The invention provides an orbital transfer strategy optimization method and system for orbit injection of a large elliptical frozen orbit satellite, and the method comprises the steps: obtaining a satellite-rocket separation orbit and observation station parameters, calculating the elevation angle of a satellite and an observation station, and determining a pulse ignition true anomaly range meeting the measurement and control requirements; in combination with the pulse ignition true anomaly range, a fuel-saving pulse orbital transfer strategy of the satellite starting from the initial orbit to the target orbit is generated, and orbital transfer speed increment, the ignition position and the number of times of ignition are determined; determining an engine shutdown condition of each orbital transfer and the number of drifting turns between two adjacent orbital transfer; according to a pulse orbital transfer strategy, initial values of the ignition duration, the ignition moment and the thrust direction of each orbital transfer are determined, and the final ignition duration, the ignition moment and the thrust direction of each orbital transfer are determined. The fuel optimal orbit transfer strategy for orbit injection of the large elliptical frozen orbit satellite is designed by adopting a non-apogee double-pulse orbit transfer strategy, and the design method problem of the orbit transfer strategy is solved.
本发明提供了一种用于大椭圆冻结轨道卫星入轨的轨道转移策略优化方法及系统,包括:获取星箭分离轨道和测站参数计算卫星与测站的仰角,进而确定满足测控要求的脉冲点火真近点角范围;结合脉冲点火真近点角范围,生成卫星从初始轨道出发到目标轨道的燃料最省脉冲变轨策略,确定变轨速度增量、点火位置和点火次数;确定各次变轨的发动机关机条件以及相邻两次变轨之间的漂移圈数;根据脉冲变轨策略,分别确定各次变轨的点火时长、点火时刻和推力方向的初值,确定最终的各次变轨的点火时长、点火时刻和推力方向。本发明采用非远地点双脉冲变轨策略来设计大椭圆冻结轨道卫星入轨的燃料最优轨道转移策略,解决了该类轨道转移策略的设计方法问题。
Orbit transfer strategy optimization method for orbit injection of large elliptical frozen orbit satellite
用于大椭圆冻结轨道卫星入轨的轨道转移策略优化方法
2023-12-08
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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