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  • THERMODYNAMICS AND COMBUSTION  (1,363)
  • 1970-1974  (1,363)
Collection
Keywords
Years
Year
  • 1
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    Ablator manufacturing (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Studies are being conducted to determine how manufacturing-induced defects affect the performance of ablative heat shields. If commonly occurring defects do not affect material performance, simpler manufacturing techniques can be used, quality control requirements can be relaxed, repair and rework operations can be held to a minimum, and thus the total manufacturing cost can be reduced.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA Space Shuttle Technol. Conf.; p 475-504
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Manufacturing developments in insulation application (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Manufacturing development studies have been conducted to provide information on the fabrication and handling characteristics of a number of candidate multilayer insulation systems. The application of these complex, lightweight insulation systems to large-scale, flight-type cryogenic tankage and other structures has of necessity required the development of new methods, processes, and tooling concepts. Results of some of the studies that have contributed to the advancement of cryogenic technology are presented. The insulation systems that are of primary importance for future application are those using the sliced foam spacers, the net type spacers, the glass fiber paper spacers, and the Superfloc system which consists of tufts of dacron fibers flocked on the surface of the radiation shields.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Cryog. Res. at MSFC: Res. Achievements Rev., Vol. 4, No. 2; p 73-92
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Design for advanced insulation systems (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The design of principal multilayer insulation (MLI) systems being investigated by Marshall Space Flight Center and its contractors for application to flight-type cryogenic tankage for long-term storage in space vehicles is described. The MLI systems were designed for application to a 105 in. diameter cryogenic test tank to simulate full-scale design and installation methods representative of flight-type hardware. The MLI systems selected for design represent systems suitable for use on space vehicles such as the modular nuclear vehicles that require application of thicknesses up to 6 in. The MLI systems are lightweight and structurally efficient.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Cryog. Res. at MSFC: Res. Achievements Rev., Vol. 4, No. 2; p 53-72
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Multilayer high performance insulation materials (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: A number of tests are required to evaluate both multilayer high performance insulation samples and the materials that comprise them. Some of the techniques and tests being employed for these evaluations and some of the results obtained from thermal conductivity tests, outgassing studies, effect of pressure on layer density tests, hypervelocity impact tests, and a multilayer high performance insulation ambient storage program at the Kennedy Space Center are presented.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Cryog. Res. At MSFC: Res. Achievements Rev., Vol. 4, No. 2; p 93-98
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Fire extinguishment in hypobaric and hyperbaric environments (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Work that has been performed to provide information on the effects of various fire extinguishing agents in special atmospheres is discussed. Data used in the development of both equipment and techniques for manned spacecraft and related equipment are discussed. The equipment includes a hypobaric chamber suitable for low pressure use and a hyperbaric chamber for high pressure operation. The effectiveness of agents in weightless environment is also discussed.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Conf. on Mater. for Improved Fire Safety; p 163-169
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    The combustion process (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The effect of thermodynamic, chemical, and physical properties on the combustion of materials is discussed. The mechanisms which produce and support combustion of various materials are examined. The effects of free radical reactions, convection and gravitational effects on combustion rates, and changes in flame propagation due to size and shape of surfaces are described.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Conf. on Mater. for Improved Fire Safety; p 3-7
    Format: text
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  • 7
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    Conditions for local thermodynamic equilibrium in uranium (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Model for calculation of parameters for local thermodynamic equilibrium in uranium
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: FLORIDA UNIV. RES. ON URANIUM PLASMAS AND THEIR TECHNOL. APPL. 1971; P 173-178
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Thermal design of a satellite telescope (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Thermal control techniques in designing large orbiting telescopes
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA, WASHINGTON OPT. TELESCOPE TECHNOL. 1970; P 359-379
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Thermodynamics of the internal combustion engine (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Pollution aspects of internal combustion engine thermodynamics
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ET. AND THERMODYN. IN HIGH TEMP. GASES 1970; P 31-40
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Rocket combustion instability suppression with cavity resonators (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Properly tuned Helmholtz resonator damping devices are an effective method for eliminating high frequency combustion instability in rocket engine thrust chambers. A program was implemented with the objective of extending Helmholtz resonator theory to thrust chamber conditions to establish a standard design procedure. By using systematic cold-flow testing and hot firings, empirical design equations were formulated. An effort is currently underway to extend the design theory to other types of acoustical damping devices such as quarter-wave tubes and slots.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Res. Achievements Rev., Vol. 4, No. 6; p 53-59
    Format: text
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