The invention relates to a micro-thrust on-orbit calibration method suitable for a drag-free control spacecraft. The spacecraft comprises a plurality of micro-Newton-level micro-thrusters used for spacecraft attitude control. Comprising the following steps: S1, observing the angular acceleration of a spacecraft by using an angular acceleration observer; S2, calculating a measurement matrix of the spacecraft at the current moment according to the dynamics of the drag-free spacecraft; S3, calculating a gain matrix of the spacecraft according to the measurement matrix of the spacecraft at the current moment; s4, calculating a spacecraft covariance matrix according to the current moment gain matrix of the spacecraft; s5, calculating a micro-thruster calibration value according to the spacecraft gain matrix and the covariance matrix; s6, updating the nominal parameter matrix of the micro-thruster according to the estimated value of the micro-thruster; s7, the nominal force and torque of the micro-thruster are deconstructed to estimate parameters of the micro-thruster; and S8, the parameters of the micro-thruster are fed back to the spacecraft for adjustment. The method has the beneficial effects that the method is suitable for real-time accurate calibration of the multi-thruster state and thrust during the on-orbit period of the drag-free control spacecraft.
本发明涉及一种适用于无拖曳控制航天器的微推力在轨标定方法,所述航天器包括若干用于航天器姿态控制的微牛级微推力器;包括以下步骤:S1、使用角加速度观测器观测航天器角加速度:S2、根据无拖曳航天器动力学计算航天器当前时刻量测矩阵:S3、根据航天器当前时刻量测矩阵计算航天器增益矩阵;S4、根据航天器当前时刻增益矩阵计算航天器协方差矩阵;S5、根据航天器增益矩阵和协方差矩阵计算微推力器标定值;S6、根据微推力器估计值更新微推力器标称参数矩阵;S7、解构微推力器标称力与力矩估算微推力器参数:S8、将微推力器参数反馈给航天器进行调整。有益效果是适用于无拖曳控制航天器在轨期间多推力器状态和推力实时精确标定。
Micro-thrust on-orbit calibration method suitable for drag-free control spacecraft
一种适用于无拖曳控制航天器的微推力在轨标定方法
2024-09-27
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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