Attitude description and dynamics modeling for Halo-orbit spacecraft
-
摘要: 日地系Halo轨道位于平动点附近,且不存在以地球为中心的轨道平面,这使得Halo轨道探测器的姿态描述和建模问题完全不同于近地卫星.针对三轴稳定方式的探测器,给出了2种姿态描述方案:对日定向方案(方案I,基于日、地敏感器)和旋转坐标系下定向方案(方案II,基于星敏感器).依据两者所定义的不同轨道坐标系,分别建立了姿态动力学模型.分析2类描述方案的相对误差,发现方案I的上限不超过5%,而方案II的上限不超过0.005%.并就方案I设计了姿态镇定控制器,以验证所提出的姿态描述方案的合理性.结果表明:具体工程应用中应以方案II为正常工作模式,并定期修正星历表的误差;方案I作为备份,保证探测器的正常运行.Abstract: Halo orbit locates about the libration point in the Sun-Earth system and has no orbital plane focusing the Earth, which makes the attitude description and dynamics modeling for Halo-orbit spacecraft is quite different from that for the usual satellite around the Earth. Two different schemes of attitude description were proposed for the spacecraft in the three axis stabilization, sun-orienting scheme (Scheme I, using the Sun and Earth attitude sensors) and rotating-reference scheme (Scheme II, using the Star attitude sensor). So the attitude dynamics can be modeled from the different orbital coordinates defined by the two schemes. The upper limits of relative errors for the two schemes were estimated theoretically: no more than 5% for Scheme I, and 0.005% for Scheme II. A controller was designed for the attitude stabilization to validate the feasibility of the schemes. The research shows that Scheme II is set as the normal mode with the astronomical ephemeris periodically corrected, while Scheme I is used as the alternate device for the failure mode.
-
Key words:
- Halo orbit /
- libration point /
- attitude description /
- dynamics modeling
-
[1] Farquhar R W, Dunham D W, Guo Y P, et al. Utilization of libration points for human exploration in the sun-earth-moon system and beyond [J]. Acta Astronautica, 2004, 55:687-700 [2] Richardson D L. Analytical construction of periodic orbits about the collinear points [J]. Celestial Mechanics, 1980, 22:241-253 [3] Mihai P, Vladimir C. The domain of initial conditions for the class of three-dimensional halo periodical orbits [J]. Acta Astronautica, 1995, 36:193-196 [4] 徐明, 徐世杰. 地-月系平动点及Halo轨道的应用研究[J]. 宇航学报, 2006, 27(4):696-699 Xu Ming, Xu Shijie. The application of libration points and halo orbits in the earth-moon system to space mission design [J]. Journal of Astronautics, 2006, 27(4):696-699 (in Chinese) [5] 章仁为. 卫星轨道姿态动力学与控制[M]. 北京: 北京航空航天大学出版社, 1998 Zhang Renwei. Orbit and attitude dynamics and control of satellite [M]. Beijing: Press of Beijing University of Aeronautics and Astronautics, 1998 (in Chinese) [6] Carpenter J R, Folta D C, Moreau M C, et al. Libration point navigation concepts supporting the vision for space exploration Astrodynamics Specialist Conference and Exhibit. Reston: AIAA/AAS, 2004: 179-193 期刊类型引用(3)
1. 艾梦琪，郭保，赵彦. 双机身布局验证机气动特性及横航向飞行品质分析. 飞行力学. 2023(06): 10-15 . 
百度学术2. 陈奎，闫稳，王凌伟，王建生. 一种新型高隐身低阻尼控制系统设计与仿真. 计算机仿真. 2020(06): 30-35 . 百度学术3. 陈俊平，王立新. 低能量状态对飞行安全的危害及改出方法. 航空学报. 2017(08): 66-76 . 百度学术其他类型引用(2)
-
百度学术
点击查看大图
计量
- 文章访问数: 3241
- HTML全文浏览量: 212
- PDF下载量: 1414
- 被引次数: 5
下载:
