基于拟能量的高超声速飞行器再入轨迹优化  

Reentry Trajectory Optimization of Hypersonic Vehicle Based on Pseudo Energy

作　　者：孙勇[1] 段广仁[1] 张卯瑞[1] 张泽[1] 

机构地区：[1]哈尔滨工业大学控制理论与制导技术研究中心,哈尔滨150001

出　　处：《上海交通大学学报》2011年第2期262-266,共5页Journal of Shanghai Jiaotong University

基　　金：国家自然科学基金资助项目(60710002)

摘　　要：考虑高超声速飞行器再入过程总加热量最小,基于拟能量将单段轨迹优化转化为多段轨迹优化问题,采用非等间距控制变量参数化方法对每段轨迹分别优化.高超声速飞行器再入轨迹必须满足热流率、动压和过载3个约束.通过把控制变量参数化,同时引入时间尺度变换和不等式约束转化方法,将轨迹优化问题转化为含有约束的非线性规划问题.基于拟能量概念,将再入轨迹进行了分段优化,以4段为例进行了仿真,计算时间比单段情况下缩短了约50%.The whole heating of the hypersonic vehicle in reentry process was minimized based on the pseudo energy,which is used to divide the reentry trajectory into some segments.The control variable parameterization with different time durations was introduced to optimize each trajectory.The reentry trajectory of the hypersonic vehicle must satisfy the heating rate,dynamic pressure and the overload path constraints.The control variable parameterization was applied and the trajectory optimization problem become a nonlinear programming problem by the time scaling and the inequality constraint transformation.The pseudo energy definition was introduced to divide the reentry trajectory into some segments for optimization.A case with four segments was taken as an example for simulation.The computing time is less than that of one segment by 50%.

关 键 词：高超声速飞行器 拟能量 再入轨迹优化 控制变量参数化 

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]