多模态充液挠性航天器有限时间控制  

Finite-time control for multiple model liquid-filled flexible spacecraft

作　　者：朱志浩[1] 郭毓[1] 陈庆伟[1] Zhu Zhihao;Guo Yu;Chen Qingwei(School of Automation,Nanjing University of Science and Technology,Nanjing 210094,China)

机构地区：[1]南京理工大学自动化学院,江苏南京210094

出　　处：《南京理工大学学报》2020年第2期134-141,共8页Journal of Nanjing University of Science and Technology

基　　金：国家自然科学基金(61773211,61673214,61673219);江苏省重点研发计划项目(BE2017161);江苏省研究生科研与实践创新计划项目(KYCX18_0430)。

摘　　要：针对多模态充液挠性航天器在有限时间内完成姿态大角度机动等问题,提出了一种有限时间控制方法。为减小航天器机动过程中挠性附件振动和液体晃动强度,设计了一种机动性更加灵活的正弦过渡角机动度七段路径规划方法,把期望信号规划为更加连续光滑的路径,避免了阶跃响应引起的剧烈挠性部件振动和液体晃动。利用输入成型器对路径规划后的期望信号进一步调制,有效抑制了残余振动和液体晃动。最后,通过仿真研究验证了所提控制方法的有效性。In this paper,the problem of attitude large angle maneuver completed in finite-time for the multiple liquid-filled flexible spacecraft is investigated,and a finite-time control algorithm is proposed.Aiming at reducing the flexible appendages’vibration and liquid sloshing during attitude maneuvering of the spacecraft,a sinusoidal angular jerk-based seven segment curve path is designed to smooth the desired attitude and avoid the violent vibration and sloshing resulted by step signal.To further rejecting the residual vibration and sloshing,the input shaper is utilized to modulate the smooth path.Finally,the effectiveness of the proposed finite-time control approach is illustrated by the simulation results.

关 键 词：多模态 充液挠性航天器 有限时间控制 路径规划 输入成型器 

分 类 号：TP273[自动化与计算机技术—检测技术与自动化装置]