The invention discloses a thrust on-orbit calibration test method, belongs to the technical field of spacecraft electric propulsion, and can solve the problem that an existing on-orbit calibration test method is relatively large in deviation, so that the control precision of a micro thruster on an orbit is relatively low. The method comprises the following steps: when the number of running turns of a satellite is an even number of turns, applying thrust to the satellite to obtain a non-thrust acting ring and a thrust acting ring of the satellite; obtaining a thrust estimated value range of thethruster according to the average orbit semi-major axis of the thrust-free action ring and the thrust action ring adjacent to the thrust-free action ring; obtaining prediction positions of all sampling points according with the thrust estimation value range according to the orbit dynamics model; according to the prediction positions and the actual measurement positions of all the sampling pointsin each thrust application time period, obtaining a thrust optimal estimation value in each thrust application time period; and obtaining thrust calibration information of the thruster according to the thrust optimal estimation value. The on-orbit calibration test method is used for on-orbit calibration of the thrust of the satellite thruster.
本发明公开了一种推力在轨标定试验方法,属于航天器电推进技术领域,能够解决现有的在轨标定试验方法偏差较大,导致微推力器对轨道的控制精度较低的问题。所述方法包括:在卫星运行圈数为第偶数圈时,向卫星施加推力,以获得卫星的无推力作用圈和有推力作用圈;根据无推力作用圈和紧邻其后的有推力作用圈的平均轨道半长轴,获得推力器的推力估计值范围;根据轨道动力学模型获得符合推力估计值范围的所有采样点的预测位置;根据每个推力施加时段内所有采样点的预测位置和实测位置,获得每个推力施加时段内的推力最优估计值;并根据推力最优估计值获得推力器的推力标定信息。本发明用于卫星推力器推力在轨标定。
Thrust on-orbit calibration test method
一种推力在轨标定试验方法
2021-02-02
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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