RESEARCH

Stochastic Optimal Control for Space Applications

Robust Spacecraft Guidance & Control under Uncertainty
(CU Boulder, 2017-present)

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Stationkeeping on an unstable Halo orbit in the Earth-Moon system (K. Oguri, M. Ono, and J. McMahon, IEEE CDC, 2019)

Related Publications:

  • K. Oguri, M. Ono, and J. W. McMahon. Convex Optimization over Sequential Linear Feedback Policies with Continuous-time Chance Constraints. In 2019 IEEE Conference on Decision and Control, Nice, France, 2019
  • K. Oguri and J. W. McMahon. Autonomous Guidance for Robust Achievement of Science Observations around Small Bodies. In AAS Guidance, Navigation, and Control, Breckenridge, Colorado, 2020

Risk-aware Space Trajectory Design under Uncertainty
(CU Boulder, 2017-present)

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“Risk-aware” trajectory with impulsive maneuver around asteroid Bennu (K. Oguri and J. McMahon, AAS/AIAA ASC, 2019)

Related Publications:

  • K. Oguri and J. W. McMahon. Risk-aware Trajectory Design with Continuous Thrust: Primer Vector Theory Approach. In AAS/AIAA Astrodynamics Specialist Conference, Portland, ME, 2019
  • K. Oguri and J. W. McMahon. Risk-aware Trajectory Design with Impulsive Maneuvers: Convex Optimization Approach. In AAS/AIAA Astrodynamics Specialist Conference, Portland, ME, 2019

SRP-based Orbit Control

SRP-based Orbit Control around Small Bodies
(CU Boulder, 2017-present)

“With appropriate control algorithms, solar radiation pressure (SRP) can be effectively utilized for orbit control around small celestial bodies. In contrast to the historical treatment of SRP as a disturbance at the weak gravity environment, the present paper finds active control of spacecraft attitude promising for orbit control. We develop an optimal control law for the SRP-based orbit control, where a complex reflection model is considered to make the control law applicable to realistic surface reflection models.”
(K. Oguri and J. McMahon, JGCD, 2019)

Landing on asteroid Bennu via SRP-based orbit control (K. Oguri and J. McMahon, JGCD, 2019)

Related Publications:

  • K. Oguri and J. W. McMahon. Solar Radiation Pressure-Based Orbit Control with Application to Small-Body Landing. Journal of Guidance, Control, and Dynamics, 2019. doi: 10.2514/1.G004489
  • K. Oguri and J. W. McMahon. SRP-based Orbit Control with Application to Small Body Landing. In AAS/AIAA Astrodynamics Specialist Conference, Snowbird, UT, 2018
  • K. Oguri and J. W. McMahon. SRP-based Orbit Control for Asteroid Exploration. In 32nd International Symposium on Space Technology and Science, Fukui, Japan, 2019
  • K. Oguri and J. W. McMahon. SRP-based Orbit Control with Application to Orbit Stationkeeping at Small Bodies. Advances in the Astronautical Sciences, 2019

Solar Sailing Trajectory Optimization
(NASA/JPL-Caltech, Fall 2019-present)

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NEA Scout mission (Link) ©︎NASA

Non-Keplerian Dynamics around Small Celestial Bodies

Science Orbit Design under Irregular Gravity Field Perturbations

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Psyche mission (Link) ©︎SSL/ASU/P. Rubin/NASA/JPL-Caltech

Related Publications:

  • K. Oguri, G. Lantoine, B. Hart, and J. W. McMahon. Science Orbit Design with Frozen Beta angle: Theory and Application to Psyche mission. Advances in the Astronautical Sciences, 168(2):1971–1987, 2019
  • K. Oguri, G. Lantoine, W. Hart, and J. McMahon. Science orbit design with a quasi-frozen beta angle: Effects of body obliquity on J2-perturbed dynamics. Celestial Mechanics and Dynamical Astronomy, under review

Space Mission Design

“Dismantling Rubble Pile Asteroids with AoES”
(CU Boulder, 2017-present) PI: Prof. Jay McMahon

Funded by NASA Innovative Advanced Concepts (NIAC) program.

I am currently working on mission design for the new concept of asteroid exploration, “Dismantling Rubble Pile Asteroids with AoES.” This mission concept is to explore and mine small asteroids using a light-weight soft robot. This spacecraft takes advantage of its high area-to-mass ratio to control the orbit around asteroids exploiting Solar Radiation Pressure (SRP), which is a dominant force around small bodies. My current work is to develop orbital control strategies and show the feasibility of the mission concept.

Related Publications:

  • K. Oguri and J. W. McMahon. Solar Radiation Pressure-Based Orbit Control with Application to Small-Body Landing. Journal of Guidance, Control, and Dynamics, 2019. doi: 10.2514/1.G004489
  • J. McMahon, S. K. Mitchell, K. Oguri, et. al. Area-of-Effect Softbots (AoES) for Asteroid Proximity Operations. In 2019 IEEE Aerospace Conference, Big Sky, Montana, 2019. doi: 10.1109/AERO.2019.8741680

 Mission Analysis for Cis-Lunar Exploration CubeSat EQUULEUS
(UTokyo & ISAS/JAXA, 2016-present)

Funded by ISAS/JAXA.

I worked on design of the science orbits for EQUilibriUm Lunar-Earth point 6U Spacecraft (EQUULEUS) mission, as a member of the Mission analysis team led by Dr. S. Campagnola (see here about EQUULEUS mission). Our work leverages the dynamical structure of the circular restricted three-body problem (CR3BP) to systematically and efficiently design quasi-halo orbits in the ephemeris model and perform stationkeeping analysis. The systematic approach enabled us to design over 13,000 of quasi-halo orbits and perform Monte-Carlo stationkeeping simulation for each, which contributed to the complex mission design in the multi-body regime with constrained launch conditions.

Quasi-halo orbits designed in the ephemeris model

Related Publications:

  • K. Oguri, K. Oshima, S. Campagnola, K. Kakihara, N. Ozaki, N. Baresi, Y. Kawakatsu, and R. Funase. EQUULEUS Trajectory Design. The Journal of the Astronautical Sciences, Jan. 2020. doi: 10.1007/s40295-019-00206-y
  • S. Campagnola, J. Hernando-Ayuso, K. Kakihara, Y. Kawabata, T. Chikazawa, R. Funase, N. Ozaki, N. Baresi, T. Hashimoto, Y. Kawakatsu, T. Ikenaga, K. Oguri, and K. Oshima. Mission Analysis for the EM-1 CubeSats EQUULEUS and OMOTENASHI. IEEE Aerospace and Electronic Systems Magazine, 2019. doi: 10.1109/MAES.2019.2916291
  • K. Oguri, K. Kakihara, S. Campagnola, N. Ozaki, K. Oshima, T. Yamaguchi, and R. Funase. EQUULEUS Mission Analysis: Design of the Science Orbit Phase. In International Symposium on Space Flight Dynamics, Ehime, Japan, 2017

Attitude-Orbit Coupled Dynamics & Control of Solar Sailing Spacecraft
(UTokyo, 2014-2017)

Funded by Grant-in-Aid for scientific research #17J09626 as a JSPS DC1 fellow (2017).

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The first solar sail IKAROS. © JAXA

Related Publications:

  • K. Oguri, A. Ishikawa, S. Ikari, T. Kudo, and R. Funase. Precision Evaluation of Reduced Dynamics Model for Non-uniform Spinning Solar Sail Driven by Reflectivity Control. In 4th International Symposium on Solar Sailing, Kyoto, Japan, 2017
  • K. Oguri and R. Funase. Time-optimal Attitude Control Law with a Strategy of Applying to Orbital Control for Spinning Solar Sail Driven by Reflectivity Control. Advances in the Astronautical Sciences, 2016.
  • K. Oguri, T. Kudo, and R. Funase. Design Criteria of Reflectivity Control System Under Uncertainty in Sail Property for Maneuverability Requirement of Spinning Solar Sail. In AIAA/AAS Astrodynamics Specialist Conference, Long beach, CA, 2016

Small-Sat Development

 Cis-Lunar Exploration CubeSat EQUULEUS
(UTokyo & ISAS/JAXA, 2016-present) PI: Prof. T. Hashimoto & Prof. R. Funase

Funded by ISAS/JAXA.

For EQUULEUS mission, in addition to its mission analysis, I worked on the system design as a system manager. EQUULEUS is a 6U CubeSat scheduled to be launched in 2019 by NASA’s Space Launch System (SLS) Exploration Mission 1 (EM-1) (visit here for more detail). The CubeSat aims to reach the 2nd Earth-Moon Lagrange point (EML2) by using a low-energy transfer technique in order to conduct scientific observation as well as to demonstrate the low-energy orbit control technique via CubeSat. After the mission was officially selected by NASA in 2016 spring-summer, as a system manager, I led a small team consisting of master/undergrad students for the preliminary mission design and analysis. Given the CubeSat’s limited capability and high-level mission objectives, we searched an “optimal” solution to “what the spacecraft system should be like?”

Cis-lunar exploration CubeSat EQUULEUS. © UTokyo & JAXA

The First Deep-Space Micro Spacecraft PROCYON
(UTokyo & ISAS/JAXA, 2014-2017) PI: Prof. R. Funase & Prof. Y. Kawakatsu

Funded by ISAS/JAXA.

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Group award:

  • Japanese government MEXT Commendation for Science and Technology “Prize for Science and Technology (Research Category)” (2017).
  • The University of Tokyo President’s Award for Students (2015).
First deep-space micro spacecraft PROCYON. © UTokyo & JAXA

-Acknowledgment-

Funding

2017-present

  • Graduate research assistantship, Department of Aerospace Engineering Sciences, CU Boulder
  • Masason foundation fellowship, from Masason foundation, Japan

2017-2019

  • Scholarship for study abroad, Nakajima Foundation, Japan

2017

  • Departmental fellowship, Department of Aerospace Engineering Sciences, CU Boulder
  • Tuition fee half exemption for outstanding students, the University of Tokyo, Japan
  • JSPS DC1 research fellowship for young scientists, Japan Society for the Promotion of Science (JSPS), Japan

2015-2016

  • Japanese Government MEXT Scholarship, the Ministry of Education, Culture, Sports, Science, and Technology (MEXT), Japan

2016

  • Support for international technological interaction, Tokyo Electric Power Company Holdings (TEPCO) Memorial Foundation, Japan
  • Grant for short overseas research, Murata Foundation, Japan
  • Short-term international travel support, Ministry of Education, Culture, Sports, Science, and Technology (MEXT), Japan

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