The invention relates to an optimal small-thrust transfer segmentation design method for translation point orbit. The method comprises the following steps: a, establishing a kinetic equation of an aircraft under a centroid rotating coordinate system; b, determining the invariant manifold of the translation point orbit; c, determining an initial value of a design variable through global search; andd, determining an optimal transfer track through local optimization. The method is based on a three-body system. Global search is carried out in combination with the invariant manifold; an appropriate splicing point position and a design variable initial value are rapidly determined; then, the optimal small-thrust transfer track of the fuel is solved through local optimization, the transfer design of the detector between translation points of the system is achieved, the problems of small-thrust near-earth multi-circle divergence and initial values can be effectively solved, the application range is wide, and the method can be suitable for transfer design of translation point tracks of an earth-moon L1 point, a sun-earth L1 point and an L2 point.
本发明涉及一种平动点轨道最优小推力转移分段设计方法,包括以下步骤:a、在质心旋转坐标系下建立飞行器的动力学方程;b、确定平动点轨道的不变流形;c、全局搜索确定设计变量的初值;d、局部优化确定最优的转移轨迹。本发明基于三体系统,结合不变流形进行全局搜索,快速确定合适的拼接点位置与设计变量初值,然后局部优化求解燃料最优小推力转移轨迹,实现探测器在系统平动点间的转移设计,能够有效地解决小推力近地多圈发散与初值问题,适用范围广,能够适用于地月L1点、日地L1点与L2点的平动点轨道的转移设计。
Optimal small-thrust transfer segmentation design method for translation point orbit
平动点轨道最优小推力转移分段设计方法
2020-12-01
Patent
Electronic Resource
Chinese
Optimal, Low-Thrust, Earth-Moon Orbit Transfer
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