The invention relates to the technical field of spacecraft attitude control, and discloses a micro-electric propulsion-based high-precision attitude control method, which comprises the following steps of S1, acquiring current attitude information of a spacecraft by using an attitude sensor; s2, based on the measured attitude information, using an attitude estimation algorithm to predict the attitude of the spacecraft; s3, calculating a required thrust instruction through an attitude control algorithm; the thrust instruction obtained through calculation is converted into a control signal of the micro-electric thruster; s4, implementing a corresponding thrust instruction according to the control signal to realize accurate attitude control of the spacecraft, and S5, performing attitude measurement again after the thrust instruction is implemented, and comparing a measurement result with an expected attitude. By fusing a microelectronic technology and a control system, real-time high-precision attitude control of the spacecraft is realized, the stability and the performance are improved, a micro electric propulsion method is adopted to provide large specific impulse thrust for the spacecraft, the task execution efficiency is remarkably improved, the orbit service life is remarkably prolonged, and meanwhile, the energy consumption is reduced.
本申请涉及航天器姿态控制技术领域,公开了基于微电推进的高精度姿态控制方法,包括以下步骤:S1、使用姿态传感器获取航天器当前的姿态信息;S2、基于测量到的姿态信息,使用姿态估计算法对航天器的姿态进行预测;S3、通过姿态控制算法计算出所需的推力指令;将计算得到的推力指令转化为微电推进器的控制信号;S4、根据控制信号实施相应的推力指令,实现航天器的精确姿态控制,S5、在推力指令实施后重新进行姿态测量,并将测量结果与期望姿态进行比较。通过融合微电子技术和控制系统,实现航天器实时高精度姿态控制,提升稳定性和性能,采用微电推进方法为航天器提供大比冲推力,显著提高执行任务效率和轨道寿命,同时降低能耗。
High-precision attitude control method based on micro electric propulsion
基于微电推进的高精度姿态控制方法
2024-04-30
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
Pico-satellite orbit and attitude control by electric propulsion
Tema Archive | 2014
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