Flight property around the sphere of influence and the application to satellites exploration

• Material Type: 文書・図像類
• Title: Flight property around the sphere of influence and the application to satellites exploration
• 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: 2002-11-01
• Publication Date (W3CDTF): 2002-11-01
• Alternative Title: 作用圏境界を飛行する軌道の力学的性質と小衛星探査への応用
• Periodical title: NASDA English Translation
• ISSN (Periodical Title): ISSN : 1345-7926
• Text Language Code: eng
• Subject Heading: 小型科学衛星; 探索; 円形固定3体問題; 偽軌道; 力学特性; 数値確認; フォボス; 光センサー; 太陽・地球系; 重力; 研究開発; small scientific satellite; exploration; circular restricted three body problem; pseudo orbit; dynamic characteristic; numerical verification; Phobos; optical sensor; Sun-Earth system; gravitation; research and development
• Target Audience: 一般
• Note (General): In this paper, small satellites around planets, whose size of sphere of influence is nearly equal to the size of their own, are chosen as the targets discussed for the exploration by spacecraft, since it is difficult to realize simple orbits around such small satellites. As the exploration orbits around small satellites, two kinds of orbits are studied here. One is the high altitude orbit group for the global observation of a small satellite. Since this kind of orbits exist outside of the sphere of influence of the small satellite, the motion of the spacecraft in this orbit group is governed mainly by the planet gravity field. Actual orbit around a celestial body in this gravitational circumstances is called 'Pseudo Orbit' in this paper, since apparently the spacecraft flies around the satellite. In order to observe the polar region of the small satellite, the pseudo orbit should have large inclination with respect to the satellite's orbital plane. The other is low altitude orbit group, from which close proximity to the small satellite is observed. Small satellites, in general, have significantly irregular shape. Therefore, the low altitude orbit around such a satellite may impact it with ease. In order to avoid impact to the small satellite, low altitude orbits are required to be trajectories with hovering maintaining altitude by thrusters or special trajectories which fly in the boundary region of the sphere of influence. The pseudo orbit, which belongs to a high altitude orbit group, has complicated dynamic features. Innanen et al. showed that the pseudo orbit has the upper limit in the inclination. The rigorous mathematical property on the instability of the pseudo orbit, however, was not given yet. This paper presents it for the first time. First of all, it is shown that the eccentricity of the pseudo orbit has the lower limit. Then, by the method of virtual energy, that the out-of-plane motion of the pseudo orbit causes disturbances in the in-plane motion is derived. Further, it is clarified that the motion of the pseudo orbit is reduced to the Mathieu's equation which has a periodic coefficient, and that the instability peculiar to the solution of the Mathieu's equation is induced from the disturbances caused by the out-of-plane motion of the pseudo orbit. In addition to it, by making full use of the characteristics of the stability region of the Mathieu's equation and selecting the peculiar eccentricity which exists discretely, a new method of stabilization scheme is proposed. This strategy of stabilization is called 'stabilization by resonance' in this paper. By selecting the eccentricity which causes the stabilization by resonance, a pseudo orbit with larger inclination is realized. And by utilizing the secular perturbation of the argument of periapsis due to the gravity of the small satellite, the global observation of the small satellite is accomplished. In the low altitude orbit group, the non-ballistic constant-altitude transfer and the L1-L2 points connecting trajectory over polar region, which is a ballistic trajectory and flies in the boundary of the sphere of influence where characteristics of the three-body problem clearly appear, are mainly studied. In the constant-altitude transfer, for example, the relationship between the transfer velocity and the required velocity increment to various directions are clarified. In the L1-L2 points connecting trajectory over polar region, the existence of the spiral-shaped trajectory that avoids impact to the small satellite is shown using the analytical solution of the linear equations of motion near the L1 or L2 point, and the trajectory is illustrated in the numerical calculations for the Mars-Phobos system. The stability analysis for the pseudo orbit shown in the first half of this paper is the result clarified for the first time by this paper. The orbit, which has large inclination and is stabilized by resonance, is useful for such missions as observe wide space around the Earth from points out of the ecliptic plane as well as for the small satellite exploration. The results obtained for the low altitude orbit group are indispensable for the design of missions for the exploration of close proximity to small satellites, and are useful in the engineering purposes.; 資料番号: AA0035831000; レポート番号: NASDA-ETR-020005; レポート番号: NASDA-TMR-010007
• Source: https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=42812&item_no=1&attribute_id=31&file_no=1
• Access Restrictions: 限定公開
• 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