一种皮纳卫星MEMS固体微推力器阵列联合姿态控制的高精度方法

To achieve high precision attitude control for the pico-and nano-satellite at low cost, this paper presents a coordinated control method of double actuators using flywheel and solid propellant microthruster (SPM) array. The global fast terminal sliding mode controller is adopted to solve the rapid maneuvering of disturbed pico-and nano-satellite, which is verified by the Lyapunov stability. Meantime, the energy optimal switching strategy is derived, namely, the three sections of individual flywheel control, flywheel and SPM array coordinated control and individual SPM array control. In this way, the dual effects of high attitude stability precision and global minimum consumption of SPM array are realized. In this paper, the Monte Carlo method is used to optimize the allocation matrix in order to arrange the ignition sequence reasonably and minimize the consumption of the SPM array. The results of numerical simulation show that the coordinated control method of double actuators enables the pico-and nano-satellite complete high precision attitude control tasks at low cost, the attitude angle precision is 0.045 7°, and the attitude angular rate precision is 0.006 2 (°)/s.