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Effects of Motion of the Equatorial Plane on Equatorial Elements of an Earth Satellite
https://jaxa.repo.nii.ac.jp/records/44952
https://jaxa.repo.nii.ac.jp/records/4495278daec2c-2af2-4b14-a482-8513b04c9c10
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
naltr00695.pdf (1.0 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 | Effects of Motion of the Equatorial Plane on Equatorial Elements of an Earth Satellite | |||||||||
| 言語 | en | |||||||||
| 言語 | ||||||||||
| 言語 | eng | |||||||||
| 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 | ||||||||||
| その他のタイトル | 地球の人工衛星の赤道系要素に対する赤道面の運動の影響に関する研究 | |||||||||
| 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 | ||||||||||
| 著者所属（英） | ||||||||||
| en | ||||||||||
| Space Technology Research Group, National Aerospace Laboratory(NAL) | ||||||||||
| 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-695 巻 695, p. 17, 発行日 1982-01 |
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| 抄録（英） | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | As the reference system an intermediate, quasi-inertial reference frame is adopted. This system has been shown by Kozai and Kinoshita 2). In this system the inclination and the argument of perigee are referred to the instantaneous equator of date, and the longitude of the node is measured from the mean equinox of 1950.0 along the mean equator of 1950.0 and then along the instantaneous equator of date. The earth is rotating uniformly in this system, thus giving a particularly simple expression for the sidereal angle. The Lagrange’s planetary equations in their usual form which hold for the orbital elements referred to the non-rotating axial system defined at 1950.0 are used. Then the equations are modified to include the effects of motion of the reference system and transformed into Gaussian form. Because of this motion partial derivatives of orbital elements with respect to time are introduced in the equations. The partial derivatives are derived from the expressions including the terms up to the third order of prcession. The equations are solved by the method of linear perturbations and the perturbations to satellite equatorial orbital elements by the motion of the equatorial plane are obtained. | |||||||||
| 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: NALTR0695000 | |||||||||
| 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-695 | |||||||||
