控制力矩陀螺辅助的空间站大角度姿态机动

在推力器机动技术与零燃料机动(Zero Propellant Maneuver,ZPM)技术的基础上,提出了一种新的空间站大角度姿态机动技术概念——控制力矩陀螺辅助机动(Control Momentum Gyroscopes Assisting Maneuver,CMGs AM)技术。文章给出了CMGs AM燃料最优控制问题模型,在对燃料最优解控制结构分析的基础上,采用基于改进的伪谱结点法的求解策略,求解了CMGs AM燃料最优机动问题,与仅基于推力器机动的燃料最优解和空间站上的绕特征轴的常速率机动进行了比较,结果表明相对于推力器机动,CMGs AM技术更加节省燃料,并同时实现了机动始末动量管理模式的光滑连接;相对于ZPM机动,其机动时间大大缩短,同时具有更强的抵御干扰的能力。CMGs AM技术实现了对推力器技术与零燃料机动技术的高效综合,进一步丰富了空间站大角度机动技术。

Study of control momentum gyroscopes assisting maneuver

A new large-angle space station attitude maneuver technique concept: Control Momentum Gyroscopes Assisting Maneuver (CMGs AM) technique is proposed, which employs both the Control Moment Gyroscopes (CMGs) and the thruster Reaction Control System (RCS) as the actuator. The fuel-optimal control problem of CMGs AM is formulated, using a two-step solving strategy which utilizes an improved pseudo spectral knotting method, the fuel-optimal solution is obtained, the results are compared to the fuel-optimal solution and constant-rate eigenaxis maneuver of thrust maneuver technique. It is shown that the CMGs AM technique inherits and further enhances the advantages of thruster maneuver and Zero Propellant Maneuver (ZPM) techniques. It significantly saves fuel compared as the thrust maneuver and shortens the maneuver time greatly with greater robustness compared to ZPM.