轨控大干扰下的系统角动量管理  

Momentum Management for a Momentum Exchange Device System with Large Disturbance Torque in Orbit Control Process

作　　者：王淑一[1,2] 雷拥军[1,2] 王新民[1,2] 袁军[1] WANG Shuy;LEI Yongjun;WANG Xinmin;YUAN Jun(Bejing Institute of Control Engineering, Beijing 100094, China;Science and Technology on Space Intelligent Control Laboratory, Beijing 100094, China.)

机构地区：[1]北京控制工程研究所,北京100190 [2]空间智能控制技术重点实验室,北京100190

出　　处：《空间控制技术与应用》2018年第2期19-24,共6页Aerospace Control and Application

基　　金：国家杰出青年科学基金资助项目(61525301)~~

摘　　要：针对利用角动量交换装置系统实现轨控期间姿态维持的情况,研究当轨控推力器存在大力矩扰动时系统角动量管理方法.结合对地运行航天器轨道运动特性,分析轨控干扰力矩的积累角动量变化规律;考虑角动量管理装置系统的角动量存贮容量,基于角动量积累规律提出了一种结合偏置角动量建立与对称分布轨控位置选择的系统角动量管理方法,实现了对称轨控位置积累角动量互相抵消的自平衡效果,极大程度地提高轨控效率且避免系统角动量饱和现象.所提出的方法适用于喷气欠驱动控制系统,方法的有效性通过了数学仿真验证及在轨型号应用.For attitude keeping control with momentum exchange device system during orbit control stage,the momentum management problem is investigated in the case of the large disturbance resulting from orbit jets. Characteristic of disturbance accumulated momentum is analyzed in detail based on the orbital motion features of the Earth-orienting spacecraft,and then a momentum management method is proposed,which includes establishment of biased momentum and determination of symmetrical distributed orbit control positions to self-counteract the accumulated momentum. With the method utilization,the efficiency of orbit control can be achieved to the maximum degree and meanwhile the momentum saturation phenomenon can be avoided. The proposed method for under-actuated spacecraft attitude control,the effectiveness of the method is demonstrated by the numerical simulation results and the practical application.

关 键 词：航天器 角动量管理 轨道控制 干扰力矩 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]