临近空间滑翔飞行器初始下降段轨迹规划  

Initial Descent Phase Trajectory Planning for Near-space Glide Vehicle

作　　者：孙建波 潘幸华 赵育善[1] Sun Jianbo;Pan Xinghua;Zhao Yushan(Department of Astronautics,Beihang University,Beijing 100191,China;Science and Technology on Complex System Control and Intelligent Agent Cooperation Laboratory,Beijing 100074,China;Beijing Electro-mechanical Engineering Institute,Beijing 100074,China)

机构地区：[1]北京航空航天大学宇航学院,北京100191 [2]复杂系统控制与智能协同技术重点实验室,北京100074 [3]北京机电工程研究所,北京100074

出　　处：《战术导弹技术》2020年第5期114-120,共7页Tactical Missile Technology

摘　　要：对临近空间滑翔飞行器初始下降段的轨迹规划问题进行了深入研究。首先利用拟平衡滑翔条件,推导了初始下降段末端的切换条件;然后将初始下降段分为开环控制段和轨迹规划段,在轨迹规划段以攻角作为控制量,设计满足过程约束、切换条件和控制约束的控制律。根据所建动力学模型,采用高斯伪谱法进行轨迹优化;以航迹角偏差为自变量,设计圆弧过渡函数生成攻角指令。仿真结果表明:两种方法都能满足各种约束,且圆弧过渡法不依赖于传统的标称攻角设计,计算量小,便于在线运用。This paper focus on initial descent phase trajectory planning problem for near-space glide vehicle. Firstly,transition condition at the terminal of initial descent phase is deduced by the quasi-equilibrium glide condition. Afterwards,the initial descent phase is divided into two sub-phases noted as openloop control phase and trajectory planning phase,angle of attack is designed as control variable to satisfy path constraints,transition condition and control constraints during the second phase. The dynamic modeling is formulated for trajectory optimization and solved by Gauss pseudo-spectral method. Then,the angle of attack command is generated by the arc transition function with the flight path angle deviation as independent variable. The simulation results show that all the constraints can be satisfied using the two proposed methods. The arc transition method does not require the traditional nominal angle of attack design,which can be applied online with low computational cost.

关 键 词：临近空间滑翔飞行器 初始下降段 拟平衡滑翔 高斯伪谱法 圆弧过渡法 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]