充液挠性航天器姿态机动控制的多目标优化  

Multi-objective Optimization for the Attitude Maneuver Control for Liquid-Filled Flexible Spacecraft

作　　者：朱锐 郭毓[1] 王璐 钟晨星 ZHU Rui;GUO Yu;WANG Lu;ZHONG Chenxing(School of Automation,Nanjing University of Science and Technology,Nanjing 210094,Jiangsu,China;Nanjing Research Institute,HUAWEI Technology Limited Liability Company,Nanjing 210012,Jiangsu,China;The 29th Research Institute of China Electronics Technology Group Corporation,Chengdu 610036,Sichuan,China)

机构地区：[1]南京理工大学自动化学院,江苏南京210094 [2]华为技术有限公司南京研究所,江苏南京210012 [3]中国电子科技集团公司第二十九研究所,四川成都610036

出　　处：《上海航天（中英文）》2020年第1期11-17,共7页Aerospace Shanghai（Chinese&English）

基　　金：国家自然科学基金资助项目(61973167,61773211);江苏省重点研发计划资助项目(BE2017161);江苏高校优势学科建设工程资助项目(AD20540)

摘　　要：针对充液挠性航天器姿态快速机动、快速稳定的控制要求,为减小姿态机动对挠性附件振动和液体晃动的激发,设计了一种基于正弦型加加速度的姿态机动路径规划方法。为进一步提高姿态控制性能,提出了一种基于云多目标粒子群算法的姿态控制器参数和机动路径参数联合优化方法。以最小化充液挠性航天器三轴姿态达到指定指向精度的时间以及三轴姿态稳定度,构建多目标优化模型,并应用云多目标粒子群算法求取姿态控制器参数和机动路径参数的Pareto最优解。仿真结果表明:采用多目标联合优化算法得到的控制器与路径参数,能够有效减小液体晃动和挠性附件振动,显著提高充液挠性航天器大角度姿态机动的快速性和稳定性。In view of the control requirements of fast maneuvering and stabilizing of the liquid-filled flexible spacecraft,in order to reduce the inducement of attitude maneuver to the vibration of flexible appendages and liquid sloshing,an attitude maneuver path planning method based on a sinusoidal acceleration is designed.To improve the attitude control performance further,a joint optimization algorithm of attitude controller parameters and maneuvering path parameters based on the cloud multi-objective particle swarm optimization(CMOPSO)algorithm is proposed.A multi-objective optimization model is built to minimize the time for the three-axis attitude of the spacecraft to reach the specified pointing accuracy and the stability of the three-axis attitude,and the optimal Pareto solutions of the attitude controller parameters and maneuvering path parameters are obtained by use of the CMOPSO algorithm.The simulation results show the rapidity and stability of the large angle attitude maneuver of the liquid-filled flexible spacecraft with the optimized controller and maneuver path parameters are significantly improved,as well as the liquid sloshing and flexible appendage vibration have been effectively reduced.

关 键 词：充液挠性航天器 姿态机动 大角度 路径规划 云多目标粒子群优化 

分 类 号：TP412.42[自动化与计算机技术]