应用变速控制力矩陀螺的微小卫星大角度姿态机动控制  

Attitude Control of Large Angle Maneuver for Microsatellite Using Variable Speed Control Moment Gyros

作　　者：刘军[1] 韩潮[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《空间科学学报》2007年第4期336-341,共6页Chinese Journal of Space Science

摘　　要：研究了变速控制力矩陀螺(VSCMG)作为执行机构的微小卫星多目标快速姿态机动的控制问题.控制力矩陀螺(CMG)可以在不增加功耗、质量和体积的条件下为微小卫星提供独特的控制力矩、角动量和姿态机动能力,这有助于微小卫星变得更加机动灵活.首先建立了以变速控制力矩为执行机构的航天器姿态动力学模型,采用修正Rodrigues参数描述姿态.在考虑执行机构饱和、机动速率限制、控制带宽限制等情况下,设计了基于Lyapunov理论的非线性姿态反馈控制器.以采用VSCMG为执行机构的某微小卫星为例进行了数值仿真,结果表明卫星在机动中达到了快速和稳定的要求,提出的非线性姿态反馈控制器有很好的鲁棒性和有效性.The multi-projects rapid attitude maneuver problem for agile microsatellites with VSCMG （Variable Speed Control Moment Gyros） as actuators was investigated. VSCMG is a recently introduced actuator for spacecraft attitude control, and it is a hybrid one between two types of internal torque generators; namely, a conventional control moment gyro and a reaction wheel. These actuators can provide unique torque, angular momentum and slew rate capabilities to microsatellites without any increase in power, mass or volume. This will help microsatellites become more agile. The attitude dynamic equation of a spacecraft with VSCMG attached was presented, the attitude was described by MRP （Modified Rodrigues Parameters）. A nonlinear feedback controller based on Lyapunov stability condition was developed under various physical constraints, including the actuator saturation, slew rate limit, control bandwidth limit, etc. A numerical simulation was presented on the sample of the attitude maneuver of a microsatellite with VSCMG. Simulation results demonstrate the effectiveness and robust performance of the proposed nonlinear feedback control system.

关 键 词：微小卫星 变速控制力矩陀螺 姿态机动 修正的Rodrigues参数 

分 类 号：V441[航空宇航科学与技术—飞行器设计] V448.2