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 学際科学研究系 准教授
- 研究者番号
- 80873380
- ORCID ID
https://orcid.org/0000-0003-3337-1249- J-GLOBAL ID
- 202001017783214748
- researchmap会員ID
- R000000751
研究キーワード
5研究分野
1経歴
3-
2025年1月
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2020年1月 - 2024年12月
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2019年4月 - 2019年12月
学歴
3-
2016年4月 - 2019年3月
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2014年4月 - 2016年3月
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2010年4月 - 2014年3月
受賞
5-
2015年3月
論文
19-
Journal of Geophysical Research: Space Physics 2025年4月 査読有り
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Acta Astronautica 227 114-125 2025年2月 査読有り
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Springer Aerospace Technology 695-720 2024年12月14日
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Space Science Reviews 220(1) 2024年1月24日Abstract Here we describe the novel, multi-point Comet Interceptor mission. It is dedicated to the exploration of a little-processed long-period comet, possibly entering the inner Solar System for the first time, or to encounter an interstellar object originating at another star. The objectives of the mission are to address the following questions: What are the surface composition, shape, morphology, and structure of the target object? What is the composition of the gas and dust in the coma, its connection to the nucleus, and the nature of its interaction with the solar wind? The mission was proposed to the European Space Agency in 2018, and formally adopted by the agency in June 2022, for launch in 2029 together with the Ariel mission. Comet Interceptor will take advantage of the opportunity presented by ESA’s F-Class call for fast, flexible, low-cost missions to which it was proposed. The call required a launch to a halo orbit around the Sun-Earth L2 point. The mission can take advantage of this placement to wait for the discovery of a suitable comet reachable with its minimum $\varDelta $V capability of $600\text{ ms}^{-1}$. Comet Interceptor will be unique in encountering and studying, at a nominal closest approach distance of 1000 km, a comet that represents a near-pristine sample of material from the formation of the Solar System. It will also add a capability that no previous cometary mission has had, which is to deploy two sub-probes – B1, provided by the Japanese space agency, JAXA, and B2 – that will follow different trajectories through the coma. While the main probe passes at a nominal 1000 km distance, probes B1 and B2 will follow different chords through the coma at distances of 850 km and 400 km, respectively. The result will be unique, simultaneous, spatially resolved information of the 3-dimensional properties of the target comet and its interaction with the space environment. We present the mission’s science background leading to these objectives, as well as an overview of the scientific instruments, mission design, and schedule.
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Journal of Evolving Space Activities 2 n/a 2024年 査読有り筆頭著者責任著者In recent years, nanosatellites and microsatellites have become more than just a technology demonstration tool, but also a tool that can bring about scientific and economic outcomes, mainly in low Earth orbit. On the other hand, the use of microsatellites in interplanetary missions is still limited. There are two main problems in using microsatellites for interplanetary missions. To address the issue of lack of launch opportunities directly to the deep space, we are investigating a microsatellite system that is capable of escaping from Earth orbit, which has relatively frequent launch opportunities such as GTO, into deep space using its own propulsion system. We conducted the conceptual design of a microsatellite for the GEO-X mission, which will perform X-ray imaging of the Earth's magnetosphere from the orbit as far as Lunar Orbit. We designed a 50 kg microsatellite using a 500 N class hybrid kick motor for orbit transfer from GTO, based on previous rideshare launch opportunities. Since suppression of the disturbance torque is important when using such a high thrust propulsion system, a spin-stabilized system is used. A conceptual design was performed taking these considerations into account, and rough feasibility and future issues were extracted.
MISC
31-
Journal of Evolving Space Activities 1 n/a 2023年 査読有りThe low reliability of nano-satellites has become a problem, with the cause often being defects in the design and manufacturing process. It is required to take sufficient measures to account for those defects through ground tests to reduce on-orbit failures. The model-based fault diagnosis method can prevent oversight of fault candidates and compensate for a lack of knowledge in human-based diagnosis. Since the developing time of nano-satellites is limited, fault diagnosis needs to be carried out efficiently also while being careful not to cause secondary faults. This paper presents a novel method that can find the appropriate command to verify candidates of fault location in a satellite. The proposed method can consider the side effect of a command and the efficiency of narrowing them down by using the information transmission path model. In the case study, the proposed method is applied to an earth-orbiting 6U CubeSat, and this case study reveals that 33% of the failures that occur in ground tests can apply to the proposed method. In addition, the proposed method can identify the fault location of some of these failures, although there are several limitations to implementing the proposed method in the actual satellite development.
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電子情報通信学会技術研究報告 = IEICE technical report : 信学技報 116(319) 227-231 2016年11月24日
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スペース・エンジニアリング・コンファレンス講演論文集 2015 _B04-1_-_B04-6_ 2015年 査読有り短期間かつ高信頼度での開発が求められる超小型衛星では,ハードウェア,およびソフトウェアにおいて実績品を再利用することが有効である.しかし,衛星によって構造やミッションが異なることから,ソフトウェアは各機関が毎回個別に開発することが多い.そこで本研究では,姿勢制御系ソフトウェアのモジュールを衛星の構造に応じて自動生成するシステムの構築を行った.これにより,多様な超小型衛星において再利用性の高い姿勢制御系ソフトウェアを実現する.
講演・口頭発表等
82Works(作品等)
2共同研究・競争的資金等の研究課題
2-
日本学術振興会 科学研究費助成事業 学術変革領域研究(B) 2020年10月 - 2023年3月
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2016年9月 - 2019年3月
