摘要
运用吻切锥法生成了高超声速乘波构型,对乘波构型进行了全三维流场计算,研究了乘波构型在不同飞行状态下的气动性能。采用结合惩罚函数的单纯形法对吻切锥乘波构型在设计状态下以升阻比最大为目标分别进行了不考虑约束条件以及以容积效率、前体长度为约束条件的构型优化,生成了更为适合工程应用的乘波构型。计算结果表明:吻切锥乘波构型的设计状态升阻比通过优化设计可以得到大幅提高,最大升幅为35.99%;考虑约束条件后升阻比仍有较大升幅,最大升幅24.91%。
The waverider configurations were generated by osculating-cone. To better understand hypersonic waverider configuations performance, the three dimensional flow field calculations of waverider configuations was conducted. The nonlinear simplicial method with punish function was used to optimize the osculating-cone waverider with lift-to-drag ratio as the objective function. Investigation shows that the optimized waverider has higher lift-to-drag ratio in the design condition with the highest increment of 35.99% and the highest increment of 24.91% when considering limitations.
出处
《弹箭与制导学报》
CSCD
北大核心
2008年第6期183-185,188,共4页
Journal of Projectiles,Rockets,Missiles and Guidance
基金
西北工业大学青年科技创新基金
航天科技创新基金(CASC0106)资助
关键词
乘波构型
吻切锥
优化
升阻比
waverider
osculating-cone
optimization
lift-to-drag ratio
