升力式再入飞行器多约束多阶段弹道优化设计  

Multi-constraints and multi-phases trajectory optimization of lift reentry vehicle

作　　者：黄育秋[1] 何麟书[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《哈尔滨工业大学学报》2011年第7期144-148,共5页Journal of Harbin Institute of Technology

摘　　要：结合再入飞行器实际任务需要,以升力式再入飞行器机动突防弹道优化设计为研究目的,给出了多约束多阶段弹道优化模型,研究了弹道优化数值解法理论,将该多约束多阶段优化问题的多个阶段弹道优化模型统一于1个优化算法;采用直接法+序列二次规划法解该优化问题,得到了满足相应约束的再入机动突防弹道.仿真结果表明,采用该方法能够进行升力式再入飞行器的再入机动突防弹道的优化设计,并具有较好的效果.In this paper,a maneuvering penetration optimization for trajectory of lift reentry vehicle is researched.At first,a model for this problem is proposed and its trajectory optimization theory is studied,and then the multi-constraints and multi-phases trajectory optimization is unified in an optimization algorithm.The direct method and sequential quadratic programming algorithm are used to solve the trajectory optimization problem,and finally the maneuvering penetration optimization trajectory which satisfies corresponding constraint is obtained.The simulation results show that the model proposed in this paper is reasonable and feasible with good results.

关 键 词：再入飞行器 多约束多阶段弹道优化 机动突防 直接法 序列二次规划 

分 类 号：V412[航空宇航科学与技术—航空宇航推进理论与工程]