The invention relates to the technical field of satellite attitude control, in particular to a pulse type magnetic torquer attitude interference suppression method and device. Comprising the following steps: calculating a magnetic unloading moment based on a filtered unloading magnetic moment pulse width, and introducing the magnetic unloading moment into an attitude control system for feedforward compensation; and estimating the residual magnetic control torque by using a residual magnetic control torque estimator, and introducing the estimated residual magnetic control torque into an attitude control closed loop. According to the scheme, firstly, the magnetic unloading torque is introduced into the attitude control system for feed-forward compensation, then after the magnetic unloading feed-forward compensation torque introduced into the attitude control system is deducted, the residual magnetic control torque causing attitude disturbance is estimated, then the attitude control system is introduced to form dual compensation of magnetic disturbance, and the effect of high-stability attitude control is achieved.
本发明涉及卫星姿态控制技术领域,特别涉及一种脉冲式磁力矩器姿态干扰抑制方法和装置。包括:基于滤波后的卸载磁矩脉宽,计算磁卸载力矩,并将磁卸载力矩引入姿控系统进行前馈补偿;利用残余磁控力矩估计器,对残余磁控力矩进行估计,并将估计得到的残余磁控力矩引入姿控闭环。本方案首先将磁卸载力矩引入姿控系统进行前馈补偿,然后在扣除已经引入姿控系统的磁卸载前馈补偿力矩后,对引起姿态扰动的残余磁控力矩进行估计,进而引入姿控系统形成磁扰动的双重补偿,达到高稳定度姿态控制的效果。
Impulse type magnetic torquer attitude interference suppression method
一种脉冲式磁力矩器姿态干扰抑制方法
2024-06-07
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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