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  • SPACE VEHICLES  (69)
  • THERMODYNAMICS AND COMBUSTION  (41)
  • ASTROPHYSICS
  • 1970-1974  (110)
  • 1973  (110)
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  • 1970-1974  (110)
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  • 1
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    A hydrogen energy carrier. Volume 2: Systems analysis (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A systems analysis of hydrogen as an energy carrier in the United States indicated that it is feasible to use hydrogen in all energy use areas, except some types of transportation. These use areas are industrial, residential and commercial, and electric power generation. Saturation concept and conservation concept forecasts of future total energy demands were made. Projected costs of producing hydrogen from coal or from nuclear heat combined with thermochemical decomposition of water are in the range $1.00 to $1.50 per million Btu of hydrogen produced. Other methods are estimated to be more costly. The use of hydrogen as a fuel will require the development of large-scale transmission and storage systems. A pipeline system similar to the existing natural gas pipeline system appears practical, if design factors are included to avoid hydrogen environment embrittlement of pipeline metals. Conclusions from the examination of the safety, legal, environmental, economic, political and societal aspects of hydrogen fuel are that a hydrogen energy carrier system would be compatible with American values and the existing energy system.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-134176
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    A hydrogen energy carrier. Volume 1: Summary (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The production, technology, transportation, and implementation of hydrogen into the energy system are discussed along with the fossil fuel cycle, hydrogen fuel cycle, and the demands for energy. The cost of hydrogen production by coal gasification; electrolysis by nuclear energy, and solar energy are presented. The legal aspects of a hydrogen economy are also discussed.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-134175
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Simultaneous control of temperature and humidity in a confined space. I - Mathematical modeling of the dynamic behavior of temperature and humidity in a confined space. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Building Science; 8; 1973
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Thermodynamic and transport properties of gaseous tetrafluoromethane in chemical equilibrium (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Equations and in computer code are presented for the thermodynamic and transport properties of gaseous, undissociated tetrafluoromethane (CF4) in chemical equilibrium. The computer code calculates the thermodynamic and transport properties of CF4 when given any two of five thermodynamic variables (entropy, temperature, volume, pressure, and enthalpy). Equilibrium thermodynamic and transport property data are tabulated and pressure-enthalpy diagrams are presented.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TN-D-7181 , L-8483
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    A nonlinear programming approach for optimizing two-stage lifting vehicle ascent to orbit (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: An optimal atmospheric flight branched trajectory-shaping capability is presented based on the Davidon-Fletcher-Powell variable metric parameter optimization technique. Gradient information is generated using finite difference methods. A typical atmospheric flight branched optimization problem is analyzed which requires the determination of 31 parameters. This parameter set includes the three-dimensional description of vehicle attitude control angles for three branches of flight: first-stage ascent, second-stage ascent, and first-stage flyback. The important inflight inequality contraints required to maintain the integrity of the vehicles are considered. Some of the numerical methods employed are discussed, along with several new auxiliary techniques developed to improve the compatibility of the numerical gradient and iterator.
    Keywords: SPACE VEHICLES
    Type: Automatica; 9; Nov. 197
    Format: text
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  • 6
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    Development of a direct condensing radiator for use in a spacecraft vapor compression refrigeration system. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Keywords: SPACE VEHICLES
    Type: ASME PAPER 73-ENAS-5 , Intersociety Conference on Environmental Systems; Jul 16, 1973 - Jul 19, 1973; San Diego, CA; US
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Design, capability, and cost of a Versatile Upper Stage /VUS/ family of vehicles. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Trade-off studies and a preliminary design were accomplished to investigate the Versatile Upper Stage (VUS) concept. This concept entails the development by one contractor of a family of stages with a great deal of commonality to perform a spectrum of potential unmanned automated missions planned through 1990. The trade studies and analyses revealed areas where the penalty for commonality between stages was excessive in weight and performance loss. This occurred in the selection of the vehicle structural shell. In many of the expensive subsystems, especially astrionics, it was found that establishing the requirements for all family members and the application of commonality in subsystem selection could result in significant savings.
    Keywords: SPACE VEHICLES
    Type: AIAA PAPER 73-589 , Joint Space Mission Planning and Execution Meeting; Jul 10, 1973 - Jul 12, 1973; Denver, CO
    Format: text
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  • 8
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    Inflight thermodynamic properties (1973)
    In:  CASI
    Details
    Publication Date: 2006-04-02
    Description: The inflight thermodynamic parameters (temperature, pressure, and density) of the atmosphere are presented. Mean and extreme values of the thermodynamic parameters given here can be used in application of many aerospace problems, such as: (1) research and planning and engineering design of remote earth sensing systems; (2) vehicle design and development; and (3) vehicle trajectory analysis, dealing with vehicle thrust, dynamic pressure, aerodynamic drag, aerodynamic heating, vibration, structural and guidance limitations, and reentry analysis. Atmospheric density plays a very important role in most of the above problems. A subsection on reentry is presented, giving atmospheric models to be used for reentry heating, trajectory, etc., analysis.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Terrest. Environ. (Climatic) Criteria Guidelines for Use in Aerospace Vehicle Develop., 1973 Rev.; 34 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    The cylindrical electrostatic probes for Atmosphere Explorer -C, -D, and -E. (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: This paper briefly describes the cylindrical electrostatic probes to be used on the new Atmosphere Explorer-C, -D, and -E, and outlines the methods to be employed to analyze the experimental data in terms of electron temperature and ion and electron concentration. Two independent cylindrical sensors and partially redundant electronic systems permit greater reliability in measurements. Measurements are made at 1-sec and 2-sec intervals along the orbit. The sensors themselves have been modified from previous applications to cope with the lower electron temperature expected in these low-altitude orbits and to counter possible surface contamination caused by the hydrazine engines used for orbit adjustments.
    Keywords: SPACE VEHICLES
    Type: Radio Science; 8; Apr. 197
    Format: text
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  • 10
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    Effect of surface catalytic activity on stagnation heat-transfer rates. (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: An experiment was made to determine the effect heterogeneous catalytic surface reactions have on heat-transfer rates in highly frozen low-density stagnation-point boundary layers. Data were obtained in arc-heated facilities that were capable of producing large percentages of chemical energy frozen in a supersonic freestream. The heat-transfer rate to a silicon-dioxide surface was reduced to a minimum value of only one-third of the value obtained on relatively active nickel and platinum surfaces. This is the result of its low catalytic efficiency. Ionization energy was recovered on both the active and the inactive surfaces, indicating that this energy either was released many times faster than the recombination energy or was not controlled by the surface composition.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA Journal; 11; May 1973
    Format: text
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