一种挠性航天器姿态快速平稳机动的控制方法  

Attitude control for flexible spacecraft rapid and steady maneuver

作　　者：林炳[1] 郭毓[1] 钟晨星[1] 余臻[1] 

机构地区：[1]南京理工大学自动化学院,江苏南京210094

出　　处：《华中科技大学学报（自然科学版）》2013年第S1期51-54,共4页Journal of Huazhong University of Science and Technology(Natural Science Edition)

基　　金：国家自然科学基金资助项目(60975075);江苏省普通高校研究生科研创新计划资助项目(CXLX13190)

摘　　要：针对挠性航天器姿态机动过程中的振动抑制问题,提出了一种新的姿态控制方法.通过对闭环系统的柔性模态设计输入成形器,抑制挠性附件的振动;在此基础上,设计一种包含机动时间、稳定时间及模态振动能量的优化性能指标,选取闭环系统的刚体模态阻尼比,并优化反馈控制参数,保证刚体运动的平稳性.仿真结果表明所提方法可提高挠性航天器姿态机动的性能.A new attitude control approach was proposed to reduce flexible appendages vibration during spacecraft attitude maneuver.In order to suppress appendages′vibration,an input shaper was designed for flexible modes of closed loop system.Based on this,an optimization performance index consisting of maneuver time,stabilization time and modal vibration energy was designed for choosing rigid-body′s damping ratio of closed loop system and optimizing feedback control parameters,which improved the stability of rigid body motion.Simulation results show that the performance of flexible spacecraft attitude maneuver can be improved obviously by using the control law.

关 键 词：挠性航天器 反馈控制 振动抑制 快速平稳机动 输入成形 优化性能指标 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]