挠性航天器姿态机动控制的高维多目标优化  

A High Dimensional Multi-objective Optimization of Attitude Maneuver Control for Flexible Spacecraft

作　　者：周端[1] 郭毓[1] 陈庆伟[1] 胡维礼[1] 

机构地区：[1]南京理工大学自动化学院,江苏南京210094

出　　处：《信息与控制》2013年第3期299-307,共9页Information and Control

基　　金：国家自然科学基金资助项目(60975075);江苏省高校自然科学研究计划资助项目(10KGB510010)

摘　　要：为了缓解挠性航天器姿态大角度机动控制中快速性与高稳定度之间的矛盾,研究了具有模型参数不确定和环境干扰的挠性航天器姿态大角度快速机动控制的高维多目标优化问题.在动力学分析的基础上,设计了鲁棒姿态控制律.通过分析机动路径对挠性帆板振动的影响,规划了一种加加速度光滑的机动路径.建立了挠性航天器姿态控制问题的高维多目标优化模型,并基于一种改进的r支配多目标非支配排序进化算法,对挠性航天器姿态机动控制器和路径进行了联合优化.所提优化算法在挠性航天器姿态控制的高维多目标优化问题中引入偏好信息,改变了传统的仅依赖于Pareto优于关系来比较个体优劣的方法.通过对种群的生成规律进行改进,该算法可以保证优化解集的有效性和多样性.仿真结果表明了所提方法的有效性.To relieve the contradiction between rapid maneuvering performance and high stabilization performance in large angle maneuvering of flexible spacecraft, the high dimensional multi-objective optimization of the large angle rapid maneuvering control for flexible spacecraft is studied under model parametric uncertainties and external disturbances in space. Based on dynamics analysis of flexible spacecraft, a robust attitude maneuvering control strategy is designed. By analyzing the vibration excitation of flexible appendages with profile planning, a profile with smooth jerk is planned. A high dimensional multi-objective optimization model of flexible spacecraft is constructed. Based on an improved r-dominance multi-objective sorting evolutionary algorithm, the controller and the profile proposed are optimized simultaneously. By introducing preference information into high-dimensional optimization problem, the optimization algorithm proposed above transforms a normal method with which individuals are ranked by Pareto superior relationship. Also, the management of population is improved to ensure the usefulness and the diversity of the solutions obtained. The simulation results demonstrate the effectiveness of the method proposed.

关 键 词：挠性航天器 姿态机动 多目标优化 进化算法 

分 类 号：TP18[自动化与计算机技术—控制理论与控制工程]