UAH Archives, Special Collections, and Digital Initiatives

Browse Items (42 total)

  • usaerospprog_081607135439.pdf

    The document contains four charts labeled "Investigation", "Exploration", "Utilization", and "Control". Each chart is organized chronologically, contains drawings of U.S. Aerospace Program Projects, and incudes written descriptions of each project.
  • tisapollo8.pdf

    This document is prepared jointly by the Marshall Space Flight Center laboratories R-AERO-P, R-ASTR -S, and R-P&VE-VN . The document presents a brief and concise description of the AS-503 Apollo Saturn Space Vehicle. Where necessary, for clarification, additional related information has been included. It is not the intent of this document to completely define the Space Vehicle or its systems and subsystems in detail. The information presented herein, by text and sketches, describes launch preparation activities, launch facilities, and the space vehicle. This information permits the reader to follow the space vehicle sequence of events beginning a few hours prior to liftoff to its journey into space.
  • tofstatsenainvecommdevenikesyst_031607135646.pdf

    Narrative report of general H.N. Toftoy - Informal interview with Mr. Robert E. Dunne, Assistant Counsel of the Senate Permanent Investigating Subcommittee, in the presence of Mr. P. K. Schaeppi.
  • TechinfosummApol_051310121144.pdf

    The document presents a brief and concise description of the AS-505 Apollo Saturn Space Vehicle. Where necessary, for clarification, additional related information has been included.
  • tecinfsumapollo9.pdf

    The document presents a brief and concise description of the Apollo 9 Saturn Space Vehicle.
  • techinsprl10liqhydrrock_041207102029.pdf

    A technician inspects an RLlO liquid hydrogen rocket engine OD the assembly floor. of Pratt & Whitney Aircraft's Florida Research and Development Center. The 115,000-pound-thrust RLlO was designed and developed for the National Aeronautics and Space Administration's Saturn S-IV azld Centaur space vehicles.
  • technforreliability_021808121222.pdf

    Design review is becoming a basic requirement during the design and development of military systems. The main purpose of the design review is to increase the system's inherent and operational reliability. The major portion of this paper is the result of reliability's effort to comply with Paragraph 3.6 of NPC 250-1 Reliability Program Provisions for Space Contractors. The design review to be discussed is a reliability circuit design review with emphasis placed on what should be reviewed and the review techniques employed. The basic circuit design review prerequisites, component parts and their ratings, are discussed at the beginning of this paper. The remainder deals with the organization and reviewing of circuits. The review items include worst-case circuit performance, component applications, failure mode analysis, noise rejection, electrical stress, and the determination of component temperatures. Many examples are included to illustrate how each item was accomplished. This paper is intended not only to give the reliability analyst cognizance of basic design problems and troublesome circuits, but also, to aid him in formulating a design review program.
  • spaceflight_1_2.pdf

    Appears to be a rough dfraft with editorial comments and revision notes. Includes references to figures and tables.; Page 31 is missing. Pages 37 through 44 do not exist; there is a note about this on page 36. Page 67 also does not exist.
  • Selemethforupra_022410132604.pdf

    This paper will discuss selected methods for increasing the Saturn launch vehicle payload capabilities. These methods involve system changes or additions that give large step performance'increases aver those which can be obtained by product improvements. The selected philosophy of approach and the established designed systems wil1,be described, as well as anticipatedsystem concepts that may be used to increase the Saturn vehicles' capabilities.
  • sensofrockengistabtopropfeedsystdyna_040607115532.pdf

    Because of the increased reliability required of rocket systems in their more recently assigned missions, previously acceptable design features must be reappraised ad refined. In the region of rocket engine system stability, the probles is centered in two areas, the combustor and the propellant feed system The principal interest of this paper lies in the coupling that occurs between the feed system and combustion dynamics, often termed a "buzzing" instability then the dymics are characterized by periodic pressure oscillations in the range of 200 to 1000 cps appearing in the combustion chamber and' the feed system.
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