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

作　　者：宋明 和兴锁[1] 闫业毫 和东生 SONG Ming;HE Xingsuo;YAN Yehao;HE Dongsheng(School of Mechanics And Civil ＆ Architecture,Northwestern Polytechnical University,Xi＇ An 710029,China)

机构地区：[1]西北工业大学力学与土木建筑学院,陕西西安710029

出　　处：《郑州大学学报（工学版）》2018年第3期56-61,共6页Journal of Zhengzhou University（Engineering Science）

基　　金：国家自然科学基金资助(10672133)

摘　　要：在考虑大天体含扁率的情况下,研究了太阳帆在希尔型限制性三体问题的悬浮轨道设计方案.首先介绍一种太阳帆力学模型,这种模型带有改进型的反射控制设备;接着利用一些近似的简化,建立太阳帆在希尔型限制性三体问题系统中的动力学模型.研究发现,改变反射控制设备中吸收光线模块和热辐射模块的面积大小或者改变太阳帆特征加速度或者改变大天体扁率都会引起系统的共线平衡点的位置发生变化.在共线平衡点对系统进行线性化处理,运用线性二次调节器对不稳定的系统进行主动控制.仿真结果表明,通过调节太阳帆姿态角和改变吸收光线模块的面积可以得到太阳帆悬浮轨道并且使其达到渐近稳定.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 

分 类 号：V412.41[航空宇航科学与技术—航空宇航推进理论与工程]