引用本文:
【打印本页】   【HTML】   【下载PDF全文】   查看/发表评论  【EndNote】   【RefMan】   【BibTex】
←前一篇|后一篇→ 过刊浏览    高级检索
本文已被:浏览 2151次   下载 1546 本文二维码信息
码上扫一扫!
分享到: 微信 更多
全星历模型下拟Halo轨道设计
杨洪伟, 李京阳, 宝音贺西
清华大学航天航空学院, 北京 100084
摘要:
本文给出了全星历模型下适用于地月系统和日地系统的拟Halo轨道的设计方法。设计过程以限制三体模型下Halo轨道作为初值并以多点并行打靶法求解全星历模型下拟Halo轨道。采用多点并行打靶法中给出了一类新的可行约束条件,在数值仿真算例中,地月和日地系统L2点附近4圈目标拟Halo轨道均在分钟量级时间内收敛,表明了算法的有效性。
关键词:  全星历模型;打靶法;Halo轨道;轨道设计
DOI:10.15982/j.issn.2095-7777.2015.04.006
分类号:
基金项目:
Quasi Halo Orbit Design in Full Ephemeris Model
YANG Hongwei, LI Jingyang, BAOYIN Hexi
School of Aerospace Engineering, Tsinghua University, Beijing 100084, China
Abstract:
A method of designing the quasi Halo orbits in the full ephemeris model, which can be applied in both the earth-moon system and sun-earth system, is presented. In the design process, a Halo orbit designed in the restricted three-body model is taken as initial guess, and then a multiple shooting method is used to design in the full ephemeris model. A new feasible constraint condition is given. By numerical simulations, the quasi Halo orbits with four circles are both obtained about one minute for the earth-moon system and sun-earth system respectively, showing the effectiveness of the present algorithm.
Key words:  full ephemeris model;shooting method;Halo orbit;orbit design