木卫停泊轨道间低耗能小推力转移轨道设计方法研究  

DESIGN METHODS FOR LOW-ENERGY LOW-THRUST TRANSFER ORBIT BETWEEN PARKING ORBITS AROUND JOVIAN MOONS

作　　者：路毅[1] 李俊强 韩雷 李兆明 李恒年[1] 曹璐[1] 候俊楠 LU Yi;LI Junqiang;HAN Lei;LI Zhaoming;LI Hengnian;CAO Lu;HOU Junnan(Xi'an Satellite Control Center, S tate Key L aboratory of A stronautic Dynamics(ADL), X i'an 710043, China;Unit 63778 of PLA, Jiamusi 154000, Heilongjiang, China)

机构地区：[1]西安卫星测控中心,宇航动力学国家重点实验室,西安710043 [2]63778部队,黑龙江佳木斯154000

出　　处：《力学与实践》2016年第5期501-510,共10页Mechanics in Engineering

基　　金：中国国家高技术研究发展计划(2010AA7040014);中国青年自然科学基金(61503414);宇航动力学国家重点实验室开放基金(2016ADLDW0202)资助

摘　　要：对木卫停泊轨道间的低耗能小推力转移轨道设计方法进行了研究,提出基于"类halo轨道截面"法的低耗能转移轨道参数化方法和基于配点法的多体Lambert问题求解算法,并利用全局优化算法得出了燃耗最少的初步优化结果;利用多体同伦法和固定近心点高度的多圈转移控制律得到了各段小推力转移轨道的有效设计结果.所提方法同样适用于其他天体间的转移轨道设计,为多体环境下低耗能小推力转移轨道提出了新的设计思路和方法.propose a novel method for low-energy low-thrust transfer orbit between parking orbits around Jovian moons. Using a “halo-like section”, the manifold is simply parameterized and patched by the multibody Lambert algorithm based on collocation method. Then by using the global optimization algorithm, a preliminary optimization result is obtained with minimal fuel consumption. The transfer orbits with lowthrust propulsion are optimized and designed by the homotopic method with multi-body environment and the multi-circle transfer orbit design method with fixed perigee height. The proposed method may be applied to transferring orbit design between other celestial bodies. In summary, we have proposed new design ideas and methods for low-energy low-thrust transfer orbit with multi-body environment.

关 键 词：木卫 低耗能 小推力 轨道设计 多体环境 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]