Aerothermal Design of a Common Probe for Multiple Planetary Destinations

Allen, Gary A, Jr ; Milos, Frank S ; White, Todd R ; Hwang, Helen H

关键词: ABLATIVE MATERIALS;    AEROSHELLS;    ATMOSPHERIC ENTRY;    COMPUTATIONAL FLUID DYNAMICS;    FOREBODIES;    SYSTEMS ENGINEERING;    THERMAL PROTECTION;    ATMOSPHERIC MODELS;    HEAT SHIELDING;    INSULATION;    NEPTUNE (PLANET);   

RP-ID  :  ARC-E-DAA-TN57435

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来源: NASA Technical Reports Server

【 摘 要 】

Estimate the mass of the Thermal Protection System (TPS) for a single design construct of an atmospheric entry probe with a rigid aeroshell, which could be used at five destinations, i.e. Venus, Saturn, Uranus, Neptune, and perhaps, Jupiter. The entry mass of the probe is 400 kg with a ballistic coefficient of 216 kg/m2. Process: The 3DoF trajectory simulation program Traj, coupled with the TPS response program FIAT was used for simulation and design. The assumed atmospheric models were VIRA (Venus-GRAM) for Venus, the Julianne Moses' model for Saturn, a NASA Ames engineering model for Uranus, Neptune-GRAM for Neptune, and Galileo Probe (Al Seiff's) result for Jupiter.