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  • SPACECRAFT PROPULSION AND POWER  (18)
  • Aerodynamics; Spacecraft Design, Testing and Performance  (1)
  • 1
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    ASRM radiation and flowfield prediction status (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Existing and proposed methods for the prediction of plume radiation are discussed in terms of their application to the NASA Advanced Solid Rocket Motor (ASRM) and Space Shuttle Main Engine (SSME) projects. Extrapolations of the Solid Rocket Motor (SRM) are discussed with respect to preliminary predictions of the primary and secondary radiation environments. The methodology for radiation and initial plume property predictions are set forth, including a new code for scattering media and independent secondary source models based on flight data. The Monte Carlo code employs a reverse-evaluation approach which traces rays back to their point of absorption in the plume. The SRM sea-level plume model is modified to account for the increased radiation in the ASRM plume due to the ASRM's propellant chemistry. The ASRM cycle-1 environment predictions are shown to identify a potential reason for the shutdown spike identified with pre-SRM staging.
    Keywords: SPACECRAFT PROPULSION AND POWER
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    NASA TECHNICAL REPORTS
  • 2
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    SSME main combustion chamber and nozzle flowfield analysis (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation is presented of the computational fluid dynamics (CFD) tools which would accurately analyze main combustion chamber and nozzle flow. The importance of combustion phenomena and local variations in mixture ratio are fully appreciated; however, the computational aspects of the gas dynamics involved were the sole issues addressed. The CFD analyses made are first compared with conventional nozzle analyses to determine the accuracy for steady flows, and then transient analyses are discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-178893 , NAS 1.26:178893 , CI-FR-0085
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    NASA TECHNICAL REPORTS
  • 3
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    Improvements in rocket engine nozzle and high altitude plume computations (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The characteristics of rocket exhaust flow fields are very complex, and many phenomena are involved. Previously, it was necessary to use a multitude of codes to treat a nozzle/plume flow in detail. In connection with both computational and economic standpoints, however, it is desirable to have a single code which can treat all the dominant phenomena in a rocket nozzle/plume flow field. The present investigation has the objective to describe a nozzle plume flowfield code which has capabilities that do not presently exist in a single computer code. The RAMP code considered by Penny et al. (1976) was used as a basis in the development of the new code. The basic RAMP employs modular construction and provides a two-phase, reacting gas, supersonic inviscid nozzle/plume solution. Other capabilities needed, which in most cases already exist in other computer codes, were incorporated into the RAMP code to enhance its usefulness. Attention is given to results of plume calculations for bipropellant and solid propellant motors.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 83-1547
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    NASA TECHNICAL REPORTS
  • 4
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    High altitude chemically reacting gas particle mixtures. Volume 2: Program manual for RAMP2 (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: All of the elements used in the Reacting and Multi-Phase (RAMP2) computer code are described in detail. The code can be used to model the dominant phenomena which affect the prediction of liquid and solid rocket nozzle and orbital plume flow fields.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-171827 , NAS 1.26:171827 , LMSC-HREC-TR-D867400-2-VOL-2
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  • 5
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    High altitude chemically reacting gas particle mixtures. Volume 1: A theoretical analysis and development of the numerical solution (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The overall contractual effort and the theory and numerical solution for the Reacting and Multi-Phase (RAMP2) computer code are described. The code can be used to model the dominant phenomena which affect the prediction of liquid and solid rocket nozzle and orbital plume flow fields. Fundamental equations for steady flow of reacting gas-particle mixtures, method of characteristics, mesh point construction, and numerical integration of the conservation equations are considered herein.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-171826 , NAS 1.26:171826 , LMSC-HREC-TR-D867400-1-VOL-1
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    NASA TECHNICAL REPORTS
  • 6
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    Liquid Booster Module (LBM) plume flowfield model (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A complete definition of the LBM plume is important for many Shuttle design criteria. The exhaust plume shape has a significant effect on the vehicle base pressure. The LBM definition is also important to the Shuttle base heating, aerodynamics and the influence of the exhaust plume on the launch stand and environment. For these reasons a knowledge of the LBM plume characteristics is necessary. A definition of the sea level LBM plume as well as at several points along the Shuttle trajectory to LBM, burnout is presented.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-161646 , LMSC-HREC-TR-D784066
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  • 7
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    Summary of solid rocket motor plume flow field and radiation analyses (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The inclusion of solid propellant plume flow field effects in analyses and design of the space vehicle was investigated. Results of these analyses are summarized.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-161456 , LMSC-HREC-TR-D697900
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  • 8
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    Summary of nozzle-exhaust plume flowfield analyses performed in support of space shuttle applications (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Results are summarized of various analyses of the exhaust plumes of the space shuttle. Specific topics discussed included: the development of the two-phase plume flow field model, including finite rate chemistry and free molecular effects; analyses of exhaust plume simulation studies; verification of the analytical two-phase plume flow field model; and complete documentation of the two-phase plume computer code.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-147529 , LMSC-HREC-TR-D496700
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  • 9
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    Space shuttle SRM plume expansion sensitivity analysis (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The exhaust plumes of the space shuttle solid rocket motors can have a significant effect on the base pressure and base drag of the shuttle vehicle. A parametric analysis was conducted to assess the sensitivity of the initial plume expansion angle of analytical solid rocket motor flow fields to various analytical input parameters and operating conditions. The results of the analysis are presented and conclusions reached regarding the sensitivity of the initial plume expansion angle to each parameter investigated. Operating conditions parametrically varied were chamber pressure, nozzle inlet angle, nozzle throat radius of curvature ratio and propellant particle loading. Empirical particle parameters investigated were mean size, local drag coefficient and local heat transfer coefficient. Sensitivity of the initial plume expansion angle to gas thermochemistry model and local drag coefficient model assumptions were determined.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-147528 , LMSC-HREC-TM-D496636
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  • 10
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    Supersonic flow of chemically reacting gas-particle mixtures. Volume 1: A theoretical analysis and development of the numerical solution (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A numerical solution for chemically reacting supersonic gas-particle flows in rocket nozzles and exhaust plumes was described. The gas-particle flow solution is fully coupled in that the effects of particle drag and heat transfer between the gas and particle phases are treated. Gas and particles exchange momentum via the drag exerted on the gas by the particles. Energy is exchanged between the phases via heat transfer (convection and/or radiation). Thermochemistry calculations (chemical equilibrium, frozen or chemical kinetics) were shown to be uncoupled from the flow solution and, as such, can be solved separately. The solution to the set of governing equations is obtained by utilizing the method of characteristics. The equations cast in characteristic form are shown to be formally the same for ideal, frozen, chemical equilibrium and chemical non-equilibrium reacting gas mixtures. The particle distribution is represented in the numerical solution by a finite distribution of particle sizes.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-147531 , LMSC-HREC-TR-D496555-VOL-1
    Format: application/pdf
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