The invention relates to an earth-moon system L1 point translation point orbit-earth low-energy transfer orbit design method, and belongs to the technical field of aerospace. Comprising the steps that a first type of disturbance manifold is generated by increasing an initial perturbation increment, that is, initial speed perturbation is applied to a Halo periodic orbit, so that a spacecraft is rapidly separated from the Halo periodic orbit; taking the states of the initial moment and the end moment as constraint conditions, carrying out optimization solution on the transfer cost, and obtaining maneuvering parameters of the second type of disturbance manifold; when the spacecraft evolves on the first type of disturbance manifold, a second type of disturbance manifold is generated by applying maneuvering parameters on the invariant manifold; and obtaining the L1-earth low-energy transfer orbit of the earth-moon system by combining the first type of disturbance manifold and the second type of disturbance manifold. The problem that the traditional earth-moon translation point invariant manifold cannot reach the vicinity of the earth is solved, and the solution of the optimal transfer orbit is realized.
本发明涉及一种地月系L1点平动点轨道‑地球的低能转移轨道设计方法,属于航空航天技术领域。包括:通过增加初始摄动增量生成第一类扰动流形,即在Halo周期轨道上施加初始速度摄动,使得航天器较快脱离Halo周期轨道;以初始时刻和末端时刻状态为约束条件,对转移成本进行最优化求解,得到第二类扰动流形的机动参数;当航天器在第一类扰动流形上进行演化时,通过在不变流形上施加机动参数生成第二类扰动流形;结合第一类扰动流形和第二类扰动流形,得到地月系统L1‑地球低能转移轨道。解决了传统地月平动点不变流形无法到达地球附近的问题,实现了最优转移轨道的求解。
Design method of earth-moon system L1 point translation point orbit-earth low-energy transfer orbit
一种地月系L1点平动点轨道-地球的低能转移轨道设计方法
2024-11-05
Patent
Electronic Resource
Chinese
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