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提出了高超声速飞行器参数化模型,并在此基础上通过快速、高效的工程方法开展了初步的气动力计算。以类HTV-2布局为对象,开展了以升阻比和容积率为设计目标的气动布局优化研究;以类X-37布局为对象,开展了以航程和驻点总加热量为设计目标的弹道优化设计。采用加权求和的方法求解多目标优化问题。研究表明,通过优化可获得设计目标权重取不同值时的优化结果,各优化结果具有明显的不同,具体将哪一个优化结果作为最终的选择,主要依赖于设计者的需求。
The hypersonic vehicle parameterization model is proposed. Based on this, a preliminary aerodynamic calculation is carried out through a fast and efficient engineering method. Based on the HTV-2 HTV-2 layout, the aerodynamic layout optimization with lift-drag ratio and volume ratio as the design goals was carried out. For the X-37 type layout, Ballistic optimization design. Solving Multiobjective Optimization Problems with Weighted Summation. The results show that the optimization results obtained when the design objective weight is different are obtained through optimization. The optimization results have obvious differences. Which optimization result is the final choice depends on the designers’ requirements.