UAH Archives, Special Collections, and Digital Initiatives

Browse Items (716 total)

  • Satuvmissalab_080707155420.pdf

    Speech that covers the topics of the Saturn V lunar mission and the basics of a lunar mission in general.
  • Memorecomeet_121907142059.pdf

    Memorandum to go over problems with the H-1 engine.
  • Mastplanfordocu.pdf

    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.
  • 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.
  • Sa-203.pdf.pdf

    The "Saturn Technical Information Handbook" provides up-to-date reference material to the Launch Operations Center personnel. This material shows the assembly and operation of the Saturn Vehicle components for systems analysis.; Volume II is available on the NASA Technical Reports Server (NTRS) as a PDF.
  • comparadvcoolingtech_071207135801.pdf

    The document is a technical paper for Astronautics and Aerospace Engineering Magazine.The copy has handwritten notes that appear to be for revisions. The abstract states "In the early days of rocket propulsion, two primary methods were employed for cooling the walls of thrust chambers. These were uncooled metal chambers where the heat sink capacity of the chamber and nozzle wall materials limited the operating duration, and regeneratively cooled chambers where one of the propellants was circulated in a cooling jacket which constituted the chamber wall. Today, there are at least fourteen different methods with variations for cooling the combustion devices and nozzles of liquid propellant, solid propellant, and/or nuclear rocket propulsion engines. It is the intent of this paper to examine these methods, to describe for each the useful range of operating conditions, as well as present and likely future applications, to define their limitations and associated problems. Emphasis is primarily placed on liquid rocket engines."
  • Rockengiselecrit_042908141859.pdf

    This paper considers many of the factors and criteria which have to be considered and evaluated when selecting a specific rocket engine for a given vehicle application. The lists of criteria can be helpful as checklists in design and systems engineering of a rocket propulsion device. About ten different applications are examined to illustrate the relative importance of some of these selection criteria. There will be groupings of our major types of criteria; namely, performance, operational, economic and so-called judgment criteria. In many cases the last three categories are equally or more important than the performance criteria in selecting one of several rocket engines for a specific application. The actual selection usually is a compromise to make the rocket engine responsive to several important criteria.
  • compflowcont.pdf.pdf

    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 .
  • spacfligprojtodaandtomo_032207104326.pdf

    NASA symposium on scientific and technical Information.
  • 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.
  • Lettmrgeorgemlow_120208120312.pdf

    Letter to George M. Lowe and Joseph F. Shea from H.A. Storms president continuing a conversation that was left unfinished.
  • reliasseliqurockengi_062107153119.pdf

    Proposed for the 10th National Symposium on Reliability & Quality Control. This paper will deal with various techniques of treatment of such data and associated graphic displays.
  • Reliqualmana_080707155107.pdf

    The role of Reliability and Quality in NASA program management is well defined by the NPC 200 series and complimentary procurement regulations.
  • relipictmsfcphilstaffmgmt_031907142349.pdf

    Document that discusses the importance of reliability in engineering.
  • P16608~1.PDF

    A letter to Jame E. Webb proposing that the first LEM that lands on the moon to be named after President Kennedy."
  • statsmodforsaturn_012508122337.pdf

    This report presents the logic leading to a mathematical expression for mission availability. Mission availability is treated as the probability that the cumulative downtime occurring during a mission of given length will be less than the time constraint. This is opposed to more general approaches such as steady state or instantaneous availability or operating time versus real time. We intend to present a practical and usable mathematical model by deduction and demonstration. The development is based on exponentially distributed downtimes. Experience shows that certain systems follow exponential downtime distributions except near zero. This error is often so small that it may be neglected. A future report will present a downtime distribution which will account for this small error.
  • TVsystapoltele_111307142704.pdf

    Focuses on the construction and future use of the Apollo space telescope. The components described in this paper except for those listed otherwise were designed by the Space Support Division of Sperry Rand Corporation to specifications established by NASA's Marshall Space Flight Center in Huntsville, Alabama. Appreciation is extended to MSFC for permission to publish this paper and for data and help provided for its preparation.
  • Sperrandmontprog_092910151001.pdf

    The following pages contain reports for each of the individual contract appendices covering technical progress and accomplishments, related problems, and staffing progress. The report of manhours expended against each appendix by schedule order is being submitted as a part of the financial management report.
  • earorbworkcapbrochA_021110095433.pdf.pdf

    A brochure designed to depict a competence and capability in the area of large earth-orbital workshops.
  • enggcappresentation.pdf.pdf

    This Engineering Capabilities Presentation lists the competence and capability that has been demonstrated by the Space Support Division of Sperry Rand Corporation while fulfilling contractual commitments in the aerospace industry. This is a preliminary presentation; the preparation of a complete capabilities history of the division is currently in the developmental stage. The Capabilities Experience Summary is comprised of ten categories. e.g. Category 1 - Aeronautics, etc. The capabilities reported herein were performed by the Space Support Division under Contract NAS8-20055 to the National Aeronautics and Space Administration, George C. Marshall Flight Center, Astrionics Laboratory, Huntsville, Alabama.
  • SaturnIBSA217_052008142122.pdf

    This document contains a definition of a reference Saturn IB launch vehicle designated SA-217. The Saturn IB SA-217 is a projected reference vehicle, based on Saturn IB SA-212, incorporating the latest proposed product improvements. The two-stage payload capability of this vehicle to a 100-nautical-mile circular orbit is 44,965 pounds. The Saturn IB SA-217 launch vehicle is to be used as the baseline vehicle for advanced studies requiring the use of the standard or modified Saturn IB launch vehicle. This vehicle definition does not necessarily represent approved changes to any specific vehicle. This document supersedes the Saturn IB SA-213 reference Launch Vehicle, described in memorandum R-P&VE-DIR-65-92.
  • memoinditomsfccircandmsfcadmireguandprocchiemanaservoffims-ch_112607141847.pdf

    Memorandum regarding indices ready for reference and filing.
  • Intewithdrwerh52564_121008163244.pdf

    Transcription of an interview with Wernher von Braun and Mr. Sohier.
  • Letttodrwern31464_120908091357.pdf

    Archive copy is a poor photocopy. Unable to read.
  • Fabrsatus-icboos_081407122702.pdf

    AIAA Second Annual Meeting, San Francisco, California. Discusses the fabrication process of the Saturn S-IC booster.
  • facidesihandliqhyd_051107104601.pdf

    Presented to German Society for Rocket Technology & Astronautics.Essay discussing the capabilities of liquid hydrogen as fuel.
  • pracautomanufcheck_051107090838.pdf

    This paper presents a number of solutions to a number of unanswered questions regarding the Saturn projects.
  • TechProbOnBo_062408092345.pdf

    For the purposes of this paper, an onboard checkout system is defined as a system which is built into prime flight equipment, flies with it, and permits a checkout capability to exist during all the major phases of the test and mission life of that prime equipment. Varying degrees of capability may exist in such a system, depending on what is designed into it. This, in turn, is generally dependant on life and mission requirements of the prime equipment, degree of mission checkout required, reliability restrictions,redundancy levels, data management scheme, and equally important, state of the art . Not all checkout can be accomplished with onboard equipment. Mechanical system problems such as leak detection, for example, require techniques that cannot be remotely controlled and evaluated today. On the other hand, such things as in-flight telemetry have been used for quite a long time and will continue to be used for onboard checkout.
  • histrockdevsm.pdf

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

    Copy No. 026. Ger-10866.
  • iupresdedi_080207152456.pdf

    This is a note book that contains newspaper articles and photographs about the new IBM building in Huntsville, Alabama. It also has information about the Instrument Unit for the first Saturn IB flight. There is also information about the Saturn IB Instrument Unit being barged to Kennedy Space Center.; There are 2 pages that list the articles with the title, newspaper name, writer and date.; There are six color photographs that show the dedication of the IBM building and the Instrument Unit. One photograph has Dr. Wernher von Braun standing behind the ring. Two of the photographs show the Instrument Unit on a trailer being pulled by a truck.; Preferred Citation: [Identification of item] Saturn V Collection, Dept. of Archives/Special Collections, M. Louis Salmon Library, University of Alabama in Huntsville, Huntsville, AL.
  • Roleofvonbraulett_121108095421.pdf

    Memorandum from NASA Chief of Public Affairs to Eugine M. Emme. States that a video from Wernher von Braun are included regarding his views on the NASA program.
  • TechsurvABMA_111808164326.pdf

    Handwritten notes on the document.; Archive copy is a poor photocopy.
  • scanstich_072210162848.jpg

    News article that details the creation and function of a lunar module or "moon bug" created by Wernher von Braun.
  • Vonbraumoveende_072910160005.pdf

    The Huntsville Times
  • manpofacmakfut_021208085025.pdf

    This paper presents in synoptic form, an analysis of the management problems being faced in making fuhlre manned spaceflight decisions. It is an attempt to view the manned space program in total perspective - its relationship to other scientific research, other national programs, the role of Congress, the President's role, industry's role, and then show their relative influence and impact on decisior, making for the Post-Apollo period.
  • Faciengi_121508155406.pdf

    Article makes references to a film. Centers around the idea that testing space vehicles extensively before launch is cost control.
  • counlift_080607123539.pdf

    This is an article from the Boeing Magazine. The Archive copy is a very poor photocopy and is difficult to read.; About the time the S-IC-1 booster is lifting the first Apollo/Saturn V from the launch pad on its maiden unmanned flight next year, a Boeing systems test crew will begin static testing the S-IC-4 at Devils Swamp, Mississippi (MTF). Starting with S-IC-4, all Saturn V first stage boosters will be captive fired at MTF. At present, S-IC firings are conducted by MSFC's test laboratory at Huntsville. The first flight stage, the S-IC-1, was placed in the static test stand on 24 January 1966 and completed its test program 25 Feb. It was removed from the stand March 14 and is undergoing post-firing checkout. it is due to be shipped this summer to KSC where it will be mated to the two upper stages of Saturn V, the IU and Dummy Apollo payload. The S-IC-2 went into the static stand on March 22 and is being tested during April The S-IC-3 also will be tested at Huntsville in 1966. The job of putting the world's largest and most powerful rocket together will be accomplished in the world's largest building, the 52-story vehicle assembly building.
  • SatVsemAnRep_030308102345.pdf

    MA-001-00202H.; MPR-SAT V 66-3.; ABSTRACT: This Saturn V Semi-Annual Progress report describes progress and major achievements from July 1, 1966, through December 31, 1966, in the Saturn V Program.
  • manwelcon_060707141124.pdf

    Paper given at the American Ordnance Association Welding Section Panel. Focuses on the process of welding and development programs.
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