A Reliability Comparison of Classical and Stochastic Thickness Margin Approaches to Address Material Property Uncertainties for the Orion Heat Shield

Sepka, Steven A ; McGuire, Mary Kathleen ; Vander Kam, Jeremy C

关键词: HEAT SHIELDING;    ABLATIVE MATERIALS;    AEROTHERMODYNAMICS;    BALLISTIC TRAJECTORIES;    MONTE CARLO METHOD;    THERMAL PROTECTION;    ABORT TRAJECTORIES;    RELIABILITY;    FOREBODIES;    POSITION (LOCATION);    MECHANICAL PROPERTIES;    THICKNESS;   

RP-ID  :  ARC-E-DAA-TN49658

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来源: NASA Technical Reports Server

【 摘 要 】

The Orion Thermal Protection System (TPS) margin process uses a root-sum-square approach with branches addressing trajectory, aerothermodynamics, and material response uncertainties in ablator thickness design. The material response branch applies a bondline temperature reduction between the Avcoat ablator and EA9394 adhesive by 60 C (108 F) from its peak allowed value of 260 C (500 F). This process is known as the Bond Line Temperature Material Margin (BTMM) and is intended to cover material property and performance uncertainties. The value of 60 C (108 F) is a constant, applied at any spacecraft body location and for any trajectory. By varying only material properties in a random (monte carlo) manner, the perl-based script mcCHAR is used to investigate the confidence interval provided by the BTMM. In particular, this study will look at various locations on the Orion heat shield forebody for a guided and an abort (ballistic) trajectory.