挠性航天器旋转机动的输入成形变结构控制  

Sliding mode with reference input-shaping control design for flexible spacecraft slewing maneuvers

作　　者：王庆超[1] 岑小锋[1] 马兴瑞[2] 

机构地区：[1]哈尔滨工业大学航天学院,黑龙江哈尔滨150001 [2]中国航天科技集团公司,北京100830

出　　处：《系统工程与电子技术》2006年第5期727-730,共4页Systems Engineering and Electronics

基　　金：国家自然科学基金(60274002)资助课题

摘　　要：研究了挠性航天器单轴旋转机动的输入成形变结构控制方法。该方法首先根据带扰动估计的滑模控制(SMCPE)方法,导出了针对刚体模型设计的、对系统模型不确定性以及非线性扰动具有较强鲁棒性的SM-CPE控制律,并在分析等效系统的基础上,提出了基于输入成形的变结构控制方案。该方案通过指令的输入成形,使得航天器能按照指定的性能机动,同时对机动过程中的弹性振动和残余振动具有较快的抑制作用。指令的输入成形是通过不断地改变滑动模超平面实现的,本文给出了一种改变该超平面的分段取固定值的算法。同时给出了设计该控制律的数字仿真实例,并作了比较,仿真结果验证了该设计的有效性。An approach for generating a robust tracking controller for flexible spacecraft rest-to-rest slewing maneuvers is presented with the objective insensitivity to modeling errors, parameter uncertainty and minimizing the residual energy of the flexible modes. The method is based on combine the sliding mode control with perturbation estimation （SMCPE） and reference input-shaping approach for the rigid-body mode. The combination of two methods is accomplished through changing the sliding hyperplanes by shaping the reference input directly. The IS-SMCPE is enforced in paper shows a robust tracking and lead to a smooth control input which is less likely to excite the structure modes during maneuvers than sudden change of bang-bang at a switching time. This resulting changing sliding hyperplances problem is solved using the simple shooting method. The capability of this approach is demonstrated though a numerical example in detail.

关 键 词：滑模控制 输入成形 挠性航天器 姿态机动 

分 类 号：V448.222[航空宇航科学与技术—飞行器设计]