应用变速控制力矩陀螺的微小卫星大角度姿态机动控制

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. 

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

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 intro- duced 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 ac- tuators 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 actua- tor 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 demon- strate the effectiveness and robust performance of the proposed nonlinear feedback control system.