基于能耗最优的卫星姿控系统推力器可重构性设计  

Reconfigurability Design for Thrusters of Satellite Attitude Control System Based on Optimal Energy Consumption

作　　者：王世新[1,2] 邢琰[1,2] 王大轶[1,2] 刘成瑞[1,2] 

机构地区：[1]北京控制工程研究所,北京100190 [2]空间智能控制技术重点实验室,北京100190

出　　处：《航天控制》2015年第5期46-53,共8页Aerospace Control

基　　金：国家自然科学基金资助项目(61203093;61004073)

摘　　要：针对卫星姿控系统执行机构可重构性设计,提出了可重构性评价指标,并以推力器为具体的执行机构建立了优化设计模型,将遗传算法应用于其最优解的求取。Matlab/Simulink环境下搭建的卫星闭环姿控系统仿真结果表明,设计安装方案无论在故障情况下还是在正常情况下,系统可重构性和控制性能均明显优于其他比较方案,在一定程度上有效地验证了所提优化设计方法和结果的合理性和正确性。For the reconfigurability design of actuators of the satellite attitude control system,corresponding evaluation criterion is proposed. Optimization design model is established by taking thrusters as the specific actuators. And the optimal solution is acquired by the application of genetic algorithm（ GA）. The simulation results of the satellite closed- loop attitude control system built in the Matlab / Simulink environment show that whether under the fault condition or normal condition,the designed scheme is superior to the others in system reconfigurability and control performance obviously. Thus the rationality and correctness of the proposed optimization design method and designed result are verified effectively.

关 键 词：姿态控制 推力器 可重构性 优化设计 仿真验证 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]