| 关于地球转移轨道碎片的轨道寿命问题 |
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| 引用本文： | 刘林,汤靖师.关于地球转移轨道碎片的轨道寿命问题[J].飞行器测控学报,2006,25(5):55-62. |
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| 作者姓名： | 刘林 汤靖师 |
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| 作者单位： | [1]南京大学天文学系,江苏南京210093 [2]南京大学空间环境与航天动力学研究所,江苏南京210093 |
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| 摘 要： | 低轨卫星的轨道寿命主要取决于大气的耗散作用,其轨道在不断变小(即高度降低)变圆的状态下进入地球稠密大气层中陨落。但地球转移轨道(GTO)碎片的运行轨道是一个近地点高度为200km,远地点高度达36000km的大偏心率(e=0.73)椭圆轨道,其轨道寿命主要由第三体(日、月)引力摄动所决定,而且还与其轨道的初始状态有密切关系。本文将根据地球卫星轨道变化规律进行理论分析,阐明力学机制,并给出相应的数值验证。
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| 关 键 词： | 轨道力学 地球转移轨道 空间垃圾 轨道寿命 |
| 收稿时间： | 2006-06-02 |
| 修稿时间： | 2006-07-12 |
On Orbit Lifetime of GTO Debris |
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| LIU Lin,TANG Jing-shi.On Orbit Lifetime of GTO Debris[J].Journal of Spacecraft TT&C Technology,2006,25(5):55-62. |
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| Authors: | LIU Lin TANG Jing-shi |
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| Institution: | 1. Department of Astronomy, Nanjing University, Nanjing, Jiangsu Province 210093 ; 2. Institute of Space Environment and Astrodynamics, Nanjing University, Nanjing, Jiangsu Province 210093 |
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| Abstract: | The lifetime of a low orbit satellite is mainly dominated by atmospheric drag and it loses altitude in the dense atmosphere and eventually falls.However,the lifetime of GTO(Geosynchronous Transfer Orbit) debris,which goes in a large-eccentricity ellipse with a perigee altitude of 200km and an apogee altitude of 36000km(e=0.73),is determined mainly by third-body(Sun & Moon) perturbation and is also closely related to its initial state.This paper is a theoretical analysis of such a satellite orbit and it presents the dynamic mechanism together with corresponding numerical simulation. |
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| Keywords: | Orbit Dynamics Geosynchronous Transfer Orbit Space Debris Orbit Lifetime |
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