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针对具有开环树状拓扑结构的柔性多体航天器,基于真-伪坐标形式的拉格朗日方程,建立柔性多体航天器的动力学模型,充分考虑了柔性航天器的时变与不确定性的动力学特征,设计了改进的变论域分形模糊控制器,并对该系统进行了仿真验证.仿真结果表明,该方案回避了实时计算收缩因子所导致的论域范围实时收缩的缺点,实现了对柔性多体航天器大角度姿态机动的有效控制,同时保证了航天器柔性附件振动的有效抑制.
Aiming at the flexible multi-body spacecraft with an open-loop dendrimer topology, a dynamic model of a flexible multi-body spacecraft is established based on the Lagrange equation in the form of true-false coordinates. The time variations of the flexible spacecraft are fully considered Deterministic dynamic characteristics, an improved variable universe fuzzy controller is designed and the system is verified by simulation.The simulation results show that the proposed scheme avoids the disadvantage of real-time shrinkage caused by shrinkage factor in real time , Which realizes the effective control of maneuvering large-angle attitude maneuvers of the flexible multi-body spacecraft while ensuring the effective suppression of the vibration of the flexible attachment of the spacecraft.