文档介绍：国防科技大学学报
第 31 卷第 6 JOURNAL OF NAHONAL UNlVEKSriY OF DEFENSE TECmOLOGY 2009
文章塢号：1001-2486(2009)06-0077-07
高超声速滑翔式飞行器再入轨迹多目标多约束优化・
陈小庆，侯中喜,刘建霞
(国防科技大学航天与材料工程学院，湖南长沙410073)
摘 要:轨迹优化是高超声速滑翔式飞行器关键技术之一。为避免问接法求解轨迹优化问题时对初值敏 感以及伪谱法求解轨迹优化问题中难以处理航路点和禁飞区等问题•提出采用基于Akima插值多项式的直接 法求解高超声速滑翔式飞行器再入轨迹优化问題。以驻点热流密度最小和到达目标点时间最小为优化目标， 考虑了终端约束、航路点约束、禁飞区约束、动压约束、过载约束等约束条件。仿真结果表明:采用的插值方法 可以滅少插值过程中的控制变S：越界冋题;得到的Pai«o前沿具有良好的分布性，在初步设计时能够给设计 者较大的迭择余地;和文献中的单目标优化结果相比•本文所采用的算法也具有较好的寻优能力。
关键词：高超声速滑翔式飞行器;轨迹优化;多目标优化;Akima样条插值;直接法 中图分类号:V412 文献标识码：A
Multi-objective Optimization of Reentry Trajectory for Hypersonic
Glide Vehicle with Multi-constraints
CHEN Xiaoqing, HOU Jian-xia
(College of AsMpace and Material Engineering, National Univ, of Deferwe Techno'ogy. Chantha 410073, China)
Abstract:Trajectory optimization is a key toclwlogy of hypereonic glide vehicle. In order to avoid the disadvantage of indirect method's sensitivity to initial guess and pMudospectral method* s difficulty to settle path constraints, a direct method based on Akima spline interpolation is proposed to solve reentry trajectory optimization problem. A numeried example that minimizes the stagnation point heat flux and fly time to target while satisfying state constraints such as vehicle dynamics, control limitation. waypoint» nofly zone, dynamic pressure and overload is presented・ Compared with literature re