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  • 1
    facet.materialart.
    Unknown
    TPS Sizing for Access-to-Space Vehicles (1996)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: A study was carried out to identify, develop, and benchmark simulation techniques needed for optimum thermal protection system (TPS) material selection and sizing for reusable launch vehicles. Fully viscous, chemically reacting, Navier-Stokes flow solutions over the Langley wing-body single stage to orbit (SSTO) configuration were generated and coupled with an in-depth conduction code. Results from the study provide detailed TPS heat shield materials selection and thickness sizing for the wing-body SSTO. These results are the first ever achieved through the use of a complete, trajectory based hypersonic, Navier-Stokes solution database. TPS designs were obtained for both laminar and turbulent entry trajectories using the Access-to-Space baseline materials such as tailorable advanced blanket insulation. The TPS design effects (materials selection and thickness) of coupling material characteristics to the aerothermal environment are illustrated. Finally, a sample validation case using the shuttle flight database is included.
    Keywords: Nonmetallic Materials
    Type: Thirteenth Workshop for Computational Fluid Dynamic Applications in Rocket Propulsion and Launch Vehicle Technology; 963-976; NASA-CP-3332-Vol-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Unknown
    Thermal Response and Ablation Programs for TPS Sizing Computation (1997)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: The computer programs developed at NASA Ames Research Center for TPS sizing computation have been applied to many NASA's space missions, such as Mars Pathfinder, StarDust, Mars 2001, DS-II, and Saturn Entry Probe. These computer programs include FIAT (Fully Implicit Ablation and Thermal Response Program, MAT (Multi-component Ablation Thermochemistry Program), TPSX (Thermal Protection Systems Expert & Material Properties Database), and TPSGui (Thermal Protection Systems Graphical User Interface). For most planetary missions, the aerothermodynamics and material response are strongly coupled; thus a closed loop iteration technique between the FIAT and CFD (Computational Fluid Dynamics) codes has been developed to obtain the high fidelity bench mark TPS sizing solution. The computer codes and predictive methods are presented and discussed in detail.
    Keywords: Nonmetallic Materials
    Type: Workshop on Aeroassist Technologies; Jan 14, 1997 - Jan 16, 1997; Pasadena, CA; United States
    Format: text
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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