旋转大气下火星探测器轨道捕获

吕敬; 张明明; 龚胜平

旋转大气下火星探测器轨道捕获

1.
北京航空航天大学航空科学与工程学院, 北京 100191
2. 清华大学航天航空学院, 北京 100084

基金项目: 国家自然科学基金资助项目(10832004,11102006);凡舟基金资助项目(20110502)

详细信息

作者简介:
吕敬(1979-),女,河北廊坊人,讲师,lvjing@buaa.edu.cn.

中图分类号: V412.4⁺1
计量
- 文章访问数: 1525
- HTML全文浏览量: 118
- PDF下载量: 674
- 被引次数: 0
出版历程
- 收稿日期: 2012-02-28
- 网络出版日期: 2013-03-31

Aerocaptureperiod under rotating atmospheric environment for Mars vehicle

1.
School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
2. School of Aerospace, Tsinghua University, Beijing 10084, China

摘要

摘要: 针对大气辅助捕获下多次穿越的方式,分别建立探测器气动捕获段在静止大气和旋转大气模型下的轨道动力学方程并进行相应的动力学仿真,分析旋转大气对轨道捕获的影响.根据仿真结果,给出了在两种大气模型下完成目标捕获时,任务耗时以及探测器所受的热量、过载情况,通过给定不同目标轨道近火点高度,得出两种大气模型下卫星轨道的轨道参数变化形式.结论表明:当目标轨道近火点高度较低时,旋转大气对探测器轨道参数的变化形式影响较大,应该考虑旋转大气的影响.
- 大气辅助捕获 /
- 旋转大气 /
- 静止大气 /
- 卫星轨道参数
Abstract: With regard to the human exploration of Mars, based on aerobraking, the dynamics equations for the Mars vehicle were established, both in the static and rotating atmospheric environment. Simulations of the flight databases were generated by a Matlab process based on a three-dimensional dynamic model.A comparative performance analysis of atmospheric models was carried out using details of the duration, aerodynamicloading of the Mars vehicle, and other orbital parameters. The results show that changes of the orbital parameters form are large difference under the rotating and static atmospheric environments on the low periareon, the influence of the rotating atmospheric environment should be considered.
- aerobraking /
- rotating atmospheric environment /
- static atmospheric environment /
- orbital parameter

HTML全文

参考文献(1)

[1] 闵学龙,潘腾,郭海林.火星探测器使命轨道捕获策略研究[J].航天器工程,2008,17(6):39-43 Min Xuelong,Pan Teng,Guo Hailin.Analysis of orbit capture method for Mars vehicle[J].Spacecraft Engineering,2008,17(6):39-43(in Chinese) [2] David M C,James O A.Technologies of aerobraking[R].NASA TM-02854,2011 [3] Brice N.IAA Mars cosmic study report[R].IAA-102-5528,1992 [4] Nock K T,Friedlander A L.Elements of Mars transportation system[J].Acta Astronautica,1987,15(6/7):505-522 [5] Larson W J,Lindar K P.Human space flight:mission analysis and design[M].New York:McGraw-Hill,1999 [6] Angelo C,Emilio R A.Simplifified model for the evalution of the deltaV of ascent trajectories [C]//41^st AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.Tucson:Arizona,2005:267-298 [7] 肖峰.人造地球卫星轨道摄动理论[M].长沙:国防科技大学出版社,1995:178-192 Xiao Feng.Man-made earth satellite orbit perturbation theory[M].Changsha:Press of National University of Defense Technology,1995:178-192(in Chinese) [8] 符俊,蔡洪,张士峰.气动力辅助双脉冲最优异面变轨问题研究[J].导弹学报,2011,23(2):22-27 Fu Jum,Cai Hong,Zhang Shifeng.Research on optimal two-impulse aeroassisted orbital transfer[J].Joural of Ballistic,2011,23(2):22-27(in Chinese) [9] 张文普,张成义,韩波.气动力辅助变轨的数值模拟[J].力学季刊,2011,31(1):8-13 Zhang Wenpu,Zhang Chengyi,Han Bo.Numerical simulation of aeroassister orbit transfer[J].Chinese Quarterly of Mechanics,2011,31(1):8-13(in Chinese) [10] Khalil K I.The drag exerted by an oblate rotating atmosphere on an artificalsatellite[J].Applied Mathematics and Mechanics,2002,23(9):903-915 [11] Christian J A,Grant W,Jarret L,et al.Extention of traditional entry,descent and landing technologies for human Mars exploration [ J ].Journal of Spacecraft and Rockets,2008,45(1):130-141 [12] Braun R D,Manning R M.Mars exploration entry,descent and landing challenges [J].Journal of Spacecraft and Rockets,2007,44(2):310-323 [13] Vaughan D,Miller H C,Brand G.A comparative study of aerocapture missions with a mars destination [C]//41^stAIAA/ASME/SAE/ASEE Joint Propulsion Conference&Exhibit.Tucson:Arizona,2009:225-263

施引文献

资源附件(0)

访问统计