Browse Items (47 total)

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  "Conditions contributing to stress corrosion [list] photograph."

  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."
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  Double seal insulation [drawing] photograph.

  8 x 10 inch black and white photograph.; Drawing contains information about the modified epoxy adhesive, aluminum film, mylar film, perforated phenolic honeycomb core, tank skin, mylar honeycomb core, polyurethane adhesive, weight and thermal conductivity.; Photo negative no. 651746 M-268.
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  F-1 engine photograph.

  8 x 10 inch black and white photograph. Engine parts are labeled.
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  "Pratt & Whitney Aircraft RL10 liquid hydrogen rocket engine"

  Photograph of a Pratt & Whitney rocket engine.
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  "The Common Bulkhead for the Saturn S-II Vehicle: Unique Manufacturing Effort Adds to Space-Age Hardware Technology".

  Presentation regarding the construction of Apollo and Saturn rockets.
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  Combustion Oscillations in F-1 Engine.

  The set of documents includes an introductory letter written by D. Brainerd Holmes and Tischler's report with the subject "F-1 Combustion Instability Report for Associate Administrator; Period March-April, 1963".
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  "Development of the Saturn S-IV and S-IVB Liquid Hydrogen Tank Internal Insulation."

  In April of 1960 the Douglas Aircraft Company was awarded a contract to develop the second and uppermost stage for the Saturn I space booster. In order to realize the high specific impulse available, this stage, called the S-IV, was to utilize liquid hydrogen and liquid oxygen as the propellants. After burn-out of the first stage, the S-IV Stage was to ignite its engines at an altitude of approximately 200,000 feet, burn for approximately 8 minutes, and inject a 20,000 lb spacecraft into a low earth orbit. This program represented Douglas's first major endeavor with liquid hydrogen. It was necessary to develop an insulation for the S-IV Stage that was capable of withstanding the thermal shock associated with loading, could provide adequate insulative properties to limit the flow of heat into the hydrogen, and was of minimum weight. This latter fact cannot be over emphasized because every extra pound of insulation is one less pound of available payload weight.
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  Development of LOX/RP-1 engines for Saturn/Apollo launch vehicles.

  The development of liquid rocket engines follow similar patterns regardless of engine size. During the development of the H-1 and F-1 engines, may problems were encountered. Mehtods of solving the combustion instability problem are discussed.; AIAA 4th Propulsion Joint Specialist Conference, Cleveland, Ohio, June 10-14, 1968.; Also available on NASA Technical Reports Server (NTRS) as unclassified. Can be ordered. Also on AIAA.
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  "Development of LOX/RP-1 Engines for Saturn/Apollo Launch Vehicles."

  The development of liquid rocket engines follow similar patterns regardless of engine size. During the development of the H-1 and F-1 engines, many problems were encountered. Methods of solving the combustion instability problem are discussed. A description is given of the major components of each engine, outlining their unique features. The requirements for an insulation cocoon are discussed. Problems associated with materials substitution are provided; also highlighted is the fact that problems occur after engine deliveries and require continued development support. Safety features incorporated on the engines are mentioned. Solution to problems encountered in flight are discussed. Upratings of both engines systems are presented graphically.; On the NASA Technical Reports Server (NTRS) unclassified. Can also be found on AIAA.
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  "Development of LOX-Hydrogen Engines for the Saturn Apollo Launch Vehicles."

  During the development of the RL-10 and J-2 engines, many problems were encountered. Solutions to the significant problems are contained. A description of these LOX-Hydrogen engines, outlining the unique features of each will be given. Performance parameters for both engine systems are tabulated. Specific applications to various stages are shown.