The invention provides a method and device for converting a pulse speed increment into a finite thrust orbit control parameter, and relates to the field of orbit maneuver. Comprising the steps that relevant parameters of satellite orbital maneuver in a pulse mode are obtained, an inertial coordinate system is defined, a spherical coordinate system is defined, and the relevant parameters comprise the satellite dry weight # imgabs0 #, the fuel weight # imgabs1 # before maneuver, the fuel weight # imgabs2 # after maneuver, the orbital pulse maneuver moment # imgabs3 #, the speed increment V of the inertial coordinate system and the positions of a satellite and a celestial body; calculating the thrust direction under the spherical coordinate system according to the related parameters; estimating the thrust when the thruster starts to ignite and shut down according to the related parameters, and calculating the starting duration of the limited thrust of the thruster as an initial value of iterative targeting; and taking the starting time length of the limited thrust as an initial value, and finally generating a limited thrust speed direction and starting time length which are equal to the pulse speed increment through continuous iterative targeting. According to the invention, the accuracy degree of track control is increased.
本发明提供一种将脉冲速度增量转换为有限推力轨控参数的方法及装置,本发明涉及轨道机动领域。包括:获取脉冲方式下卫星轨道机动的相关参数,定义惯性坐标系,定义球形坐标系,相关参数包括卫星干重#imgabs0#,机动前燃料重量#imgabs1#,机动后燃料重量#imgabs2#,轨道脉冲机动时刻#imgabs3#,惯性坐标系速度增量V及卫星和天体位置;依据相关参数计算球形坐标系下的推力方向;依据相关参数估算推力器开始点火与关机时的推力大小,计算推力器有限推力的开机时长,作为迭代打靶的初值;依据有限推力的开机时长作为初值,经过不断迭代打靶,最终产生与脉冲速度增量等同的有限推力速度方向与开机时长。本发明增加了轨道控制的精确程度。
Method and device for converting pulse speed increment into finite thrust orbit control parameters
将脉冲速度增量转换为有限推力轨控参数的方法及装置
2025-04-15
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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