UAH Archives, Special Collections, and Digital Initiatives

Browse Items (970 total)

  • Lettfrmwmet_011508085357.pdf

    Letter stating that "A review of the research origins of the Lance weapon system - Project Hindsight -Task 1 supplement" is inside as requested.
  • spc_stnv_000148.pdf

    Pages 1 and 2 appear to have been cut out of the document. Page 14 is only half a page. Page 40 is repeated but each page has different information.
  • spc_stnv_000111.pdf

    This paper presents a "realistic model of atmospheric properties based on reliable observations and current theories" according to the abstract found on page xv. This 1956 ARDC model was meant to be used as the "basis for engineering and design work performed."
  • Theoliqupropperf1.pdf

    Archive copy is a photocopy.; The purpose of these writings is to compile in one volume the basic elements of thermodynamics and gas dynamics which are useful in the evaluation of thrust chamber performance. It is presumed that the reader will have had an elementary course in thermodynamics and gas dynamics. The discussion of topics useful in evaluating thrust chamber performance is, of necessity, limited to these physical effects amenable to other areas that are as yet in the research stage of development. The author would like to take this opportunity to express his gratitude to Mr. G. S. Gill for many stimulating discussions on this subject. Thanks are due to Mr. D. J. Kuyper for permission to utilize his discussion on elastic-plastic strain and its application to nozzle throat area change. Finally, the author wishes to express his gratitude to his wife, Alice, who typed the bulk of the manuscript.
  • comsysbladurreeoflarveh_031808114618.pdf

    This paper was published in the Proceedings of the IEEE, volume 55, number 5, May 1967.; ABSTRACT: Much of the theoretical research on reentry blackout is in a format difficult for the communications design engineer to use in his system analysis. This paper derives simplified equations for the average sheath power loss that may be added (in dB) to the usual space loss to obtain an approximate total propagation loss. The plasma and sheath properties are discussed in detail but largely without supporting mathematics, in order to give the design engineer a better understanding of the overall problem. For the same reason and to provide insight into the final results, the average radiated power is found, using both intuitive and rigorous techniques. Several graphs of plasma properties are included in the development as an aid to numerical computation, and results are compared with the work of other authors.
  • spc_stnv_000050.pdf

    Paper by J. W. Moore and J. R. Mitchell, Quality & Reliability Assurance Laboratory, Marshall Space Flight Center, and H. H. Trauboth, Computation Laboratory, Marshall Space Flight Center. The paper summary notes, "The advancement of the space age into increasingly complex and ambitious missions requiring the development and operation of more sophisticated and intricate launch vehicles has generated numerous problem areas. The purpose of this paper is to define the Aerospace Vehicle Simulation; discuss the relationship of this simulation to the major problem areas of checkout; describe the development and implementation of this simulation system; indicate multidiscipline applications to present and future programs."
  • Contrforsatuuppe_120108134449.pdf

    Details contracts for upper stages of Saturn IV and Saturn V and includes illustrative appendixes. Archive copy is a photocopy.
  • digsim.pdf.pdf

    The rapid development of computer technology and the creation of new engineering oriented languages has established that general purpose digital computers are now extremely suitable to perform simulation of large scale physical systems. With Aerospace Vehicle Simulation (AVS), an effort has been undertaken at MSFC to simulate continuous and discrete dynamics of an aerospace vehicle and its ground support equipment on a large digital computer. This simulation produces a copy of the physical vehicle configuration and its functions in the form of a large scale mathematical model in the computer. AVS will be an essential part of an integrated information system which can be used by several laboratories and offices at MSFC for the design, checkout, test, and management of aerospace vehicles.
  • satuascephasguidandconttech_040407110521.pdf

    Lunar Missions Meeting, July 17-19, 1962. Focuses on the guidence concept under development at the Marshall Space Flight Center
  • desdevfabric_071107111534.pdf

    For presentation to the Society of Automotive Engineers, 16 September 1964, Boston, Massachusetts. ABSTRACT: This paper discusses the design, development and fabrication of a prototype hydraulic transformer, Hydro-Aire Model No. 05-055, performed in fulfillment of the requirements of Contract No. NAS 8-5264 for NASA Marshall Space Flight Center. The Hydraulic Transformer described is designed to pump hydraulic oil at a flow of 100 GPM with a pressure rise of 4000 psi, and does this work by utilizing as a power source the flow of RP-1 rocket fuel at a pressure of 1900 psig. The Hydraulic Transformer built to handle this combination of flows and pressures, unprecedented in such devices, has a weight of only 70 pounds for the first development model. The development of this unit is discussed and future development improvements are mentioned.

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