The invention discloses a control method and device for entering a lunar large elliptical frozen orbit, and the method comprises the steps: carrying out the optimization solving of a far lunar maneuver pulse according to a particle swarm algorithm based on an orbit after the first near lunar braking of a satellite, and obtaining a pulse initial value of the far lunar maneuver. The pulse initial value of the far-moon maneuver represents the speed increment initial value of the satellite at the initial value of the far-moon maneuver moment. When the terminal parameter deviation corresponding to the pulse initial value is smaller than a threshold value, according to the pulse initial value of the far-moon maneuver and the target semi-major axis initial value of the second-time near-moon braking, combined planning is conducted on the far-moon maneuver and the second-time near-moon braking based on the Newton iteration method, and when the orbit parameter deviation at the third-time near-moon point moment is smaller than a convergence threshold value, the far-moon maneuver and the second-time near-moon braking are completed. The control parameters of far-moon maneuver and the control parameters of second-time near-moon braking are determined, the control parameters of third-time near-moon braking are calculated, and the control parameters for entering the lunar large elliptical frozen orbit are accurately calculated.
本发明公开了一种进入月球大椭圆冻结轨道的控制方法和装置,包括:基于卫星的第一次近月制动后的轨道,根据粒子群算法对远月机动脉冲进行优化求解,得到远月机动的脉冲初值。远月机动的脉冲初值表示在远月机动时刻的初值时卫星的速度增量初值。当脉冲初值对应的终端参数偏差小于阈值时,根据远月机动的脉冲初值和第二次近月制动的目标半长轴初值,基于牛顿迭代法对远月机动和第二次近月制动进行联合规划,直至第三次近月点时刻的轨道参数偏差小于收敛门限时,确定出远月机动的控制参数和第二次近月制动的控制参数,并计算出第三次近月制动的控制参数,实现精确计算出进入月球大椭圆冻结轨道的控制参数。
Control method and device for entering large elliptical frozen orbit of moon
一种进入月球大椭圆冻结轨道的控制方法和装置
2025-05-13
Patent
Electronic Resource
Chinese
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