Curriculum Vitaes
Profile Information
- Affiliation
- Institute of Space and Astronautical Science, Japan Aerospace Exploration AgencyResearch fellow of the Japan Society for the Promotion of Science, The Graduate School of Engineering Department of Aeronautics and Astronautics, The University of Tokyo
- Degree
- 博士（工学）(Mar, 2007, 東京大学)
- Researcher number
- 70509819
- J-GLOBAL ID
- 200901051354637504
- researchmap Member ID
- 5000090886
Research Interests
11Awards
4-
Feb, 2019
Papers
115-
Journal of Guidance, Control, and Dynamics, 47(9) 1905-1919, Sep, 2024In autonomous space systems, the reliability of navigation systems is essential. Observability in autonomous orbit determination techniques depends on the spacecraft’s orbital motion, making the design of autonomous navigation systems and orbital maneuvers a coupled process. This study develops a stable and efficient algorithm based on differential dynamic programming to design maneuver sequences that improve navigation performance. Our approach incorporates the Fisher information matrix into a cost function to quantify state observability and facilitates its convergence using a semi-analytic gradient and Hessian derived under impulsive maneuvers. Two numerical examples show the validity and effectiveness of our algorithm. The results indicate the stability and efficiency in determining maneuver sequences and the improvement of state estimation accuracy along an optimized trajectory. It is also applicable to other observability-aware optimal control problems because the algorithm is independent of specific systems.
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Space Science Reviews, 220(1), Jan 24, 2024Abstract 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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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 67(5) 274-284, 2024
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Journal of Astronomical Telescopes, Instruments, and Systems, 9(03), Sep 12, 2023
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Journal of Evolving Space Activities, 1 n/a, 2023The 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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2022 IEEE Aerospace Conference (AERO), 152 1-11, Mar 5, 2022
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The Journal of the Astronautical Sciences, Feb 4, 2022
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SPACE TELESCOPES AND INSTRUMENTATION 2022: ULTRAVIOLET TO GAMMA RAY, 12181, 2022
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JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 69(5) 179-186, 2021
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Journal of Guidance, Control, and Dynamics, 43(4) 645-655, Mar, 2020 Peer-reviewedLast author
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Acta Astronautica, 171 208-214, Feb, 2020 Peer-reviewed
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Proceedings of the International Astronautical Congress, IAC, 2020-, 2020
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Proceedings of the International Astronautical Congress, IAC, 2020-October, 2020
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Flight Model Development and Ground Demonstration of Water Resistojet Propulsion System for CubeSatsTRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 63(4) 141-150, 2020
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JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 68(2) 89-95, 2020 Peer-reviewedLast author<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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JOURNAL OF THE ASTRONAUTICAL SCIENCES, 67(3) 950-976, Jan, 2020 Peer-reviewedLast author
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JOURNAL OF SPACECRAFT AND ROCKETS, 56(5) 1400-1408, Sep, 2019 Peer-reviewed
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Advances in the Astronautical Sciences, 168 281-300, 2019
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Advances in the Astronautical Sciences, 168 4015-4026, 2019
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Advances in the Astronautical Sciences, 168 301-318, 2019
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Advances in the Astronautical Sciences, 168 3511-3526, 2019
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Aerospace Technology Japan, 17(1) 43-50, Jan, 2019 Peer-reviewed
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Aerospace Technology Japan, 17(3) 315-320, Jan, 2019 Peer-reviewed
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Advances in the Astronautical Sciences, 168 1331-1343, 2019 Last author
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Acta Astronautica, 152 299-309, Nov, 2018 Peer-reviewed
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JOURNAL OF ASTRONOMICAL TELESCOPES INSTRUMENTS AND SYSTEMS, 4(4), Oct, 2018 Peer-reviewed
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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS, 41(2) 377-387, Feb, 2018 Peer-reviewed
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Flight Model Development and Ground Demonstration of Water Resistojet Propulsion System for CubeSatsTransactions of the Japan Society for Aeronautical and Space Sciences, 16(5) 427-431, 2018 Peer-reviewed
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10th Symposium on Space Resource Utilization, 2017, 2017
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SICE Journal of Control, Measurement, and System Integration, 10(3) 192-197, 2017 Peer-reviewed
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JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 65(6) 219-226, 2017 Peer-reviewedEarth 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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Transactions of the Japan Society for Aeronautical and Space Sciences, 60(3) 181-191, 2017 Peer-reviewedLast author
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Geophysical Research Letters, 44(23) 192-197, 2017 Peer-reviewed
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Advances in Space Research, 58(4) 528-540, Aug, 2016 Peer-reviewed
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Initial Flight Operations of the Miniature Propulsion System Installed on Small Space Probe: PROCYONAerospace Technology Japan, 14(ists30) Pb_13-Pb_22, Jul, 2016 Peer-reviewed
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AIAA/AAS Astrodynamics Specialist Conference, 2016, 2016
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AIAA/AAS Astrodynamics Specialist Conference, 2016, 2016
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Advances in the Astronautical Sciences, 158 239-258, 2016
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Advances in the Astronautical Sciences, 158 933-951, 2016
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Advances in the Astronautical Sciences, 158 3053-3068, 2016
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Advances in the Astronautical Sciences, 156 1617-1630, 2016
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Proceedings of the International Astronautical Congress, IAC, 2016
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JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 64(2) 131-138, 2016 Peer-reviewedWe propose thrust vector management by correctly positioning the thruster on a spacecraft by thrust vector measurement to decrease unwanted torque of thrust vector misalignment. A ground test was performed to measure 2-dimensional ion current distribution of 10W-class miniature ion thruster by electrostatic probe. The thrust vector measurement test showed that the thrust vector inclining angle was 1.4º from the geometrically symmetric axis of the thruster. The thruster was positioned on the first interplanetary micro-spacecraft: PROCYON after redesigning thruster bracket. Thrust vector estimation in the initial on-orbit operation of 6.5 hours showed that thrust vector passes through within 5mm of the PROCYON's center of gravity.
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Proceedings of the International Astronautical Congress, IAC, 7 5231-5239, 2015
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Aerospace Technology Japan, 12(ists29) Tr_1-Tr_5, Nov, 2014 Peer-reviewed
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Aerospace Technology Japan, 12(ists29) Pk_43-Pk_50, Nov, 2014 Peer-reviewed
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Aerospace Technology Japan, 12(ists29) Pd_85-Pd_90, Nov, 2014 Peer-reviewedLead author
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Aerospace Technology Japan, 12(ists29) Tk_19-Tk_24, Aug, 2014 Peer-reviewed
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Aerospace Technology Japan, 12(ists29) Tk_7-Tk_11, Jul, 2014 Peer-reviewed
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Aerospace Technology Japan, 12(ists29) Pb_33-Pb_38, May, 2014 Peer-reviewedSolar sail is a spacecraft that has a large-scale membrane to utilize the solar radiation pressure for its thrust. Hence, maintaining the membrane structure during space flight is a critical issue to keep thrust performance of the spacecraft. In this paper, we focused on the electrostatic force due to spacecraft charging on the membrane as one of the possible factor to cause the deformation of the membrane structure. We had estimated the electrostatic force via charging simulation for the IKAROS spacecraft in solar wind plasma at 1.0 AU. We had also made a structural analysis for the deployed membrane of IKAROS with the electrostatic force. The structural analysis showed that the electrostatic force could hardly affect the membrane structure in this case.
Misc.
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宇宙科学技術連合講演会講演集(CD-ROM), 67th, 2023
Professional Memberships
1Research Projects
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科学研究費助成事業 基盤研究(S), 日本学術振興会, May, 2016 - Mar, 2021
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Grants-in-Aid for Scientific Research Grant-in-Aid for Young Scientists (B), Japan Society for the Promotion of Science, Apr, 2013 - Mar, 2017
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Grants-in-Aid for Scientific Research Grant-in-Aid for Young Scientists (B), Japan Society for the Promotion of Science, 2011 - 2012
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Grants-in-Aid for Scientific Research Grant-in-Aid for Young Scientists (Start-up), Japan Society for the Promotion of Science, 2008 - 2009
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Grants-in-Aid for Scientific Research Grant-in-Aid for JSPS Fellows, Japan Society for the Promotion of Science, 2004 - 2006
