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
190-
Icarus 377 114882-114882 2022年5月
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Acta Astronautica 2022年4月
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Earth, Planets and Space 74(1) 2022年1月 査読有り招待有りMartian moons exploration, MMX, is the new sample return mission planned by the Japan Aerospace Exploration Agency (JAXA) targeting the two Martian moons with the scheduled launch in 2024 and return to the Earth in 2029. The major scientific objectives of this mission are to determine the origin of Phobos and Deimos, to elucidate the early Solar System evolution in terms of volatile delivery across the snow line to the terrestrial planets having habitable surface environments, and to explore the evolutionary processes of both moons and Mars surface environment. To achieve these objectives, during a stay in circum-Martian space over about 3 years MMX will collect samples from Phobos along with close-up observations of this inner moon and carry out multiple flybys of Deimos to make comparative observations of this outer moon. Simultaneously, successive observations of the Martian atmosphere will also be made by utilizing the advantage of quasi-equatorial spacecraft orbits along the moons' orbits.
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EARTH PLANETS AND SPACE 73(1) 2021年12月 査読有りThe science operations of the spacecraft and remote sensing instruments for the Martian Moon eXploration (MMX) mission are discussed by the mission operation working team. In this paper, we describe the Phobos observations during the first 1.5 years of the spacecraft's stay around Mars, and the Deimos observations before leaving the Martian system. In the Phobos observation, the spacecraft will be placed in low-altitude quasi-satellite orbits on the equatorial plane of Phobos and will make high-resolution topographic and spectroscopic observations of the Phobos surface from five different altitudes orbits. The spacecraft will also attempt to observe polar regions of Phobos from a three-dimensional quasi-satellite orbit moving out of the equatorial plane of Phobos. From these observations, we will constrain the origin of Phobos and Deimos and select places for landing site candidates for sample collection. For the Deimos observations, the spacecraft will be injected into two resonant orbits and will perform many flybys to observe the surface of Deimos over as large an area as possible.
MISC
301-
日本航空宇宙学会論文集 68(2) 89-95 2020年<p>A Fault Detection, Isolation, and Recovery (FDIR) algorithm for attitude control systems is a key technology to increasing the reliability and survivability of spacecraft. Micro/nano interplanetary spacecraft, which are rapidly evolving in recent years, also require robust FDIR algorithms. However, the implementation of FDIR algorithms to these micro/nano spacecraft is difficult because of the limitations of their resources (power, mass, cost, and so on). This paper shows a strategy of how to construct a FDIR algorithm in the limited resources, taking examples from micro deep space probe PROCYON. The strategy focuses on function redundancies and multi-layer FDIR. These ideas are integrated to suit the situation of micro/nano interplanetary spacecraft and demonstrated in orbit by the PROCYON mission. The in-orbit results are discussed in detail to emphasize the effectiveness of the FDIR algorithm. </p>
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平成30年度宇宙輸送シンポジウム: 講演集録 = Proceedings of Space Transportation Symposium FY2018 2019年1月平成30年度宇宙輸送シンポジウム（2019年1月17日-18日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県資料番号: SA6000136091レポート番号: STEP-2018-036
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航空宇宙技術 18 1-8 2019年<p>JAXA has a plan to send a spacecraft to the Martian moons in the 2020s. The spacecraft needs to transfer to the orbit of one of the Martian moons. In this study, we investigate the maneuver design method and the characteristics of orbit injection that minimizes the velocity increment Δv for the JAXA's Martian exploration mission. In the previous study, a transfer trajectory with three impulsive maneuvers has been demonstrated and it has been shown that setting the initial argument of periapsis to be zero is effective to reduce the Δv for the transfer. In this paper, we proposed the optimal transfer trajectory with four impulsive maneuvers based on the grid searching of maneuver position. First, it is shown that when the declination of v-infinity vector is large relative to the Mars equatorial plane, there exists a region where adopting four impulsive maneuvers reduces the total Δv compared to the three impulsive maneuver transfer. Also, we show that optimal value of the initial argument of periapsis slightly deviates from zero when the declination is large. Finally, we investigate which transfer type has the smaller Δv for each of the possible launch windows of JAXA's Martian exploration mission.</p>
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
9-
日本学術振興会 科学研究費助成事業 2022年4月 - 2024年3月
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日本学術振興会 科学研究費助成事業 2021年11月 - 2024年3月
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日本学術振興会 科学研究費助成事業 2019年4月 - 2021年3月
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日本学術振興会 科学研究費助成事業 2014年4月 - 2017年3月
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日本学術振興会 科学研究費助成事業 2015年10月 - 2016年3月
