高超声速滑翔飞行器引入段弹道优化  

Trajectory Optimization in Injection Phase for Hypersonic Gliding Vehicle

作　　者：周浩[1] 周韬[1] 陈万春[1] 殷兴良[2] 

机构地区：[1]北京航空航天大学宇航学院,北京100083 [2]中国航天科工集团公司,北京100830

出　　处：《宇航学报》2006年第5期970-973,共4页Journal of Astronautics

摘　　要：高超声速飞行器弹道优化设计的目的是得到高超声速飞行的控制指令,从而得到方案弹道,针对其数学模型,寻找一个作为输入的攻角规律使得弹道最优。我们将此弹道问题转化成最优控制问题,通过极大值原理得到最优弹道的一阶必要条件。我们采用遗传算法求解了此两点边值问题。首先从次优化弹道得到攻角的变化规律,然后由从次优化弹道估计出的攻角范围推导出初始伴随变量的变化范围,再用遗传算法在此范围内优化初始伴随变量得到了全局最优弹道和相应的初始伴随变量。通过一个实例求得了满足热流约束的最大终端速度弹道,通过比较可知优于次优化弹道,从数值计算例子还可以看到遗传算法是求解两点边值问题的一种比较好的方法。The purpose of trajectory optimization for hypersonic vehicle was obtaining the control command, simultaneity the scheme trajectory is obtained. According hypersonic vehicle＇s mathmatical models, The fit law of the angle of attack was considered as the input to make trajectory optimization. The trajectory problem was cast as the optimal control problem and Pontriaghin Maximum Principle was used to obtain first order necessary condition. These was in the form of a two point boundary value problem （TPBVP）, and which was solved by means of the gene algorithm （GA）, firstly the scope of initial adjoint variables was estimated by the scope of the angle of attack which was obtained by suboptimal, trajectory, then in the scope the GA was used to get the goal optimal value. By a hypersonic numerical application, terminal velocity maximum optimal trajectory curve with heat rate constraint was obtained. At the same time the result was compared with suboptimal flight scheme, the terminal velocity was larger than the one of suboptimal flight scheme. The numerical example showed that the GA was a perfect method for TPBVP.

关 键 词：高超声速飞行器 最优控制 弹道 优化 

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]