UAH Archives, Special Collections, and Digital Initiatives

Browse Items (970 total)

  • Instunitcructest_091307144134.pdf

    A three-foot high Instrument tional Business Machines Corporation will be launched into orbit with a huge Saturn second stage
    later this month in a crucial test for the Apollo lunar program.
  • Instprogcompcont_082007101905.pdf

    A number of considerations are necessary in instrumentation programming, many of which are either not applicable or applicable to a lesser degree in other types of programming. This paper discusses these problems in general terms and illustrates how they have been dealt with specifically. The latter is done by describing the programming and operation of a data reduction system.
  • Inspweld_022008153722.pdf

    Archive copy is a poor photocopy. Cannot read.
  • Infoaboupratwhitairc_082007100855.pdf

    A history of Pratt and Whitney Aircraft Florida Research and Development Center.
  • InflapolsatuV_061908163151.pdf

    This paper presents some relationships between Apollo/Saturn V launch operations and multiple lunar landing sites, including the means by which site selection could facilitate launch operations.
  • imptheuprsatI_051608130002.pdf

    This paper discusses five improved versions of the Uprated Saturn I that were studied by the Chrysler Corporation Space Division, supported by the Douglas Aircraft Corporation.
  • ibmmobroolenfletoaposatunifab_031808115026.pdf

    This article was published in the April 1967 issue of Contamination Control, Volume VI, Number 4. States: "The extreme sensitivity of critical parts in the Apollo /Saturn Instrument Unit (IU) has demanded unique clean room techniques by International Business Machines Corporation."
  • IBMcleanroomcome_042209102226.pdf

    A history of the IBM's Space Systems Center clean room and a description of its uses.
  • ibmaposatpreinf_051608130354.pdf

    These are the facts about IBM's role as a NASA prime contractor in the Apollo/Saturn program. They are organized for quick reference. Computer terms are defined in a glossary. Glossy prints of photographs and illustrations are available from IBM information offices listed on the following page. Please order by photo number. Andrew J. Cella Manager of Information, IBM Federal Systems Division.
  • Huntisasdec68_040709153450.pdf

    The following article is a digest from the Book, "From Peenemunde to Outer Space", commemorating the fiftieth birthday of Wernher von Braun, March 23, 1962 condensed by H. M. Hammac).
  • humafactatmsky1.pdf.pdf

    Statement of work: Man/Machine activities -ATM; ATM problem areas; EVA commuting problem; Other EVA considerations; Analysis of crew considerations Mission 211/212; Mission objectives Crew Considerations; Mission Fight Profile & Operations Crew Considerations; Experiment operations crew considerations; EVA equipment requirements; Crew considerations carrier recommendations; Conclusions and recommendations crew considerations; Crew operations requirements preliminary 10 August 1996; ATM stabilization and control; ATM Carrier habitability and profile; Other ATM man/machine considerations.; Original is a poor photocopy.; Document has no page numbering.
  • HsvSpacCityUSA_062408165736.pdf

    An article describing Huntsville's role in various space related projects.
  • histsummvonbraumissteam_030607115637.pdf

  • histsummvonbraumissteam_030607115637.pdf

    Four and a half years have passed since President Kennedy and the United States Congress established a national goal of landing a man on the moon, before the end of the decade. This brief history is designed to be a working tool for use during the second half of this great adventure. It is expected that by presenting the events of the past in perspective this document will become a handy reference to accomplishments of the first half of the program. It is hoped that this volume will be of value to those directly and indirectly concerned with North American's portion of the Apollo program. This history contains a chronology of significant events, as well as material on the management of the program, a record of some of the breakthroughs in technology, a report of the hardware produced to date, and the many tests performed to man-rate the equipment.
  • histrockdevsm.pdf

    A document recounting the history of the Rocketdyne Development Division
  • lettdrwernvonbraundirmsfcfromholmes_031607120935.pdf

    Letter to Wernher von Braun from D. Brainerd Holmes. Contains C-5 definitive contract schedules.
  • lettdrhughodigfromhughdryd_031607081156.pdf

    Letter to Hugh Odishaw from Donald Hornig regarding a previous meeting as well as an F-1 engine report.
  • letfrogeoemueassadmformanspaflitomrjlatwprenorameaviinc_020408134617.pdf

    Letter to J. L. Atwood from George M. Mueller regarding the S-II stage.
  • letframurpvppublrel_041207100000.pdf

    Letter to Frank L. Murphy from David L. Christensen informing of an awarded contract. Also requests documents.
  • lauvehengprodevpla_073007101313.pdf

    The primary mission objective of the 5-2 Engine Project is to continue development of a liquid oxygen/liquid hydrogen engine. capable of high-altitude restart. Both Saturn IB and Saturn V vehicles will use the J-2 engine; the S-IVB stage of Saturn IB vehicles and S-IVB stage of Saturn V vehicles will be equipped with a single J-2 engine. The S-I1 stage of Saturn V vehicles will use a cluster of five J-2 engines. Figure 1-3 illustrates these stages.
  • launvehirecosystrequ_061407154402.pdf

    The primary considerations in the design and development of a recovery system applicable to present expendable first stage launch vehicles are discussed. The general requirements that define the essential characteristics of a feasible recovery system are derived from three critical phases during flight. The degree of criticalness is primarily influenced by the conditions at stage cutoff and separation. The three critical phses of flight are broken down into the following: (1) conditions and requirements between stage separation to re-entry; (2) re-entry; and (3) terminal descent and landing.
  • launvehiengiprojdeveplanjanu1,1967.pdf

    This revised edition of the Launch Vehicle Engines Project Development Plan supersedes the issue dated July 1, 1965. Significant changes which have been made are:- Removal of classified data to permit publication as an unclassified document; - Removal of material applicable to the RL-10 Engine Project which was transferred to the Lewis Research Center effective May 1, 1966; - Elimination of detailed schedules which quickly become obsolete; - Punched for maintenance in loose-leaf 3-ring binders and for ease in updating material through issuance of replacement sheets. Binders are not furnished. The information in this document is current to January 1, 1967.; The Launch Vehicle Engines Project Development Plan is established in accordance with requirements of NASA General Management Instruction 4-1-1, Planning and Implementation of NASA Projects, and OMSF Instruction MP 9320.044, Preparation and Revision of Program/Project Development Plans (PDP's). The Plan, herein referred to as the PDP, has been developed within the scope of current Apollo Projects Approval Documents (PADS) and will be maintained by the Engine Program Manager to identify program requirements, responsibilities, tasks, and resources, and time phasing of major actions required to accomplish the Engine Program.
  • launinfosatus-iv_062007154516.pdf

    The RL10, which powers the National Aeronautics and Space Administration' s Saturn S-IV, is the newest propulsion system to be put to work in advancing our nation's space effortr On November 27, 1963, a pair of RLlO's successfully powered a five-ton Centaur space vehicle in earth orbit in the first flight demonstration of the outer space powerplant which uses high-nenergy liquid hydrogen as fuel. A six-engine cluster of RLlO' s, generating a total of 90, 000 pounds of thrust, powers the Saturn S-IV stage. The 15, 000 pound-thrust engine was designed and developed for NASA's Mar shall Space Flight Center at Pratt & Whitney Aircraft's Florida Research and Development Center, 20 miles northwest of West Palm Beach.
  • launcont_030209160221.pdf

    Description of an 8 x 10 inch black and white photograph.
  • Launcomp39faci_120307161856.pdf

    Article detailing the different aspects of the Launch Complex 34 facilities.
  • LaunComp37Faci_062508141423.pdf

    Article detailing the different aspects of the Launch Complex 34 facilities.
  • LaunComp34Faci_062508095836.pdf

    Article detailing the different aspects of the Launch Complex 34 facilities.
  • kscaposatVmastespla_110207091724.pdf

    The John F. Kennedy Space Center (KSC) Apollo/Saturn V Development/Operations Plan, K-PM-0, establislies the requirement for an Apollo/Saturn V Master Test Plan (MBP). This document, prepared by the Saturn Systems Office.
  • Keymsfcpersfor.pdf

    Essay detailing potential candidates for potential interviews.
  • Keyeveninthe_120408112540.pdf

  • junovvehiclers_022107152001.pdf

    This report io the second in a scrics of reports on the JUNO V Space I Vehicle Development Program and indicates the present status of the overall I program. The objective of the overall program is to provide a reliable, economical, and flexible carrier vehicle with relatively large payload capability for orbital and space missions at the earliest possible date.
  • JunoVtransfeasstud_022807133058.pdf.pdf

    The purpose of this report is to present an investigation to determine the feasible, practical and economical method of transporting the JUNO V thrust unit. This includes the first phase of transporting between Fabrication Laboratory, Systems Analysis and Reliability Laboratory and to the test stand, as well as the later phases, onto the Redstone Arsenal loading docks and from there down the Tennessee, Ohio and Mississippi Rivers to the Atlantic Missile Range, Florida.; Transportation and Packaging Section, Systems Support Equipment Laboratory.
  • JunoVspacvehi.pdf

    The initial phase of the JUNO V space vehicle development program, as presented herein, provides for a static demonstration and a total of four flight feasibility tests. The latter two flights will give the U.S. its first payload capability in excess of 10,000 lb in mid 1961. The objective of the overall program is to provide a reliable, economical, and flexible carrier vehicle with relatively large payload capability for orbital and space missions at the earliest possible date.
  • Johnkennspaccent_092507162139.pdf

    This is primarily the bibliography of an organization located in an area which was once inhabited by more baasts and birds than people. The evolution of the Kennedy Space Center :LS :A .ceable from the Army Ballistic Missile Agency and Marshall Space Flight Center, Huntsville, Alabama. That period is fully covered by Historical Origins of NRSB's Launch epesons Center to July 1, 1962. However, because of the core working relationship between the Kennedy Space Center and the Air Force Eastern Test Range articies showing evolution of the Air Force Missile Test Center are included.
  • Johnfkennspaccent_120408110048.pdf

    This is primarily the bibliography of an organization located in an area which was once inhabited by more beasts and birds than people. The evolution of the Kennedy Space Center cea be traced from the Army Ballistic Missile Agency and Marshall Space Flight Center, Huntsville, Alabama. That period is fully covered by Historical Origins of NASA's Launch Operations Center to July 1, 1962.
  • Johnfkennmemo_120908091724.pdf

    Memorandum from Wernher von Braun regarding a request made for NASA's cooperation to obtain resources from the Kennedy Memorial Library.
  • J2rockengidata_120408110834.pdf

    A datasheet describing the function of the J-2 rocket engine.
  • j2liqhydrrock_060607141431.pdf

    The 5-2 high-energy liquid propellant rocket engine (~i~. l), a large engine producing 200,000 pounds of thrust at altitude conditions, burns liquid hydrogen and liquid oxygen to produce the necessary high specific impulse for practical space use. Rocketdyne, a Division of North American Aviation, Inc., is developing the engine for the George C. Marshall Space Flight Center, Xfi. The first use of the engine will be in the upper stages of the Saturn vehicles. Five engines will be used for the second, S-I1 stage of the Saturn V, and one will power the S-IVB third stage of the Saturn V and S-ISTI second stage of 'the Saturn IB; Original is a photocopy on onion skin.
  • iusivbforskiorbandtratheana_081707134156.pdf

    This report determines the maximum and minimum solar and terrestrial thermal energy incident and absorbed by Saturn IB/V vehicles in earth orbit and translunar travel. The influence' of this external energy on the Instrument Unit Thermal Conditioning System performance, and consequently its adequacy to maintain the electronic packages at acceptable temperature limits is ascertained. Conclusions are: a) Methanol/water coolant temperature will deviate from 111 specifications only during translunar cold flights. However, adequate thermal conditioning of the electronic equipment would still be maintained. b) Instrument Unit missions exceeding 6 1/2 hours, or electronic packages heat dissipation magnitudes lower than 3 kw or higher than 8.5 kw, should be reviewed to ascertain thermal compatibility.
  • Letttoproflogsfrom92667_121008165048.pdf

    Letter to Professor Logsdon from E. C. Welcsh denying Logsdon's request to quote Wernher von Braun and President Kennedy from their memorandums.
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