第20卷第5期 2012年5月
文章编号
1004-924X(2012)05-1031-10
光学精密工程
Optics and Precision Engineering
敏捷小卫星对地凝视姿态跟踪控制
陈雪芹*，耿云海，王峰，李冬柏
（哈尔滨工业大学卫星技术研究所，黑龙江哈尔滨150080）
Vol.20No.5
May.2012
摘要：研究了基于双框架控制力矩陀螺(DGCMG)的敏捷小卫星对地凝视成像过程中的姿态跟踪控制。首先，根据敏捷小卫星的特点和凝视成像任务露求设计执行机构配置方案。然后，根据轨道信息计算地面凝视目标的相对姿态和角速
态轨道控制系统仿真平台上增加凝视成像任务需求并调整执行机构配置，建立敏捷小卫星姿态控制系统，对文中设计的方案和控制方法进行了数学伤真验证。仿真结果表明，该算法简单有效，能够实现敏捷小卫星对地疑视姿态跟踪，同时
关键词：敏捷卫星；控制力矩陀螺；操纵律；凝视成像；姿态跟踪
中图分类号：V448.22
文献标识码：A
doi;10.3788/OPE,20122005.1031
Staringimagingattitudetracking control of agilesmall satellite
CHEN Xue-qin'，GENGYun-hai，WANGFeng,LIDong-bai
(ResearchCenter of Satellite Technology,Harbin Institute of Technology,Harbin150080,China)
Correspondingauthor,E-mail:crqhit@hit.edu.cn
Abstract: The attitude tracking control of staring imaging of an agile small satellite driven by Double-Gim-baled Control Moment Gyroscopes (DGCMG) was investigated. Firstly， an actuator configuration scheme was developed according to the characteristics of agile satellite and the staring imaging mission requirements. Then, the orbit information was used to compute the relative attitude angle and attitude angular velocity of a staring imaging target with respect to the satellite body reference frame, and the proper control law and steer ing law were introduced to avoid the singularity of Control Moment Gyroscope(CMG). Finally, based on the"SY-3" satellite attitude and orbit control simulation platform, the agile small satellite closed-loop control simulation system was established by taking the mission requirements and the actuator adjustments into ac count and the proposed design scheme and control method were verified in a mathematical simulation. Ob tained results show that the presented solution is effective for staring imaging attitude maneuver control of the agile small satellite and the least gimbal angle rate of DGCMG is the most important factor to determinate atti-tude tracking precision.
Key words: agile satellite; control moment gyroscope; steering law; staring imaging; attitude tracking
收稿日期：2011-12-02；修订日期：2011-12-29，
基金项目：国家高技术863-702基金资助项目（No，2010AA7020101)；国家自然科学基金资助项目（No.60904051，
No.61104026）；教育部博士学科点新教师基金资助项目（No.20092302120067)，微小型航天器技术国防重点学科实验室开效基金资助项目（No.HIT.KLOF.2009096）