基于特征模型的挠性航天器接触消旋控制  

Contact Detumbling Control of Flexible Spacecraft Based on Characteristic Model

作　　者：李超 何英姿 胡勇[1,2] LI Chao;HE Yingzi;HU Yong(Beijing Institute of Control Engineering,Beijing 100094,China;Science and Technology on Space Intelligent Control Laboratory,Beijing 100194,China)

机构地区：[1]北京控制工程研究所,北京100094 [2]空间智能控制技术重点实验室,北京100094

出　　处：《空间控制技术与应用》2022年第2期54-61,共8页Aerospace Control and Application

基　　金：国家自然科学基金资助项目(62003034)和(U20B2054)。

摘　　要：高价值失效卫星是在轨服务的重点目标,一般具有大的挠性和剩余角动量.直接采用机械臂抓捕目标具有碰撞风险.如果预先采用接触式消旋衰减目标角速度,会极大提高服务卫星抓捕目标的成功率.针对含有挠性振动的非合作失效卫星接触消旋控制问题,提出一种基于特征模型的挠性振动抑制方法.基于消旋动力学方程建立挠性振动角速度的特征模型,设计基于特征模型的自适应挠性振动抑制器进行数值仿真,验证了该方法对挠性振动抑制的有效性.High-value failed satellites are key targets for in-orbit service and generally have large flexibility and residual angular momentum.Using robotic arms to directly capture the target has the risk of collision.If the contact detumbling is used to reduce the target angular velocity in advance,the success rate of the service satellite to capture the target can be greatly improved.Aiming at the problem of contact detumbling control of non-cooperative failed satellites with flexible vibrations,a flexible vibration suppression method based on the characteristic model is proposed.Firstly,the characteristic model of the flexible vibration angular velocity is established based on the contact dynamic equation.Then the adaptive flexible vibration suppressor based on the characteristic model is designed.Finally,the numerical simulation is carried out.The simulation results show that the method can effectively suppress the flexible vibration of the target during the detumbling process.

关 键 词：失效卫星 接触式消旋 振动抑制 特征模型 自适应控制 

分 类 号：V19[航空宇航科学与技术—人机与环境工程]