高超声速无动力滑翔飞行器最优弹道研究  

Research on Optimal Trajectory of Hypersonic Unpowered Glide Vehicle

作　　者：张烨琛 包为民 闵昌万 张宁宁 

机构地区：[1]空间物理重点实验室,北京100076

出　　处：《导弹与航天运载技术》2014年第4期5-8,共4页Missiles and Space Vehicles

摘　　要：分析高超声速无动力滑翔飞行器滑翔段最大射程弹道普遍存在的分段现象。根据该现象将滑翔段分为过渡段与准平衡滑翔段两段。提出基于Legendre伪谱法的弹道优化设计方法:在过渡段以其终点速度最大为优化目标对攻角进行优化;在准平衡滑翔段直接将攻角设计为最大升阻比攻角,经分析,该方法所得射程与滑翔段全程优化所得射程几乎相同。该方法简化了滑翔段射程优化问题。The sectioned phenomenon existed in the maximum range trajectory of hypersonic unpowered glide vehicle is analyzed. Glide phase is divided into transitional phase and quasi-equilibrium glide phase according the phenomenon. Based on the Legendre Pseudospectral method, a trajectory optimization design method is proposed——optimize the angle of attack to achieve the maximum velocity at the terminal in transitional phase, while the angle of attack is designed with maximum lift-drag ratio in quasi-equilibrium glide phase. The range calculated in this method is the same as that of glide phase after optimization. The glide trajectory optimization problem is simplified in this method.

关 键 词：过渡段 准平衡滑翔段 弹道优化 LEGENDRE伪谱法 

分 类 号：V412[航空宇航科学与技术—航空宇航推进理论与工程]