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  • PROPULSION SYSTEMS  (1,456)
  • THERMODYNAMICS AND COMBUSTION  (1,363)
  • 1970-1974  (2,819)
Collection
Keywords
Years
Year
  • 1
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    Design of Liquid Propellant Rocket Engines Second Edition (1971)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Liquid propellant rocket engine conference proceedings and parameters for design of rocket engines and systems
    Keywords: PROPULSION SYSTEMS
    Type: NASA-SP-125
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 2
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    Heat Transfer and Thermodynamics: a Compilation (1974)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A compilation is presented for the dissemination of information on technological developments which have potential utility outside the aerospace and nuclear communities. Studies include theories and mechanical considerations in the transfer of heat and the thermodynamic properties of matter and the causes and effects of certain interactions.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-SP-5959(01)
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Launching of SERT 2 (1970)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: In-orbit performance tests of ion engines and exhaust effects on SERT 2 equipment
    Keywords: PROPULSION SYSTEMS
    Type: NASA-NEWS-RELEASE-70-8
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Thermal insulation - A compilation (1970)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Thermal insulation materials and techniques for high temperature and cryogenic environments - technology utilization
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-SP-5930/01/
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Turbofan engine for shuttle (1970)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: Air breathing engines for space shuttle reentry
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-66716
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 6
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    Liquid rocket pressure regulators, relief valves, check valves, burst disks, and explosive valves (1973)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: The development of and operational programs for effective use in design are presented for liquid rocket pressure regulators, relief valves, check valves, burst disks, and explosive valves. A review of the total design problem is presented, and design elements are identified which are involved in successful design. Current technology pertaining to these elements is also described. Design criteria are presented which state what rule or standard must be imposed on each essential design element to assure successful design. These criteria serve as a checklist of rules for a project manager to use in guiding a design or in assessing its adequacy. Recommended practices are included which state how to satisfy each of the criteria.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-SP-8080
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 7
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    Solid Rocket Motor Performance Analysis and Prediction (1971)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: Current design practices are reviewed and assessed, and guidance is established for achieving greater consistency in design, reliability in the end product, and efficiency in the design effort. The total problem is discussed, and design elements involved in successful design are identified. Design criteria are described, and the rule, guide, limitation, or standard which must be imposed on each essential design element is given. Recommended practices are presented for satisfying each of the criteria.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-SP-8039
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Thermal-Structural Evaluation of TD Ni-20Cr Thermal Protection System Panels (1974)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: The results of a thermal-structural test program to verify the performance of a metallic/radiative Thermal Protection System (TPS) under reentry conditions are presented. This TPS panel is suitable for multiple reentry, high L/D space vehicles, such as the NASA space shuttle, having surface temperatures up to 1200 C (2200 F). The TPS panel tested consists of a corrugation-stiffened, beaded-skin TD Ni-20Cr metallic heat shield backed by a flexible fibrous quartz and radiative shield insulative system. Test conditions simulated the critical heating and aerodynamic pressure environments expected during 100 repeated missions of a reentry vehicle. Temperatures were measured during each reentry cycle; heat-shield flatness surveys to measure permanent set of the metallic components were made every 10 cycles. The TPS panel, in spite of localized surface failures, performed its designated function.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-132487
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    On the Design and Test of a Liquid Injection Electric Thruster (1973)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: A liquid injection electric thruster (LINJET) was designed and tested. The results of the tests were very encouraging with thruster performance levels well in excess of design goals. Supporting activities to the engine design and test included a five-million pulse life test on the main capacitor, a 46-million pulse test on the trigger electronics, design and fabrication of a zero resistance torque connector for use with the torsional pendulum thrust stand, design and fabrication of a logic box for control of engine firing, and a physical and chemical properties characterization of the perfluorocarbon propellant. While the results were encouraging, testing was limited, as many problems existed with the design. The most significant problem was involved with excessive propellant flow which contributed to false triggering and shorting. Low power active thermal control of the propellant storage cavity, coupled with a re-evaluation of the injection ring pore size and area exposed to the main capacitor discharge are areas that should be investigated should this design be carried forward.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-132316
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 10
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    Aircraft Engine Sump Fire Mitigation (1973)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: An investigation was performed of the conditions in which fires can result and be controlled within the bearing sump simulating that of a gas turbine engine; Esso 4040 Turbo Oil, Mobil Jet 2, and Monsanto MCS-2931 lubricants were used. Control variables include the oil inlet temperature, bearing temperature, oil inlet and scavenge rates, hot air inlet temperature and flow rate, and internal sump baffling. In addition to attempting spontaneous combustion, an electric spark and a rub (friction) mechanism were employed to ignite fires. Spontaneous combustion was not obtained; however, fires were readily ignited with the electric spark while using each of the three test lubricants. Fires were also ignited using the rub mechanism with the only test lubricant evaluated, Esso 4040. Major parameters controlling ignitions were: Sump configuration; Bearing and oil temperatures, hot air temperature and flow and bearing speed. Rubbing between stationary parts and rotating parts (eg. labyrinth seal and mating rub strip) is a very potent fire source suggesting that observed accidental fires in gas turbine sumps may well arise from this cause.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-121158 , AL73T007
    Format: application/pdf
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