采用动量轮及推进器的微小卫星的姿态机动控制(英文)

Attitude maneuver of micro-satellite using thruster plus bias momentum wheel

提出了一种利用偏置动量轮及推进器实现大角度姿态机动控制的方法。首先建立轨道系下的卫星模型及动量轮推进器的模型,并基于该模型采用动量轮及推进器结合的反馈线性化控制方法,最后设计了大角度机动的参考轨迹。仿真和分析结果表明,文中的控制方法可以在45 s内使卫星机动40°,并在100 s内达到180°大角度,控制精度达到0.4°。可以无需对动量轮进行加减速操作而进行实时的姿态机动。不仅能满足实时性需要,同时可以避免动量轮饱和,降低能源消耗,为微小卫星姿态控制系统的工程实现提供了非常有价值的参考。

The main objective is to develop a combined control method for attitude maneuver of micro-satellite containing thruster and a single pitch bias momentum wheel.Firstly the system model relative to the orbit frame is established including satellite,bias momentum wheel as well as pulse width modulation（PWM） thruster.Based on the model,a controller using feedback linearization method combined with thruster and a bias momentum wheel is designed.Then a reference trajectory is designed for large angle maneuver.The overall simulation and analysis results show that the combined PWM thruster and bias momentum wheel control method can make the satellite maneuver 40°within 45 s and reach large angle of 180° within 100 s,and the control precision is up to 0.4°.It works well in the attitude control both for small angle and large angle maneuver.This control method meets the demand of real-time without the bias momentum wheel to slow-down and speed-up manipulation in the period of attitude maneuver.It can not only satisfy the real-time requirements,but also avoid the saturation of momentum wheel and save the finite fuel reserves.It gives valuable references for designing the attitude control systems of micro-satellite.