| タイトル | The singly averaged differential equations of satellite motion for e greater than or equal to 0 and less than 1 |
| 著者（英） | Dallas, S. S.; Khan, I. |
| 著者所属（英） | Jet Propulsion Lab., California Inst. of Tech. |
| 発行日 | 1976-08-01 |
| 言語 | eng |
| 内容記述 | The singly-averaged differential equations of motion of a satellite are developed in terms of parameters valid for all eccentricities less than one. The perturbations included in the acceleration model are due to an aspherical central planet (zonal harmonics up to degree 20 and resonant harmonics up to degree and order 20), atmospheric drag for a time-varying atmosphere, third-body gravity (the sun and moon for an earth satellite), solar radiation pressure with shadowing, and impulsive maneuvers. Analytic averaging is used to remove short-period terms due to the aspherical central planet and third-body gravity. Numerical averaging is used to remove short-period terms due to atmospheric drag and solar radiation pressure. |
| NASA分類 | ASTRODYNAMICS |
| レポートNO | 76A43115
AIAA PAPER 76-830 |
| 権利 | Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/441969 |
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