全部 标题 作者
关键词 摘要

OALib Journal期刊
ISSN: 2333-9721
费用:99美元

查看量下载量

相关文章

更多...
力学学报  2015 

火星引力捕获动力学与动态误差分析

DOI: 10.6052/0459-1879-14-327, PP. 15-23

Keywords: 火星制动捕获,引力球,作用球,希尔球,误差分析

Full-Text   Cite this paper   Add to My Lib

Abstract:

火星探测的制动捕获机会唯一,是影响任务成败的关键.从限制性三体问题出发,推导了火星引力球、作用球与希尔球半径的计算公式,比较了三者的特点与适用范围,并结合作用球的定义与物理意义,给出了一种火星探测制动捕获段的工程定义.在作用球范围内建立了火星制动捕获段动力学模型,给出了对捕获轨道精度产生影响的各项误差源.通过蒙特卡洛仿真,定量分析了导航初始误差、发动机推力误差、制动点火时间误差等对捕获轨道近火点与远火点高度的影响,并对不同误差源可能导致的超差概率进行了分析,指出了影响捕获精度的主导误差源,可为我国未来火星探测制动捕获段的任务实施提供参考.

References

[1]  刘林, 汤靖师. 火星轨道器运动的轨道变化特征. 宇航学报, 2008, 29(2): 461-466 (Liu Lin, Tang Jingshi. Orbit variation characteristics of the Mars' orbiters. Journal of Astronautics, 2008, 29(2): 461-466 (in Chinese))
[2]  刘林, 赵玉晖, 张巍等. 环火卫星运动的坐标系附加摄动及相应坐标系的选择. 天文学报, 2010, 51(4): 412-421 (Liu Lin, Zhao Yuhui, Zhang Wei, et al. The coordinate additional perturbations to Mars orbiters and the choice of corresponding coordinate system. Acta Astronomica Sinica, 2010, 51(4): 412-421 (in Chinese))
[3]  陈杨, 赵国强, 宝音贺西等. 精确动力学模型下的火星探测轨道设计. 中国空间科学技术, 2012, 1: 8-15 (Chen Yang, Zhao Guoqiang, Baoyin Hexi, et al. Orbit design for Mars exploration by the accurate dynamic model. Chinese Space Science and Technology, 2012, 1: 8-15 (in Chinese))
[4]  李俊峰, 宝音贺西. 深空探测中的动力学与控制. 力学与实践, 2007, 29(4): 1-8 (Li Junfeng, Baoyin Hexi. Dynamics and control in deep space exploration. Mechanics in Engineering, 2007, 29(4): 1-8 (in Chinese))
[5]  Fischer J, Denis M. Mars orbit insertion —— a new challenge for Europe success with ESA's Mars Express. European Space Operations Centre. IEEEAC, 2004, 1370
[6]  Liever P, Habchi S, Burnell S, et al. Computational fluid dynamics prediction of the Beagle 2 aerodynamic database. Journal of Spacecraft and Rocket, 2003, 40(5): 632-638
[7]  Jai B, Wenker D, Hammer B, et al. An overview of Mars reconnaissance orbiter mission and operations challenges. AIAA SPACE Conference & Exposition, Long Beach, California. 2007, AIAA 2007-6090
[8]  Liechty D. Aeroheating analysis for the Mars reconnaissance orbiter with comparison to flight data. Journal of Spacecraft and Rocket, 2007, 44(6): 1226-1231
[9]  Lyons D, Beerer J, Esposito P, et al. Mars global surveyor: aerobraking mission overview. Journal of Spacecraft and Rocket, 1999, 36(3): 307-313
[10]  Jet Propulsion Laboratory. Orbit insertion phase.
[11]  尚海滨, 崔平远, 栾恩杰. 地球-火星的燃料最省小推力转移轨道的设计与优化. 宇航学报, 2006, 27(6): 1168-1173 (Shang Haibin, Cui Pingyuan, Luan Enjie. Design and optimization of Earth-Mars optimal fuel low thrust trajectory. Journal of Astronautics, 2006, 27(6): 1168-1173 (in Chinese))
[12]  杨嘉摨. 航天器轨道动力学与控制(上). 北京: 中国宇航出版社, 2004 (Yang Jiaxi. Spacecraft Orbital Dynamics and Control (Vol.1). Beijing: China Aerospace Press, 2004 (in Chinese))
[13]  Chebotarev G. On the dynamical limits of the solar system. Soviet Astronomy, 1965, 8(5): 787-796
[14]  刘林, 侯锡云. 深空探测器轨道力学. 北京: 电子工业出版社, 2012 (Liu Lin, Hou Xiyun. Deep Space Probe Orbital Mechanics. Beijing: Electronic Industry Press, 2012 (in Chinese))
[15]  郝岩. 深空测控网. 北京: 国防工业出版社, 2004 (Hao Yan. Deep Space Telemetry Network. Beijing: National Defense Industry Press, 2004 (in Chinese))
[16]  徐福祥. 卫星工程概论. 北京: 中国宇航出版社, 2004 (Xu Fuxiang. Introduction of Satellite Engineering. Beijing: China Aerospace Press, 2004 (in Chinese)

Full-Text

Contact Us

service@oalib.com

QQ:3279437679

WhatsApp +8615387084133