SLIM Project Team

Naoya Ozaki

  (尾崎 直哉)

Profile Information

Affiliation
Associate Professor, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency
Associate Professor, Space and Astronautical Science, Department of Advanced Studies, The Graduate University for Advanced Studies, SOKENDAI
Degree
博士(工学)(東京大学)

Researcher number
90836222
ORCID ID
 https://orcid.org/0000-0002-8445-1575
J-GLOBAL ID
201801006720467786
Researcher ID
GXH-5604-2022
researchmap Member ID
B000312477

Major Awards

 7

Major Papers

 60
  • Naoya Ozaki, Ryuki Hyodo, Yuki Takao, Darryl Z. Seligman, Michael E. Brown, Sonia Hernandez, Makoto Yoshikawa, Masaki Fujimoto
    8th IAA Planetary Defense Conference, Apr, 2023  Lead authorCorresponding author
  • Naoya Ozaki, Takayuki Yamamoto, Ferran Gonzalez-Franquesa, Roger Gutierrez-Ramon, Nishanth Pushparaj, Takuya Chikazawa, Diogene Alessandro Dei Tos, Onur Çelik, Nicola Marmo, Yasuhiro Kawakatsu, Tomoko Arai, Kazutaka Nishiyama, Takeshi Takashima
    Acta Astronautica, 196 42-56, Jul, 2022  Peer-reviewedLead authorCorresponding author
  • Naoya Ozaki, Kenshiro Oguri, Ryu Funase
    The Journal of the Astronautical Sciences, Feb 4, 2022  Peer-reviewedLead authorCorresponding author
  • Naoya Ozaki, Kanta Yanagida, Takuya Chikazawa, Nishanth Pushparaj, Naoya Takeishi, Ryuki Hyodo
    Journal of Guidance, Control, and Dynamics, 2022  Peer-reviewedLead authorCorresponding author
  • Naoya Ozaki, Stefano Campagnola, Ryu Funase
    Journal of Guidance, Control, and Dynamics, 43(4) 645-655, Mar, 2020  Peer-reviewedLead authorCorresponding author
    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.
  • Naoya Ozaki, Takuya Chikazawa, Kota Kakihara, Akihiro Ishikawa, Yasuhiro Kawakatsu
    Journal of Spacecraft and Rockets, 1 PartF, 2020  Peer-reviewedLead author
  • Kenshiro Oguri, Kenta Oshima, Stefano Campagnola, Kota Kakihara, Naoya Ozaki, Nicola Baresi, Yasuhiro Kawakatsu, Ryu Funase
    JOURNAL OF THE ASTRONAUTICAL SCIENCES, 67(3) 950-976, Jan, 2020  Peer-reviewed
  • Ryu Funase, Satoshi Ikari, Kota Miyoshi, Yosuke Kawabata, Shintaro Nakajima, Shunichiro Nomura, Nobuhiro Funabiki, Akihiro Ishikawa, Kota Kakihara, Shuhei Matsushita, Ryohei Takahashi, Kanta Yanagida, Daiko Mori, Yusuke Murata, Toshihiro Shibukawa, Ryo Suzumoto, Masahiro Fujiwara, Kento Tomita, Hiroki Aohama, Keidai Iiyama, Sho Ishiwata, Hirotaka Kondo, Wataru Mikuriya, Hiroto Seki, Hiroyuki Koizumi, Jun Asakawa, Keita Nishii, Akihiro Hattori, Yuji Saito, Kosei Kikuchi, Yuta Kobayashi, Atsushi Tomiki, Wataru Torii, Taichi Ito, Stefano Campagnola, Naoya Ozaki, Nicola Baresi, Ichiro Yoshikawa, Kazuo Yoshioka, Masaki Kuwabara, Reina Hikida, Shogo Arao, Shinsuke Abe, Masahisa Yanagisawa, Ryota Fuse, Yosuke Masuda, Hajime Yano, Takayuki Hirai, Kazuyoshi Arai, Ritsuko Jitsukawa, Eigo Ishioka, Haruki Nakano, Toshinori Ikenaga, Tatsuaki Hashimoto
    IEEE Aerospace & Electro. Systems Magazine, Nov, 2019  Peer-reviewed
  • Stefano Campagnola, Javier Hernando-Ayuso, Kota Kakihara, Yosuke Kawabata, Takuya Chikazawa, Ryu Funase, Naoya Ozaki, Nicola Baresi, Tatsuaki Hashimoto, Yasuhiro Kawakatsu, Toshinori Ikenaga, Kenshiro Oguri, Kenta Oshima
    IEEE AEROSPACE AND ELECTRONIC SYSTEMS MAGAZINE, 34(4) 38-44, Apr, 2019  Peer-reviewed
  • Naoya Ozaki, Stefano Campagnola, Ryu Funase, Chit Hong Yam
    JOURNAL OF GUIDANCE CONTROL AND DYNAMICS, 41(2) 377-387, Feb, 2018  Peer-reviewed
  • KOSHIRO Yuki, OZAKI Naoya, FUNASE Ryu, NAKASUKA Shinichi
    JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 65(6) 219-226, 2017  Peer-reviewed
    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.
  • Naoya Ozaki, Yosuke Kawabata, Hiroshi Takeuchi, Tsutomu Ichikawa, Ryu Funase, Yasuhiro Kawakatsu
    SICE Journal of Control, Measurement, and System Integration, 10(3) 192-197, 2017  Peer-reviewed

Misc.

 50
  • Takayuki Hosonuma, Takeshi Miyabara, Naoya Ozaki, Ko Ishibashi, Yuta Suzaki, Peng Hong, Masayuki Ohta, Takeshi Takashima
    Apr 2, 2025  
    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.
  • Shota Ito, Hironori Sahara, Naoya Ozaki, Dario Izzo
    AAS/AIAA Space Flight Mechanics Meeting, Jan, 2025  
  • Risa Ito, Naoya Ozaki
    AAS/AIAA Space Flight Mechanics Meeting, Jan, 2025  Last author
  • Akira Hatakeyama, Shota Ito, Toshihiko Yanase, Naoya Ozaki
    AAS/AIAA Space Flight Mechanics Meeting, Jan, 2025  Last author
  • Ryo Yasufuku, Yasuhiro Kawakatsu, Naoya Ozaki
    AAS/AIAA Space Flight Mechanics Meeting, Jan, 2025  Last author

Major Works

 4

Major Research Projects

 8