敏捷小卫星姿态控制律和操纵律一体化设计

Integrated attitude control algorithm and steering law for agile small satellites

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.

Abstract:

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.