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3 edition of Finite-element reentry heat-transfer analysis of space shuttle orbiter found in the catalog.

Finite-element reentry heat-transfer analysis of space shuttle orbiter

Finite-element reentry heat-transfer analysis of space shuttle orbiter

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Published by National Aeronautics and Space Administration, Scientific and Technical Information Branch, For sale by the National Technical Information Service] in [Washington, D.C.], [Springfield, Va .
Written in English

    Subjects:
  • Space shuttles,
  • Heat -- Transmission

  • Edition Notes

    Other titlesFinite element reentry heat transfer analysis of space shuttle orbiter.
    StatementWilliam L. Ko, Robert D. Quinn, and Leslie Gong.
    SeriesNASA technical paper -- 2657.
    ContributionsQuinn, Robert D., Gong, Leslie., United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL15274152M

    Structural performance and resizing of the finite-element thermal analysis computer program was used in the reentry heat transfer analysis of the space shuttle orbiter. One midfuselage cross section and one midspan wing segment were selected to study the effects of internal convection and internal radiation on the structural temperatures. Re-entry heating of Space Shuttle Orbiter re-enters the atmosphere as a blunt body by having a very high (40 degrees) angle of attack. Majority of the heating over 80% is caused by compression of the air ahead of the ultrasonic vehicle Fig 2: Reentry heating of Space Shuttle I SEMESTER MACHINE DESIGN Batch

    Finite element analysis of turbulent forced convection in lid‐driven rectangular cavities Solution accuracies of finite element reentry heat transfer and thermal stress analyses of space shuttle orbiter. William L. Ko; Pages: ; First Published Monte Carlo method for radiative heat transfer analysis of general gas‐particle. Full text of "Space Shuttle orbiter entry heating and TPS response: STS-1 predictions and flight data" See other formats ^/ SPACE SHUTTLE ORBITER ENTRY HEATING AND TPS RESPONSE: STS-1 PREDICTIONS AND FLIGHT DATA Robert C. Rled, Winston D. Goodrich, Chien P. Li, Carl D. Scott, Stephen M. Derry, and Robert J. Maraia NASA Lyndon B. Johnson Space Center Houston r Texas .

    Experimental assessment of a computer program used in space shuttle orbiter entry heating analyses (NASA technical memorandum) Unknown Binding – by William L Wells (Author) See all formats and editions Hide other formats and editions. Price New from Author: William L Wells. A structural performance and resizing (SPAR) finite element thermal analysis computer program was used in the heat transfer analysis of the Space Shuttle Orbiter that was subjected to reentry aerodynamic heatings. One wing segment of the right wing (WS ) and the whole left wing were selected for the thermal : L. Gong, R. D. Quinn and W. L. Ko.


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Finite-element reentry heat-transfer analysis of space shuttle orbiter Download PDF EPUB FB2

Finite-Element Reentry Heat-Transfer Analysis of Space Shuttle Orbiter Author: Ko, William L., Robert D. Quinn, and Leslie Gong Subject: NASA TP Keywords: Heat-transfer analysis, Reentry heating, Space Shuttle orbiter, Space t ransportation system data Created Date: 7/2/ AM.

A structural performance and resizing (SPAR) finite-element thermal analysis computer program was used in the heat-transfer analysis of the space shuttle orbiter subjected to reentry aerodynamic heating.

Three wing cross sections and one midfuselage cross section were selected for the thermal by: Get this from a library. Finite-element reentry heat-transfer analysis of space shuttle orbiter.

[William L Ko; Robert D Quinn; Leslie Gong; United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.]. SUMMARY A SPAR (structural performance and resizing) finite element thermal analysis computer program was used in the reentry heat transfer analysis of the space shuttle.

Two typical wing cross sections and a midfuselage cross section were selected for the analysis. Finite-element reentry heat-transfer analysis of space shuttle orbiter / By William L.

Ko, Leslie. Gong, Robert D. Quinn and Ames Research Center. A structural performance and resizing (SPAR) finite-element thermal analysis computer program was used in the heat-transfer analysis of the space shuttle orbiter subjected to reentry aerodynamic heating. Three wing cross sections and one midfuselage cross section were selected for the thermal analysis.

A structural performance and resizing!SPAR) finite-element computer program and NASA structural analysis (NAST2AN) finite-clement computer programs were used in the thermal stress analysis of the space shuttle orbiter subjected to reentry aerodynamic heating.

A SPAR structural model was set up for the entire left wing of the orbiter,File Size: 1MB. SUMMARY A structural performance and resizing (SPAR) finite-element thermal analysis computer program was used in the heat-transfer analysis of the space shuttle orbiter subjected to reentry aerodynamic heating.

Three wing cross sections and one midfuselage cross section were selected for the thermal Size: 2MB. Thermal Stress Analysis of Space Shuttle Orbiter Subjected to Reentry Ae rodynamic Heating Author: William L.

Ko and Roger A. Fields Subject: NASA TM Keywords: Finite-element modelings; Space shuttle orbiter; STS-5 heating; Thermal stress analysis Created Date: 4/2/ PM. After completing the Space portion of its mission, the Orbiter was designed to be able to reenter the earth’s atmosphere at a very high speed, slow down significantly, and land intact.

“Finite-Element Reentry Heat-Transfer Analysis of Space Shuttle Orbiter”, NASA Technical PaperDecember () Estimating the Orbiter Author: Irwin E. Alber. Abstract A structural performance and resizing (SPAR) finite element thermal analysis computer program was used in the heat transfer analysis of the space shuttle orbiter that was subjected to reentry aerodynamic heatings.

One wing segment of the right wing (WS ) and the whole left wing were selected for the thermal analysis. The cooling performance for the sustained hypersonic flight and transient reentry Skip to main content Piol O. and Kuhn M., “ Heat Balance of a Transpiration-Cooled Heat Shield,” Journal of Thermophysics and Heat Transfer, Vol Quinn R.

and Gong L., “ Finite-Element Reentry Heat-Transfer Analysis of Space Shuttle Orbiter Author: Tobias Hermann, Matthew McGilvray, Imran Naved. Returning from Space: Re-entry Re-entry Motion Analysis in Action Trajectory and Deceleration Trajectory and Heating The Space Shuttle in orbit has a mass ofkg (, lb.), an orbital velocity of m/s (17, m.p.h.), and an altitude of km ( mi.).

In. Structural performance and resizing (SPAR) finite element thermal analysis computer programs was used in the heat transfer analysis of the space shuttle orbiter wing subjected to reentry aerodynamic by: 3.

FINITE-ELEMENT REENTRY HEAT-TRANSFER ANALYSIS OF SPACE SHUTTLE ORBITER, Technical Paper Authors: William L. Ko, Robert D. Quinn and Leslie Gong Report Number: NASA-TP Performing Organization: NASA Dryden Flight Research Center, Edwards, CA Availability: Format(s) on-line: PDF (2, KBytes) Report Date: December No.

Pages: Leslie Gong's 14 research works with 84 citations and reads, including: Hypothetical Reentry Thermostructural Performance of Space Shuttle Orbiter With Missing or. A structural performance and resizing (SPAR) finite element thermal analysis computer program was used in the heat transfer analysis of the Space Shuttle Orbiter that was subjected to reentry.

This report deals with hypothetical reentry thermostructural performance of the Space Shuttle orbiter with missing or eroded thermal protection system (TPS) tiles.

The original STS-5 heating (normal transition at sec) and the modified STS-5 heating (premature transition at sec) were used as. Different finite element models previously set up for thermal analysis of the space shuttle orbiter structure are discussed and their shortcomings identified.

Element density criteria are established for the finite element thermal modelings of space shuttle orbiter-type large, hypersonic aircraft structures. These criteria are based on rigorous studies on solution accuracies using different Cited by: 3.

A structural performance and resizing (SPAR) finite-element thermal analysis computer program was used in the heat-transfer analysis of the space shuttle orbiter subjected to reentry aerodynamic. A heat-transfer model has been developed for two common, inherently flame-resistant fabrics, Nomex® IIIA and Kevlar®/PBI, when subjected to the high heat fluxes used in bench top tests, such as the thermal protective performance (TPP) test, ASTM D The apparent heat capacity method was used to model thermochemical reactions in these materials with information from thermal Cited by: Abstract.

Structural performance and resizing (SPAR) finite-element thermal analysis computer program was used in the heat transfer analysis of the Space Shuttle Orbiter wing subjected to reentry aerodynamic heating.Cfd Analysis of Tile-Repair Augers for the Shuttle Orbiter Re-Entry Aeroheating [Mazaheri, Ali R., Nasa Technical Reports Server (Ntrs)] on *FREE* shipping on qualifying offers.

Cfd Analysis of Tile-Repair Augers for the Shuttle Orbiter Re-Entry AeroheatingCited by: 1.