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地球の人工衛星の運動における大気の抵抗の影響に関する研究
https://jaxa.repo.nii.ac.jp/records/45006
https://jaxa.repo.nii.ac.jp/records/4500616cc2296-1a25-4fcd-b811-189c08ba65df
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
naltr00748.pdf (1.1 MB)
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| Item type | テクニカルレポート / Technical Report(1) | |||||||||
|---|---|---|---|---|---|---|---|---|---|---|
| 公開日 | 2015-03-26 | |||||||||
| タイトル | ||||||||||
| タイトル | 地球の人工衛星の運動における大気の抵抗の影響に関する研究 | |||||||||
| 言語 | ||||||||||
| 言語 | jpn | |||||||||
| 資源タイプ | ||||||||||
| 資源タイプ識別子 | http://purl.org/coar/resource_type/c_18gh | |||||||||
| 資源タイプ | technical report | |||||||||
| その他のタイトル（英） | ||||||||||
| その他のタイトル | Atmospheric Drag Effects on the Motion of an Artificial Earth Satellite | |||||||||
| 著者 |
武内, 澄夫
× 武内, 澄夫
× TAKEUCHI, Sumio
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| 著者所属 | ||||||||||
| 航空宇宙技術研究所宇宙研究グループ | ||||||||||
| 出版者 | ||||||||||
| 出版者 | 航空宇宙技術研究所 | |||||||||
| 出版者（英） | ||||||||||
| 出版者 | National Aerospace Laboratory(NAL) | |||||||||
| 書誌情報 |
航空宇宙技術研究所報告 en : Technical Report of National Aerospace Laboratory TR-748 巻 748, p. 16, 発行日 1982-12 |
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| 抄録（英） | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | Perturbative effects of atmospheric drag on the motion of an artificial earth satellite are investigated in this paper. The atmosphere is considered to rotate with the same angular velocity as the earth. The altitudes of the satellite are given with reference to the standard earth-ellipsoid. The Lagrange planetary equations in Gaussian form are applied to determine the variations of the orbital elements. The atmospheric density at the satellite is regarded as a function of time. The density function is approximated by polynomials determined by the least-squares method. The coefficients are calculated from the finite set of ordinates corresponding to the density values computed by analytically evaluating the 1971 Jacchia density model. By use of the osculating orbital elements the position of the satellite is predicted. In this case it is assumed that the orbit of the satellite is perturbed by the variations of the earth’s gravitaional field alone. The ratio of the rate of the earth’s rotation and the mean motion of the satellite is usually less than 1/10. This ratio and the eccentricity of the orbit are considered to be of the first order. In the expression of the magnitude of the relative velocity of the satellite with respect to the atmosphere, terms up to the third order are included. By the method of linear perturbations the equations are solved and the perturbative effects on satellite orbital elements are obtained. The solution obtained in this manner consists of terms of three types: purely secular, periodic and mixed secular types. | |||||||||
| ISSN | ||||||||||
| 収録物識別子タイプ | ISSN | |||||||||
| 収録物識別子 | 0389-4010 | |||||||||
| 資料番号 | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | 資料番号: NALTR0748000 | |||||||||
| レポート番号 | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | レポート番号: NAL TR-748 | |||||||||
