火箭定姿定点入轨的最优制导方法  

The Optimal Guidance of Rocket Fixed⁃attitude andFixed⁃point Orbit Injection

作　　者：王健[1] 刘星栋 支晶 Wang Jian;Liu Xingdong;Zhi Jing(Beijing Aerospace Automatic Control Institute,Beijing 100854,China)

机构地区：[1]北京航天自动控制研究所,北京100854

出　　处：《航天控制》2023年第5期42-46,共5页Aerospace Control

摘　　要：提出了一种能够给定入轨姿态并同时满足速度位置的6个终端约束的最优制导方法。针对发动机推力方向可控的运载火箭,建立了火箭定姿定点入轨的最优控制命题。通过引入新的控制变量将带等式约束的命题转化为控制变量无约束问题,并通过推导得到可解的哈密顿方程组,通过代数方法对哈密顿方程进行推导和简化,再利用数值算法方便地计算出协态变量,进而得到最优控制量曲线。仿真结果表明,通过调节推力的方向,本文提出的制导方法能够使火箭以预定的姿态在指定的入轨点进入目标轨道。A 6⁃terminal constrained optimal guidance method for orbit injection is proposed in this paper,which can provide an orbit attitude andsatisfy the specified speed and position at the same time.In view of the controllable engine thrust direction of launch vehicle,the optimal control proposition of the rocket fixed⁃attitude and fixed⁃point orbit injection is targeted.By introducing a new control variable,the proposition with equality constraints is transformed to control variable unconstraint and the solvable Hamiltonian equa⁃tion set is obtained through derivation.Hamilton equation is derived and simplified through applying alge⁃braic method,and numerical algorithm is used to calculate the co⁃state variable conveniently,and then the optimal control curve is obtained.Simulation shows that the guidance method proposed can make the rocket injected into the target orbit at a specified point under constrained speed and attitude by adjusting the direc⁃tion of the thrust.

关 键 词：运载火箭 定点入轨 最优制导 协态变量 

分 类 号：V11[航空宇航科学与技术—人机与环境工程]