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 准教授総合研究大学院大学 先端学術院 宇宙科学コース 准教授
- 学位
- 博士(工学)(東京大学)
- 研究者番号
- 90836222
- ORCID ID
https://orcid.org/0000-0002-8445-1575
- J-GLOBAL ID
- 201801006720467786
- Researcher ID
- GXH-5604-2022
- researchmap会員ID
- B000312477
経歴
5-
2023年4月 - 現在
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2019年3月 - 2023年3月
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2018年4月 - 2019年2月
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2017年6月 - 2017年12月
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2016年10月 - 2016年12月
学歴
3-
2015年4月 - 2018年3月
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2013年4月 - 2015年3月
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2010年4月 - 2013年3月
受賞
7-
2015年3月
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2013年3月
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2010年3月
主要な論文
60-
8th IAA Planetary Defense Conference 2023年4月 筆頭著者責任著者
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Acta Astronautica 196 42-56 2022年7月 査読有り筆頭著者責任著者
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The Journal of the Astronautical Sciences 2022年2月4日 査読有り筆頭著者責任著者
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Journal of Guidance, Control, and Dynamics 2022年 査読有り筆頭著者責任著者Asteroid exploration has been attracting more attention in recent years. Nevertheless, we have just visited tens of asteroids, whereas we have discovered more than 1 million bodies. As our current observation and knowledge should be biased, it is essential to explore multiple asteroids directly to better understand the remains of planetary building materials. One of the mission design solutions is utilizing asteroid flyby cycler trajectories with multiple Earth gravity assists. An asteroid flyby cycler trajectory design problem is a subclass of global trajectory optimization problems with multiple flybys, involving a trajectory optimization problem for a given flyby sequence and a combinatorial optimization problem to decide the sequence of the flybys. As the number of flyby bodies grows, the computation time of this optimization problem expands maliciously. This paper presents a new method to design asteroid flyby cycler trajectories utilizing a surrogate model constructed by deep neural networks approximating trajectory optimization results. Because one of the bottlenecks of machine learning approaches is the heavy computation time to generate massive trajectory databases, we propose an efficient database generation strategy by introducing pseudo-asteroids satisfying the Karush–Kuhn–Tucker conditions. The numerical result applied to Japan Aerospace Exploration Agency’s DESTINY+ mission shows that the proposed method is practically applicable to space mission design and can significantly reduce the computational time for searching asteroid flyby sequences.
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Journal of Guidance, Control, and Dynamics 43(4) 645-655 2020年3月 査読有り筆頭著者責任著者Recent low-thrust space missions have highlighted the importance of designing trajectories that are robust against uncertainties. In its complete form, this process is formulated as a nonlinear constrained stochastic optimal control problem. This problem is among the most complex in control theory, and no practically applicable method to low-thrust trajectory optimization problems has been proposed to date. This paper presents a new algorithm to solve stochastic optimal control problems with nonlinear systems and constraints. The proposed algorithm uses the unscented transform to convert a stochastic optimal control problem into a deterministic problem, which is then solved by trajectory optimization methods such as differential dynamic programming. Two numerical examples, one of which applies the proposed method to low-thrust trajectory design, illustrate that it automatically introduces margins that improve robustness. Finally, Monte Carlo simulations are used to evaluate the robustness and optimality of the solution.
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Journal of Spacecraft and Rockets 1 PartF 2020年 査読有り筆頭著者
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JOURNAL OF THE ASTRONAUTICAL SCIENCES 67(3) 950-976 2020年1月 査読有りThis paper presents the trajectory design for EQUilibriUm Lunar-Earth point 6U Spacecraft (EQUULEUS), which aims to demonstrate orbit control capability of CubeSats in the cislunar space. The mission plans to observe the far side of the Moon from an Earth-Moon L2 (EML2) libration point orbit. The EQUULEUS trajectory design needs to react to uncertainties of mission design parameters such as the launch conditions, errors, and thrust levels. The main challenge is to quickly design science orbits at EML2 and low-energy transfers from the post-deployment trajectory to the science orbits within the CubeSat's limited propulsion capabilities. To overcome this challenge, we develop a systematic trajectory design approach that 1) designs over 13,000 EML2 quasi-halo orbits in a full-ephemeris model with a statistical stationkeeping cost evaluation, and 2) identifies families of low-energy transfers to the science orbits using lunar flybys and solar perturbations. The approach is successfully applied for the trajectory design of EQUULEUS.
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IEEE Aerospace & Electro. Systems Magazine 2019年11月 査読有り
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IEEE AEROSPACE AND ELECTRONIC SYSTEMS MAGAZINE 34(4) 38-44 2019年4月 査読有り
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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 41(2) 377-387 2018年2月 査読有りLow-thrust propulsion is a key technology for space exploration, and much work in astrodynamics has focused on the mathematical modeling and the optimization of low-thrust trajectories. Typically, a nominal trajectory is designed in a deterministic system. To account for model and execution errors, mission designers heuristically add margins, for example, by reducing the thrust and specific impulse or by computing penalties for specific failures. These conventional methods are time-consuming, done by hand by experts, and lead to conservative margins. This paper introduces a new method to compute nominal trajectories, taking into account disturbances. The method is based on stochastic differential dynamic programming, which has been used in the field of reinforcement learning but not yet in astrodynamics. A modified version of stochastic differential dynamic programming is proposed, where the stochastic dynamical system is modeled as the deterministic dynamical system with random state perturbations, the perturbed trajectories are corrected by linear feedback control policies, and the expected value is computed with the unscented transform method, which enables solving trajectory design problems. Finally, numerical examples are presented, where the solutions of the proposed method are more robust to errors and require fewer penalties than those computed with traditional approaches, when uncertainties are introduced.
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日本航空宇宙学会論文集 65(6) 219-226 2017年 査読有りEarth observation satellites can improve the flexibility of observation sites by having “maneuverability,” and low-thrust obtained by ion thruster will be a promising method for orbital change for micro-satellites. Designing low-thrust trajectories for these satellites is a multi-revolution and multi-objective (time/fuel-optimal) optimization problem, which usually requires high computational cost to solve numerically. This paper derives an analytical and approximate optimal orbit change strategy between two circular orbits with the same semi-major axis and different local time of ascending node, and proposes a graph-based method to optimize the multi-objective criteria. The optimal control problem results in a problem to search a switching point on the proposed graph, and mission designers can design an approximate switching point on this graph, by using two heuristic and reasonable assumptions that 1) the optimal thrust direction should be tangential to orbit and 2) the optimal thrust magnitude should be bang-bang control with an intermediate coast. Finally, numerical simulation with feedback control algorithm taking thrust margin demonstrates that the proposed method can be applicable in the presence of deterministic and stochastic fluctuation of aerodynamic disturbances.
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SICE Journal of Control, Measurement, and System Integration 10(3) 192-197 2017年 査読有り
MISC
50-
2025年4月2日DESTINY+ is an upcoming JAXA Epsilon medium-class mission to flyby multiple asteroids including Phaethon. As an asteroid flyby observation instrument, a telescope mechanically capable of single-axis rotation, named TCAP, is mounted on the spacecraft to track and observe the target asteroids during flyby. As in past flyby missions utilizing rotating telescopes, TCAP is also used as a navigation camera for autonomous optical navigation during the closest-approach phase. To mitigate the degradation of the navigation accuracy, past missions performed calibration of the navigation camera's alignment before starting optical navigation. However, such calibration requires significant operational time to complete and imposes constraints on the operation sequence. From the above background, the DESTINY+ team has studied the possibility of reducing operational costs by allowing TCAP alignment errors to remain. This paper describes an autonomous optical navigation algorithm robust to the misalignment of rotating telescopes, proposed in this context. In the proposed method, the misalignment of the telescope is estimated simultaneously with the spacecraft's orbit relative to the flyby target. To deal with the nonlinearity between the misalignment and the observation value, the proposed method utilizes the unscented Kalman filter, instead of the extended Kalman filter widely used in past studies. The proposed method was evaluated with numerical simulations on a PC and with hardware-in-the-loop simulation, taking the Phaethon flyby in the DESTINY+ mission as an example. The validation results suggest that the proposed method can mitigate the misalignment-induced degradation of the optical navigation accuracy with reasonable computational costs suited for onboard computers.
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AAS/AIAA Space Flight Mechanics Meeting 2025年1月
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AAS/AIAA Space Flight Mechanics Meeting 2025年1月 最終著者
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AAS/AIAA Space Flight Mechanics Meeting 2025年1月 最終著者
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AAS/AIAA Space Flight Mechanics Meeting 2025年1月 最終著者
主要なWorks(作品等)
4主要な共同研究・競争的資金等の研究課題
8-
日本学術振興会 学術変革領域研究(B) 2020年10月 - 2023年3月
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日本学術振興会 科学研究費助成事業 若手研究 2019年4月 - 2023年3月
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科学技術振興機構(JST) 研究成果最適展開支援プログラム(A-STEP) トライアウト 2020年10月 - 2022年3月
メディア報道
3-
Tellus 宙畑 2021年11月24日 インターネットメディア人工衛星の軌道を3回に分けて学ぶ連載の最終回。人工衛星でよく使われる軌道についてひとつずつ解説していきます。
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Tellus 宙畑 2021年10月28日 インターネットメディア人工衛星の軌道記事の第2弾!今回はPythonを使って人工衛星の軌道を表現していきます。
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Tellus 宙畑 2021年10月6日 インターネットメディア人工衛星はどのように動いているのでしょうか。人工衛星の軌道解説シリーズ、第一弾は軌道と用途の関係を徹底解説します!