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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。
Based on Zero Propellant Maneuver (ZPM) technology and thruster technology, a new concept of large-angle attitude maneuver of space station-Control Momentum Gyroscopes Assisting Maneuver (CMGs AM )technology. In this paper, the CMGs AM fuel optimal control model is given. Based on the analysis of fuel optimal control structure, the optimal maneuvering problem of CMGs AM fuel is solved by the solution method based on improved pseudo-spectral node method. Comparisons of thruster-only fuel optimal solutions with those at the space station around the characteristic axes show that CMGs AM technology offers greater fuel savings relative to thruster maneuvers and at the same time achieves maneuvering momentum management Smooth connection; Compared with the ZPM maneuver, its maneuvering time is greatly shortened, and at the same time, it has stronger ability to resist interference. The CMGs AM technology enables efficient integration of thruster technology and zero-fuel maneuvering technology, further enriching the space station’s high-angle maneuvering technology.