| 任意偏心率卫星的大气阻力的短周期摄动 |
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| 引用本文： | 陆本魁,戎鹏志.任意偏心率卫星的大气阻力的短周期摄动[J].中国空间科学技术,1987(Z1). |
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| 作者姓名： | 陆本魁 戎鹏志 |
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| 作者单位： | 中国科学院·紫金山天文台
(陆本魁)，中国科学院·紫金山天文台(戎鹏志) |
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| 摘 要： | 通过本文采用的计算方法和CIRA 1972在160～2000公里高度围范的大气密度的分析模型,导出了人造地球卫星大气阻力短周期摄动的一种计算公式,它形式简单,收敛性好,适用于任意偏心率的卫星。
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| 关 键 词： | 轨道摄动 偏心轨道 气动阻力 卫星 |
THE SHORT PERIOD TERMS CAUSED BY AIR DRAG PERTURBATION OF ARTIFICIAL EARTH SATELLITE IN ORBIT WITH ARBITRARY-ECCENTRICITY |
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| Lu Benkui Rong Pengzhi.THE SHORT PERIOD TERMS CAUSED BY AIR DRAG PERTURBATION OF ARTIFICIAL EARTH SATELLITE IN ORBIT WITH ARBITRARY-ECCENTRICITY[J].Chinese Space Science and Technology,1987(Z1). |
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| Authors: | Lu Benkui Rong Pengzhi |
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| Institution: | Lu Benkui Rong Pengzhi |
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| Abstract: | Using the calculating method and the analytical model of air density of CIRA 1972 at the height between 160 and 2000 km proposed by the authors, a new set of formulae for computing the short period terms caused by air drag perturbation of artificial earth satellite have been deduced. They are with simple form, good convergence, and are applicable to compute the orbit with arbitraryeccentricity. |
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| Keywords: | Orbit perturbation Eccentric orbit Aerodynamic drag Satellite |
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