高超声速滑翔式再入飞行器最大航程飞行轨迹分析  

The Maximum-range Trajectory Analysis of Hypersonic Glide-reentry Vehicle

作　　者：丁洪波[1] 蔡洪[1] 张士峰[1] 李安梁[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《国防科技大学学报》2009年第6期67-72,共6页Journal of National University of Defense Technology

基　　金：国家部委基金资助项目;教育部新世纪优秀人才计划项目(NCET-05-0901)

摘　　要：针对航程最大的再入问题,研究了高超声速滑翔式再入飞行器的飞行轨迹特性。使用Legendre伪谱法进行轨迹优化,得到最优轨迹。分析了路径约束对轨迹的影响,以及在路径约束下控制量对飞行轨迹的影响。根据控制量的取值规律,提出一种升力系数的分段直线取值模型。数字仿真表明,通过该模型得到的飞行轨迹与最优轨迹类似,且航程相差很小,可以作为一种使航程最大的轨迹控制方法。In order to maximize the range of reentry, the trajectory of hypersonic glide-reentry vehicle is studied. The optimal trajectory is obtained using legendre pseudospactral method （LPM）. The effect of the path constraints on the trajectory is analyzed. Furthermore, the regulation of the control variable of the constrained trajectory is analyzed. According to the rule, a piecewise linear model of the coefficient of lift is proposed. Numerical simulation shows that the trajectory derived by dais model is very similar to the optimal trajectory, and the ranges of the two trajectories are nearly the same, demonstrating a good control method for the maximumrange trajectory.

关 键 词：高超声速滑翔式再入 航程最大 轨迹 伪谱法 升力系数 分段直线取值模型 

分 类 号：V412[航空宇航科学与技术—航空宇航推进理论与工程]