小型月球探测器主动章动控制

摘要

小型月球探测器由地球停泊轨道向地月转移轨道射入时，要求采用自旋稳定来建立发动机 的 点火姿态。由于细长体和能量耗散的存在，导致了自旋运动的发散—章动运动，为此采用两 种工程上常用的喷气主动控制方法设计了主动章动控制器。针对两种方法消耗燃料比较大的 缺点，提出了一种模糊喷气主动章动控制方法。%Spin stability is taken for the small lunar explorer to build up the solid m otor firing attitude when it was injected from the Earth-berth orbit to the Ear t h-Moon transfer orbit. The prolate body and the energy dissipation lead to the i nstability of the spinning. Two common control scheme was used to design the active nutation controller. For the disadvantage of wasting fuel, a f uzzy active nutation control scheme was proposed. The three schemes were all giv en the numerical simulation result.