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针对太阳高纬度探测器轨道设计任务要求,研究了基于多目标遗传算法的小推力借力飞行轨道设计方法基于圆锥曲线拼接假设,将探测器轨道分为小推力日心转移轨道段和木星借力飞行轨道段两部分.在日心转移轨道段,选择燃料最省为优化目标,采用标称轨道法设计小推力的推力控制率.在借力飞行轨道段,选择借力后日心轨道倾角为优化目标,对借力飞行的关键参数进行分析.采用多目标遗传算法对该多目标进行了优化.结果表明,多目标遗传算法可以有效地解决轨道设计中的多目标优化问题.优化得到的小推力控制率不仅可以节省发射能量,还可以保证借力飞行后探测器能够进入太阳高纬度探测轨道.
According to the mission requirements of high latitude detector orbit, the design method of small-thrust leap-orbit based on multi-objective genetic algorithm is studied based on conic spline assumption. The orbit is divided into small thrust heliostat transfer orbit and Jupiter leveraging Flight orbit section in the heliocentric transition orbit section, select the fuel province as the optimization objective, the use of nominal orbit thrust control thrust design of small thrust in the orbit paragraph, select the leveraging of orbital orbit angle of Optimize the target and analyze the key parameters of leveraging flight.The multi-objective genetic algorithm is used to optimize the multi-objective.The results show that the multi-objective genetic algorithm can effectively solve the multi-objective optimization problem in orbit design.Optimization of the small Thrust control rate can not only save the launch energy, but also can ensure that the detector will be able to enter the sun’s high latitude detection orbit by leveraging the flight.