研究者業績
基本情報
- 所属
- 国立研究開発法人宇宙航空研究開発機構 宇宙科学研究所 宇宙飛翔工学研究系 教授(兼任)国際宇宙探査センター 火星衛星探査機プロジェクトチーム プロジェクトマネージャ
- 学位
- 博士(工学)(東京大学)
- J-GLOBAL ID
- 200901025451103270
- researchmap会員ID
- 5000092382
- 外部リンク
研究キーワード
7研究分野
1論文
195-
The Journal of the Astronautical Sciences 2026年1月8日
-
Acta Astronautica 2024年12月
-
The Journal of the Astronautical Sciences 2024年11月15日
-
Space Telescopes and Instrumentation 2024: Ultraviolet to Gamma Ray 89-89 2024年8月21日
MISC
305-
宇宙航空研究開発機構特別資料 JAXA-SP- (09-016) 2010年
-
60th International Astronautical Congress 2009, IAC 2009 2 1140-1149 2009年 査読有り
-
A Collection of Technical Papers of The 18th Workshop on Astrodynamics and Flight Mechanics 155-160 2008年7月
-
Transactions of the Japan Society for Aeronautical and Space Sciences, Space Technology Japan (Web) 5(5) 1-7 2007年Discussed in this paper is a lunar approach strategy tolerant of a lunar orbit injection (LOI) failure. LOI is one of the most critical events for a lunar orbiting mission. If LOI is not performed, the spacecraft flies by the moon, and in the worst case, it escapes not only from the moon but also from the earth, which leads to mission failure. The proposed strategy is to design a trajectory so as to re-encounter the moon even when LOI is not performed. It provides an opportunity for mission recovery even in the case of an unexpected fly-by. A trajectory design procedure is introduced and an example of the designed trajectory is shown.
-
宇宙技術 6(6) 87-96 2007年Analyzed in this paper are Near-Earth Asteroids sample return mission opportunities in early 2010s. The mission sequences supposed are Keplerian orbits connected with impulsive velocity changes including planetary gravity assists. The sequences are constructed by "trajectory parts connecting method", which is exploited by the author. The method enables to construct the possible sequences comprehensively under defined structure and given constraints. At the same time, it enables to assess the dynamical feasibility of the constructed sequences quantitatively by way of the total required velocity increment required to complete the sequences. Over 4000 Near-Earth Asteroids are taken into account as the candidates of the mission targets, and the mission sequences include not only the sample return from a single asteroid, but also the sample return from two asteroids. Lists of the asteroids (or their combinations) which have mission opportunities in early 2010s are provided and some example sequences are shown.
-
Transactions of the Japan Society for Aeronautical and Space Sciences, Space Technology Japan (Web) 5(5) 9-15 2007年In this paper, the translunar trajectory of the simple sequence is investigated. The trajectory discussed in this paper is a two-burn ballistic trajectory from the low earth parking orbit to the low lunar orbit. The problem is practical in that the geometric relation from the launch site to the moon is fully considered. The paper includes three subjects. First is the structure of the problem and the solution space. The problems are defined and the solutions are grouped by the properties of the lunar transfer sequence. Second are the characteristics of optimal solutions. The topics discussed are the transition of the required velocity increment based on the launch date, and the difference according to the property of the lunar transfer sequence. Third is the sensitivity analysis of a number of items to the deviation of the parameters from the optimal solution.
講演・口頭発表等
11-
71st International Astronautical Congress 2020年10月
共同研究・競争的資金等の研究課題
10-
日本学術振興会 科学研究費助成事業 2023年3月 - 2024年3月
-
日本学術振興会 科学研究費助成事業 2022年4月 - 2024年3月
-
日本学術振興会 科学研究費助成事業 2021年11月 - 2024年3月
-
日本学術振興会 科学研究費助成事業 2019年4月 - 2021年3月
-
日本学術振興会 科学研究費助成事業 2014年4月 - 2017年3月