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- W2331535749 abstract "As missions to Mars become more complex, new technology is needed to meet the required objectives. Aeroshell shape optimization has the potential to improve current technology so that these new objectives can be met. This work outlines an optimization methodology using gradient-based optimization strategies and CFD to determine optimal aeroshell shapes in hypersonic entry conditions. Pareto fronts are generated in a laminar perfect gas ow, a turbulent perfect gas ow, and a turbulent Mars 9-species atmosphere. The optimal capsules generated using the Mars atmospheric model show a signicant reduction in heating from the MSL capsule. These optimal shapes are spherical Apollo-like capsules which reduce the maximum heating to the forebody of the capsule by over 80 W=cm 2 while still maintaining similar aerodynamic characteristics. This signicant reduction in heating can allow for thinner and potentially lighter TPS materials. The reduction in TPS mass allows for an increase in payload mass while still maintaining a constant ballistic coecient." @default.
- W2331535749 created "2016-06-24" @default.
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- W2331535749 date "2013-01-05" @default.
- W2331535749 modified "2023-09-23" @default.
- W2331535749 title "CFD-Based Axisymmetric Aeroshell Shape Optimization in Hypersonic Entry Conditions" @default.
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- W2331535749 doi "https://doi.org/10.2514/6.2013-630" @default.
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