H-2Aによるユリシーズ型太陽極軌道への軌道設計

• Material Type: 規格・テクニカルリポート類
• Title: H-2Aによるユリシーズ型太陽極軌道への軌道設計
• Author/Editor: 歌島, 昌由; Utashima, Masayoshi
• Author Heading: 歌島, 昌由; Utashima, Masayoshi
• Publication, Distribution, etc.: 宇宙開発事業団
• Publication Date: 2001-12-25
• Publication Date (W3CDTF): 2001-12-25
• Alternative Title: Orbital design for Ulysses-type solar polar orbit by H-2A
• Periodical title: 宇宙開発事業団技術報告
• ISSN (Periodical Title): ISSN : 1345-7888
• Text Language Code: jpn
• Subject Heading: H-2ロケット打ち上げ型有翼回収機; 太陽極軌道; 打ち上げ機; 太陽電気推進; 太陽磁場; バックグランド放射; 木星; 2次プログラミング; HOPE; H-2 Orbiting Plane; solar polar orbit; launch vehicle; solar electric propulsion; solar magnetic field; background radiation; Jupiter; quadratic programming
• Target Audience: 一般
• Note (General): In the field of planetary science in Japan, future vision up to about 2020 is being made. In that work, the observation of the solar magnetic field, the zodiacal light, the interstellar dusts, and the infrared space background radiation from the points far away from the ecliptic plane is thought to be promising. The orbit of the Ulysses (about 370 kg) launched in 1990 is the solar polar orbit realized by the Jupiter swingby and is one of the adequate orbits, since the maximum deviation of the orbit from the ecliptic plane is large. In this report, it is studied what amount of spacecraft can be injected into the Ulysses-type solar polar orbit by the 2 ton-version H-2A launch vehicle. For the flight to the Jupiter, 3 methods of (a) going to the Jupiter directly by the solid motor upper stages, (b) utilizing the Earth swingby after the injection into an intermediate orbit by the solid motor, and (c) utilizing the E delta V-EGA by the solar electric propulsion system, are studied. The Ulysses used the method (a). In this report, the candidate launch years are set to be 2013-2020, and the perihelion radius of the solar polar orbit is set to be 1.8 AU. By the method (a), the spacecraft of about 317 kg can be delivered to the Jupiter in one year and three months. By the method (b), the spacecraft of about 448 kg can be delivered to the Jupiter in four years and four months. By the method (c), the spacecraft of about 752 kg can be delivered to the Jupiter in about three years. The method (c) can inject a massive spacecraft into the Ulysses-type solar polar orbit in a relatively short period. The method (c), however, requires an advanced electric propulsion system with the variable performance of both thrust and specific impulse between 0.6 and 1.6 times of the nominal values. Research and development for the realization of such a propulsion system are expected.; 資料番号: AA0032597000; レポート番号: NASDA-TMR-010011
• Access Restrictions: インターネット公開
• Periodical Title (NCID): AN00364784; https://ci.nii.ac.jp/ncid/AN00364784
• Data Provider (Database): 国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）; https://irdb.nii.ac.jp
• Original Data Provider (Database): 宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ

• Summary, etc.: 日本の惑星科学分野において、2020年頃までの将来計画のビジョンを描く作業が進められており、太陽極軌道を実現して、黄道面から大きく離れた空間からの太陽磁場、黄道光、星間塵、赤外線宇宙背景放射などの観測の有効性が認識されている。NASAとESAの共同ミッションとして1990年10月に打ち上げられたユリ...