高超声速飞行器滑行段最优弹道的间接算法  

Indirect Method for the Hypersonic Vehicle Maximum-Glide Problem

作　　者：李佳峰[1] 周浩[1] 陈万春[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《飞行力学》2009年第3期41-44,49,共5页Flight Dynamics

基　　金：航天支撑技术基金资助

摘　　要：针对高超声速飞行器滑行段非线性程度高的特点,提出了逐步细分的参数法优化策略,采用序列二次规划(SQP)算法得到了问题的次优解。在此基础上,构建了原系统的等价系统,并给出了两个系统协态变量之间的关系,提出了沿次优弹道的分段打靶法,求解等价系统的两点边值问题(TPBVP)后,经转化得到了原问题的最优解。优化结果表明,采用逐步细分的优化策略能克服优化算法对初值敏感的缺点,快速稳定地收敛到问题的解,沿次优弹道的分段打靶法更能适应非线性程度高的系统。A parameter method of gradually increased subsections was proposed to fit in with the highly nonlinear characteristics of the hypersonic vehicle maximum-glide problem. Based on the suboptimal results obtained by optimizing with the SQP method, the equivalence system was established and the co-states relation to the original problem was derived; then, a subsection shooting method along the suboptimal trajectery solution was given to explore the TPBVP of the equivalence system, and the optimal solution was computed by transforming. The simulation results indicate that： first, the method of gradually increasing subsections overcomes shortcomings of initial value sensitivity, and takes on fast convergence rate and high stabilization; second, the subsection shooting method fits the highly nonlinear problems.

关 键 词：高超声速飞行器 弹道优化 最优控制 间接算法 打靶法 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]