutea \j Dotcrainios crew inputo for autcaiatic operation of the ATM ^ Evaluating ooquencc for cxperlnent cctamanda (tsaxiraum 100 ccxsands) Selecting control toodeo coopatible with operator capabilitioa Analysing available ATM target and status presentetioa har(h7are Selecting diaplsQ' and control coabinotlon which places least demand on operator skill and endurance Insuric^ that AiM to opGrstcr input 2. c end LE2I ASS prc'ide near synchronous respcnse D-Jtucwitie training requlreL^nts to ensuire ma-y<tmrm crew proflciencv t^ith selected /AM display ajid ccntrol hardware By Specifying critical tacke required for perfomeace of A'-AI alsoion Providing course and briefing outlines for crew fcsdUerizatioa and training InawiiiS direct ccrrolction between trainer and opcracionoi equipircnt •T h �ATM 1. r'Mtabll.'.(:y_rnd "roCj.\e Evaiuat* haoiualtiiity By Analysing ovorall usabla volutn.; Avnllabillty Insuring ATI! peeullcr and crev fiupport equipasnt ecaplles vltb buisaa enginacring and fllghc snfcty criCaria Inruring adequacy of Illumination for A1^! display and cnntrol eystems Entabliahing vrorb cycle conipecible with overall mission requlrcnonts and Gcailni/Apollo data 2. Evaluate carrier profile for coirpatibllity vitb ATM oysteas By Chacking ATM retrievable (EVA) cassette alze against hatch sizec Evaluating data ensootte maaseo to eisure crew translation capability Confirroing compatibility between cascettes and carrier otowago provisions C Evaluating ATM DJC for cdB^liance with human engineering work station criteria Confirming volume allocation and stot-age configuration for special EVA gear, i.e., maneuvering system, tools, lights, life support f O �Am u:^7^^Ac^^y::a co??57p};p,^Txo^ls n.^onj'.vof^jr.tfl Fvow ATd 1V\ Ground chsckout of ATH OrbJ.tnl checkout of All-I Sonceeraft poAntlnE end trncking prior and durlns experiment Crev notion reotri.ctlons during tracking Ara poiutlag end trucking design and techniques ATH enperlircnft Goqucnclng and control Tarseto of opportunity (in-flight noprosrninalng) ATH ocbltcl reactivation (potential rainfccnancc) Control/dicpley coinpatibllity with LEH/AXM C£-.D Orbital/baSC-H cosaounicationn and flig^C planning C ^ f, E7A ti'."/, film data retrieval (esasette management) r^'A crew equipment fcr frequent Bv'A'b (mod^s) Cr.--.- locc.-nction and tcthsring (hardware) Cv£!.* rr:tabolAc load (vork cchedulc) IllualnaCion duriaag EVA Crew corpartceut pre- during and post- KVA procedures Crcv; corrpartiMnt EVA coinpacibillty (b&tchcs, O2 supply) A'.il rc^tctiration and rafurhishmcnt (fcatterlea, Ci-';G'8, etc.) Crev force aiui morsant impacts on iVlM Instsllation design Special tools and test equipment. � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket. Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite. A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used. Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context sdsp_skyl_000073 Title A name given to the resource "Human Factor: ATM/Skylab." Description An account of the resource The "Skylab" in the title was a later addition. This is a summary of the human factor aspects of the Apollo Applications space habitat. Creator An entity primarily responsible for making the resource Martin Marietta Corporation Date A point or period of time associated with an event in the lifecycle of the resource 1966-09-21 Temporal Coverage Temporal characteristics of the resource. 1965-1970 Subject The topic of the resource Martin Marietta Corporation Skylab Program Apollo applications program Human factors in engineering design Apollo Telescope Mount Onboard equipment Extravehicular mobility units Life support systems 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 19, Folder 9 University of Alabama in Huntsville Archives and Special Collections, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource Skylab Document Scanning Project Metadata Skylab 50th Anniversary