超声速进气道结构参数优化设计研究  

Optimization Design for Supersonic Inlet Structure Parameter

作　　者：戎宜生[1] 陈伟芳[2] 杨宇斌[3] 刘伟强[1] 

机构地区：[1]国防科技大学航天与材料工程学院,长沙410073 [2]浙江大学航空航天学院,杭州310027 [3]北京航天长征飞行器研究所,北京100076

出　　处：《力学季刊》2010年第3期371-375,共5页Chinese Quarterly of Mechanics

摘　　要：本文以总压恢复系数最大为优化目标,给出了一种设计超声速进气道结构的优化方法。该方法依据一维定常流的理论,推导得到了优化问题和约束条件的表述,并采用拉格朗日乘子法实现对优化问题的求解。将优化结果与经典结论进行比较分析,证明该优化方法的可行性。最后对优化结构进行了数值验证,实现了稳定的波系结构和流场参数分布。An optimization design method for supersonic inlet＇s structure was presented in order to maximize total pressure recovery coefficient. The expression of the optimization problem and constraints were derived based on 1D steady flow theory and were solved by the use of Lagrangian method. The optimization result with the classic conclusion were compared and analyzed, the result proves the optimization method was feasible. And the numerical experiment also was done to test the optimized structure, which obtained steady shocks and flow parameter distribution.

关 键 词：超声速进气道 一维定常流 总压恢复系数 

分 类 号：O342[理学—固体力学] O354.3[理学—力学]