摘要
研究了以控制力矩陀螺(CMG)为执行机构的敏捷小卫星姿态控制系统控制律和操纵律的一体化设计.首先,采用4个单框架控制力矩陀螺(SGCMG)构成典型的金字塔构型的CMG,并根据CMG的框架轴轴承会逐步退化建立CMG动力学模型.然后,基于自适应控制思想,设计控制律和操纵律一体化的控制器,同时考虑到为避免CMG奇异性影响,基于Lyapunov理论证明其组成的闭环系统渐近稳定.最后,通过建立敏捷小卫星闭环姿态控制系统对算法进行仿真验证,仿真结果表明该算法简单有效,能够实现敏捷小卫星快速姿态机动.
This paper investigates the integrated attitude control algorithm and steering law for agile small satellites configured with control moment gyroscope（CMG）.Firstly,considering the deterioration over time of the typical pyramid-shaped CMG cluster with 4 single-gimbal CMGs,the CMG dynamic model was built.Then,based on the adaptive control theory,the integrated attitude control algorithm and steering law were designed,and the asymptotic stability of the closed-loop system was proved via Lyapunov analysis.Finally,mathematical simulation has validated the solution in a satellite closed-loop attitude control system,and the simulation shows that the solution is simple and effective for attitude maneuver control of agile small satellites.
出处
《哈尔滨工业大学学报》
EI
CAS
CSCD
北大核心
2012年第1期7-11,共5页
Journal of Harbin Institute of Technology
基金
国家自然科学基金资助项目(60904051
61104026)
教育部博士点新教师基金资助项目(20092302120067)
微小型航天器技术国防重点学科实验室开放基金资助项目(HIT.KLOF.2009096)
关键词
敏捷卫星
控制力矩陀螺
操纵律
姿态机动
agile satellite
control moment gyroscope
steering law
attitude maneuver
