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  • PROPULSION SYSTEMS  (296)
  • THERMODYNAMICS AND COMBUSTION  (231)
  • 1970-1974  (527)
  • 1935-1939
Collection
Keywords
Years
Year
  • 1
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    Space shuttle auxiliary propulsion system design study. Phase C and E report: Storable propellants, RCS/OMS/APU integration study (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Auxiliary propulsion concepts for application to the space shuttle are compared. Both monopropellant and bipropellant earth storable reaction control systems were evaluated. The fundamental concepts evaluated were: (1) monopropellant and bipropellant systems installed integrally within the vehicle, (2) fuel systems installed modularly in nose and wing tip pods, and (3) fuel systems installed modularly in nose and fuselage pods. Numerous design variations within these three concepts were evaluated. The system design analysis and methods for implementing each of the concepts are reported.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-128819 , MDC-E0708 , MSC-04423-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Development and in-flight performance of the Mariner 9 spacecraft propulsion system (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: On November 14, 1971, Mariner 9 was decelerated into orbit about Mars by a 1334-newton (300-lbf) liquid bipropellant propulsion system. The development and in-flight performance are described and summarized of this pressure-fed, nitrogen tetroxide/monomethyl hydrazine bipropellant system. The design of all Mariner propulsion subsystems has been predicated upon the premise that simplicity of approach, coupled with thorough qualification and margin-limits testing, is the key to cost-effective reliability. The qualification test program and analytical modeling of the Mariner 9 subsystem are discussed. Since the propulsion subsystem is modular in nature, it was completely checked, serviced, and tested independent of the spacecraft. Proper prediction of in-flight performance required the development of three significant modeling tools to predict and account for nitrogen saturation of the propellant during the six-month coast period and to predict and statistically analyze in-flight data. The flight performance of the subsystem was excellent, as were the performance prediction correlations. These correlations are presented.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-129097 , JPL-TM-33-574
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Stagnation region heating of a phenolic-nylon ablator during return from planetary missions (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of a stagnation-line analysis of the radiative heating of a phenolic-nylon ablator are reported. The analysis includes flowfield coupling with the ablator surface, equilibrium chemistry, multicomponent or binary diffusion and a coupled line and continuum radiation calculations. Users manual and operating instructions for the computer programs listed in the report are included.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-112026
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Study of casing treatment stall margin improvement phenomena (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of a program of experimental and analytical research in casing treatments over axial compressor rotor blade tips are presented. Circumferential groove, axial-skewed slot, and blade angle slot treatments were tested. These yielded, for reduction in stalling flow and loss in peak efficiency, 5.8% and 0 points, 15.3% and 2.0 points, and 15.0% and 1.2 points, respectively. These values are consistent with other experience. The favorable stalling flow situations correlated well with observations of higher-then-normal surface pressures on the rotor blade pressure surfaces in the tip region, and with increased maximum diffusions on the suction surfaces. Annular wall pressure gradients, especially in the 50-75% chord region, are also increased and blade surface pressure loadings are shifted toward the trailing edge for treated configurations. Rotor blade wakes may be somewhat thinner in the presence of good treatments, particularly under operating conditions close to the baseline stall.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-134552 , R73AEG326
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Operating manual for coaxial injection combustion model (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An operating manual for the coaxial injection combustion model (CICM) is presented as the final report for an eleven month effort designed to provide improvement, to verify, and to document the comprehensive computer program for analyzing the performance of thrust chamber operation with gas/liquid coaxial jet injection. The effort culminated in delivery of an operation FORTRAN IV computer program and associated documentation pertaining to the combustion conditions in the space shuttle main engine. The computer program is structured for compatibility with the standardized Joint Army-Navy-NASA-Air Force (JANNAF) performance evaluation procedure. Use of the CICM in conjunction with the JANNAF procedure allows the analysis of engine systems using coaxial gas/liquid injection.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-129031
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Formulation, derivation and development of the analysis of the interaction of ablating protection systems and stagnation region heating (1970)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Conservation equations for analysis of interaction of ablating protection systems and stagnation region heating
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-66931 , NASA-RFL-TR-70-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Experimental and theoretical aerodynamic heating and flow field analysis of a space shuttle orbiter (1972)
    In:  CASI
    Details
    Publication Date: 2006-07-18
    Description: The results of work on the McDonnell Douglas delta wing orbiter are summarized and compared to other data and theories where applicable. The tests were conducted in the continuous hypersonic Tunnel B at Mach 8 and in the hypervelocity hotshot Tunnel F at Mach 10.5. Photographic data are used to illustrate the regions of peak heating on the lee-side and to show the vortical nature of the flow. Windward centerline data include measurements of shock angle, surface pressure, flow field pitot pressure and total temperature, and heat transfer rate coefficient distributions. Shock angles, surface pressures, and local Mach number distributions are compared with tangent cone theory over an angle of attack range from 10 to 60 deg. The measured heat transfer rate coefficient distributions are compared to both laminar and turbulent theories and boundary layer transition data are compared to the McDonnell Douglas criteria.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 261-296
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Mariner 9 propulsion subsystem performance during interplanetary cruise and Mars orbit insertion (1972)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: On 14 November 1971 the Mariner 9 1334-N-(300-lbf)-thrust rocket engine was fired for just over 15 min to place the first man-made satellite into orbit about Mars. Propulsion subsystem data gathered during the 5-month interplanetary cruise and orbit insertion are of significance to future missions of this type. Specific results related to performance predictability, zero g heat transfer, and nitrogen permeation, diffusion, and solubility values are presented.
    Keywords: PROPULSION SYSTEMS
    Type: JPL Quarterly Tech. Rev., Vol. 2, No. 1; p 113-122
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    V/STOL propulsion (1971)
    In:  CASI
    Details
    Publication Date: 2006-04-20
    Description: Propulsion technology for STOL and V/STOL commercial aircraft
    Keywords: PROPULSION SYSTEMS
    Type: AIRCRAFT PROPULSION 1971; P 135-168
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Development status of reusable nonmetallic thermal protection (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Development of reusable oxidation resistant carbon-carbon laminates and surface insulation materials for thermal protection systems
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 2 APR. 1971; P 1-38
    Format: text
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    NASA TECHNICAL REPORTS
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