摘要
针对太阳帆航天器在地月限制性三体问题中的往复巡弋轨道的设计问题,在晕轨道不变流形的基础上,构建混合推进太阳帆动力学转换策略,建立3种返回轨道动力学模型,实现地月空间往复巡弋轨道优化设计,通过数学仿真验证方法的有效性。仿真结果表明,与传统任务相比,混合推进太阳帆可以减少燃料消耗。
This paper proposes an application of the hybrid solar sail dynamics model in the Earth-Moon transfer orbit to achieve the design method of the reciprocal cruising orbit of solar sail spacecraft in Earth-Moon space.Based on the halo orbit invariant manifold,a strategy for hybrid solar sail dynamics conversion is established,and the theoretical methods of the three return orbits are explained.The results of simulation verification show that the hybrid solar sail can realize the reciprocal cruise orbit design based on the halo orbit invariant manifold.Compared with the traditional mission,the hybrid solar sail in this paper can reduce fuel consumption and facilitate recycling.
作者
史晨曦
廖波
尤超蓝
许志豪
SHI Chenxi;LIAO Bo;YOU Chaolan;XU Zhihao(School of Astronautics,Nanjing University of Aeronautics and Astronautics,Nanjing 211100;Shanghai Institute of Satellite Engineering,Shanghai 201109;No.8511 Research Institute of CASIC,Nanjing 211100)
出处
《飞控与探测》
2025年第6期63-70,共8页
Flight Control & Detection
基金
民用航天项目(D010301)。
关键词
地月空间
混合太阳帆
限制性三体问题
晕轨道
不变流形
Earth-Moon space
hybrid solar sail
restricted three-body problem
halo orbits
invariant manifold
