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首页> 外文期刊>Journal of Spacecraft and Rockets >Multi-Objective Hypersonic Entry Aeroshell Shape Optimization
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Multi-Objective Hypersonic Entry Aeroshell Shape Optimization

机译：多目标超音速进入机壳形状优化

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摘要

A framework has been developed to identify hypersonic entry aeroshell shapes that are Pareto-optimal with respect to multiple conflicting objectives. The objectives and constraints are derived from the aeroshell geometry and aerodynamic performance. Shapes are parameterized using nonuniform rational B-splines for maximum design flexibility. Hypersonic aerodynamic objectives and constraints are based on rapid predictions obtained from Newtonian flow theory. Single- and multi-objective genetic algorithms are employed for optimization. This framework has been applied to the Mars Science Laboratory mission to quantify tradeoffs inherent to blunt-body aeroshells. Lift-to-drag ratio, volume, and size constraints were derived from the 70-degree sphere-cone aeroshell for this mission, and aeroshell shapes were optimized based on three conflicting objectives: drag area, longitudinal static stability, and volumetric efficiency. First, single-objective optimization revealed the extreme designs for this objective space. Next, two-objective optimization produced Pareto fronts of compromise designs that illustrate the tradeoffs among each pair of objectives. Finally, a three-objective optimization provided Pareto-optimal designs that offer simultaneous improvement in all three objectives relative to the baseline 70-degree sphere-cone aeroshell.
机译：已经开发出一种框架，以识别相对于多个相互冲突的目标而言帕累托最优的高超音速进气翼形状。目标和约束条件是从飞机的几何形状和空气动力学性能得出的。使用非均匀有理B样条参数化形状，以实现最大的设计灵活性。高超音速的空气动力学目标和约束条件基于从牛顿流理论获得的快速预测。采用单目标和多目标遗传算法进行优化。该框架已应用于火星科学实验室任务，以量化钝体机壳固有的权衡。升空阻力比，体积和尺寸约束均来自于此任务的70度球形圆锥形飞机壳体，并且基于三个相互冲突的目标对飞机壳体的形状进行了优化：阻力区域，纵向静态稳定性和体积效率。首先，单目标优化揭示了该目标空间的极端设计。接下来，两目标优化产生了折衷设计的Pareto前沿，说明了每对目标之间的权衡。最终，三目标优化提供了帕累托最优设计，相对于基线70度球锥机身，这三个目标同时得到了改善。

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