刚体航天器的最小能量姿态机动最优控制研究  

Study on the Minimal Energy Maneuvering Control of a Rigid Spacecraft with Momentum Transfer

作　　者：张士峰[1] 钱山[1] 李鹏奎[1] 

机构地区：[1]国防科技大学航天与材料工程学院,长沙410073

出　　处：《宇航学报》2009年第4期1504-1509,1515,共7页Journal of Astronautics

摘　　要：针对航天器姿态机动最优控制问题,研究了初始条件和目标状态给定,以三个正交安装的动量轮为控制执行机构且机动控制时间不定的最小能量姿态机动控制方案。首先,采用与传统打靶法不同的非线性规划NLP方法来描述带约束的姿态控制问题,将控制次数设为固定值,将采样周期看作变量,通过迭代方法进行求解;然后,提出NLP初始可行解的构造方法,以不同初始可行解为初值,多次寻优,最终找到刚体航天器最小能量姿态机动的相对最优控制方案;最后,通过仿真试验验证了该方法的可行性和优越性。To the problem of attitude maneuvers by optimal control, a minimal energy maneuvering control problem with open final time of a rigid spacecraft actuated by three orthogonal momentum wheels was studied. Firstly, this control problem was formulated and solved as a constrained nonlinear programming （NLP） by utilizing an iterative procedure. Different from conventional shooting methods, the count of control steps was fixed initially and the sampling period was treated as a variable in this novel method. Secondly, an approach to find the initial feasible solutions of the NLP problem was proposed. Since initial feasible solutions can be found easily, the optimization process of the NLP problem can be started from different points to find the minimal energy rest-to-rest maneuver of the rigid spacecraft between two attitudes. Finally, to show the feasibility of the proposed method, simulation results were included for illustration.

关 键 词：最小能量控制 非线性规划 刚体航天器 动量转移 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]