郑州大学学报（工学版）2018，Vol.39Issue(3)：56-61,6.DOI:10.13705/j.issn.1671-6833.2017.06.015
含扁率的希尔型三体系统太阳帆悬浮轨道设计
Design of Displaced Orbits for Solar Sail in Hill's Restricted Three-body Problem with Oblateness
摘要
Abstract
The solar sail displaced orbits in the Hill's restricted three-body problem was investigated,where the larger primary was an oblate spheroid in the system.Firstly,the model of solar sail equipped with a new version of reflectance control device was introduced.Next,dynamical model of the system with the larger primary an oblate spheroid was established and the Hill's restricted three-body problem with oblateness was built through appropriate simplifications.The collinear equilibrium points of the Hill's system varying with the variations of areas of absorption and thermal radiation of reflectance control devices in the solar sail,or the dimensionless characteristic acceleration of solar sail,or the oblateness of the larger primary were also investigated.Then,Linearization near the collinear equilibria of the system was applied.A linear quadratic regulator was used to stabilize the nonlinear system.The simulation revealed that solar sail displaced orbits in this system were doable and asymptotically stable by means of adjusting the pitch angle of solar sail and the area of absorption in reflectance control devices.关键词
太阳帆/悬浮轨道/反射控制设备/希尔型限制性三体问题/扁率Key words
solar sail/displaced orbits/reflectance control devices/hill's restricted three body problem/oblateness分类
航空航天引用本文复制引用
宋明,和兴锁,闫业毫,和东生..含扁率的希尔型三体系统太阳帆悬浮轨道设计[J].郑州大学学报（工学版）,2018,39(3):56-61,6.基金项目
国家自然科学基金资助(10672133) （10672133）
