Aerothermodynamic Shape Optimization of Hypersonic Entry Aeroshells
Author(s)
Theisinger, John E.
Braun, Robert D.
Clark, Ian G.
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Abstract
Previous work by the authors has focused on the optimization of entry aeroshell shapes
based solely on objectives related to aeroshell geometry and hypersonic aerodynamic
performance. This multi-objective optimization framework has been extended to include the
impact of hypersonic aerothermodynamics - that is, aerodynamic heating is now considered
alongside the previously-developed objectives. The methodology for performing
aerothermodynamic analyses has been adapted from research that has demonstrated the
ability to obtain an approximate three-dimensional heating distribution using axisymmetric
analyses by matching certain similarity criteria. In the current work, axisymmetric solutions
are obtained by coupling Newtonian inviscid solutions with axisymmetric boundary-layer
relations that provide an estimate of heat flux. Non-uniform rational B-spline surfaces are
used to represent aeroshell shapes. In order to maintain continuity with the previous work,
the current aerothermodynamic analysis method is applied to the Mars Science Laboratory
mission, in which a heat-rate-minimization objective is traded against objectives to maximize
drag-area, static stability, and volumetric efficiency. Two-objective optimizations are
performed to highlight major trends and tradeoffs between heat rate and the other three
objectives. Results are compared to the baseline 70-degree sphere-cone aeroshell.
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Date
2010-09
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