Determination of Uncertainties for Analytically Derived Material Properties to Be Used in Monte Carlo Based Orion Heatshield Sizing

Coughlin, Scott J ; Sixel, William R ; Sepka, Steven A ; McGuire, M Kathleen

关键词: ABLATIVE MATERIALS;    ATMOSPHERIC ENTRY;    COMPUTATION;    ENTHALPY;    HEAT SHIELDING;    MONTE CARLO METHOD;    PARAMETERIZATION;    PYROLYSIS;    THERMAL PROTECTION;    THERMOGRAVIMETRY;    THICKNESS;   

RP-ID  :  JSC-E-DAA-TN50319

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来源: NASA Technical Reports Server

【 摘 要 】

Ablative materials are often used for spacecraft heatshields to protect underlying structures from the extreme environments associated with atmospheric reentry. NASA's Orion EM-1 capsule has been designed to use a molded Avcoat material system. In order to determine the required heatshield thickness, a Monte Carlo approach to the sizing process was proposed. To perform the Monte Carlo simulation, statistical uncertainties on all material property input parameters were required. Obtaining these values for measured properties is straightforward, however input parameters that are derived analytically have historically used uncertainties based on engineering judgment. A MATLAB program was created to use laboratory generated thermogravimetric analysis (TGA) data to calculate uncertainties on the Arrhenius parameters for molded Avcoat. Uncertainties associated with the normalized ablation rate and pyrolysis gas enthalpy were also generated using a wrapper script and the ACE code. These uncertainties could then be tied directly to measured values of individual elemental constituents. The resulting uncertainty values will allow for a probabilistic sizing approach on molded Avcoat with a higher level of confidence in the input parameters.