Kenshiro Oguri

Kenshiro Oguri
Purdue University | Purdue · School of Aeronautics and Astronautics

Ph.D. in Aerospace Engineering

About

30
Publications
10,225
Reads
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147
Citations
Introduction
Assistant Professor of Aeronautics and Astronautics at Purdue University; Research interest: Astrodynamics, Optimal Control, Optimization, Stochastic Systems, and Space Science, with application to Spacecraft GNC, Trajectory Optimization, and Space Exploration; Research website: https://engineering.purdue.edu/OguriGroup
Additional affiliations
August 2021 - December 2021
California Institute of Technology
Position
  • Postdoctoral Fellow
Description
  • Worked on robust low-thrust trajectory design methods, with particular emphasis on their applications to solar sailing missions
September 2019 - November 2019
California Institute of Technology
Position
  • Researcher
Description
  • Worked on solar sailing trajectory design techniques for NEA Scout mission. Group: Outer Planet Mission Analysis. Mentors: Dr. Gregory Lantoine, Dr. Jon Sims
June 2018 - August 2018
California Institute of Technology
Position
  • Researcher
Description
  • Worked on science orbit design for an asteroid exploration mission Psyche. Group: Outer Planet Mission Analysis Mentors: Dr. Gregory Lantoine, Dr. Jon Sims
Education
August 2017 - March 2021
University of Colorado Boulder
Field of study
  • Aerospace Engineering Sciences
April 2015 - March 2017
The University of Tokyo
Field of study
  • Aeronautics and Astronautics
April 2011 - March 2015
The University of Tokyo
Field of study
  • Aeronautics and Astronautics

Publications

Publications (30)
Conference Paper
Full-text available
Any space trajectories are subject to state uncertainty due to imperfect state knowledge , random disturbances, and partially known dynamical environments. Ideally, such uncertainty and associated risks must be properly quantified and taken into account in the mission design process to ensure a sufficiently low risk of causing hazardous events. How...
Article
PROCYON is the world’s first deep-space micro spacecraft launched on December 3, 2014, as a secondary payload on the launch of JAXA’s Hayabusa2 spacecraft. The mission objectives include the high-speed flyby observation of a near-Earth asteroid, which is enabled by utilizing miniature electric propulsion and an Earth swing-by. Through the PROCYON m...
Conference Paper
Solar sailing is an emerging technology that harnesses solar radiation pressure to propel spacecraft, providing the potential to enable longer-duration, higher Delta-V missions. To ensure successful solar sailing missions, mission designers need to design trajectories that are robust against uncertainty due to navigation error, control error, and u...
Article
Solar sailing is an emerging technology that harnesses solar radiation pressure (SRP) to propel spacecraft, providing the potential to enable longer-duration, higher delta-V missions. It is crucial for solar sailing missions that their trajectories are designed with practical mission considerations such as imperfect SRP force modeling and sail atti...
Article
Any space trajectories are subject to state uncertainty due to imperfect state knowledge, random disturbances, and partially known dynamical environments. Ideally, such uncertainty and associated risks must be properly quantified and taken into account in the process of trajectory design, ensuring a sufficiently low risk of causing hazardous events...
Article
Dynamical environments around small celestial bodies are complex and uncertain, leading to highly perturbed, uncertain orbital motions in their proximity. Under such complexity and uncertainty, mission designers need to plan robust guidance and control of the spacecraft orbit to meet some requirements derived from their mission objectives such as p...
Article
Full-text available
The beta angle, an angle formed by the sunlight and a spacecraft orbital plane, is an important parameter for science orbit design of orbiter missions. This angle defines lighting conditions and eclipse occurrences, and is used for science observation planning. Not only is this parameter perturbed by the irregular gravity field of the primary body,...
Conference Paper
Full-text available
To carry out precise scientific observations around small bodies, the spacecraft orbit needs to be controlled within some prescribed accuracy over the observation campaign. At the same time, dynamical environments around small bodies are complex and uncertain, leading to highly perturbed, uncertain orbital dynamics. To ensure the desired science ou...
Article
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 uncerta...
Article
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 mic...
Conference Paper
The present paper extends the classically studied chance-constrained optimal control to incorporate continuous-time chance constraints. While the classical approaches provide risk guarantees only at discretized epochs, it is essential for most physical systems to have continuous-time risk guarantees. However, optimization problems with continuous-t...
Article
With appropriate control algorithms, solar radiation pressure (SRP) can be effectively used 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. An optimal control la...
Conference Paper
Full-text available
Guaranteeing safety is a major concern in any space mission design. It is especially important for missions that need to operate in uncertain environment or that require spacecrafts make decisions autonomously. Although the current mission design typically takes heuristic safety margins for the design constraints, such approaches may not capture th...
Conference Paper
Full-text available
This two-part series shares the common objective: design optimal spacecraft trajectories with guaranteed safety, with different focuses in terms of the orbit control approaches. This paper presents a framework for solving risk-aware trajectory design problems with continuous thrust. In contrast to the impulsive maneuver case, convex optimization ap...
Conference Paper
Full-text available
With appropriate control algorithms, solar radiation pressure (SRP) can be effectively exploited as a source of orbit control force around asteroids. SRP-based orbit control utilizes the SRP acceleration for controlling spacecraft orbits by active attitude changes. In previous studies, the authors developed an optimal control law for the SRP-based...
Article
Full-text available
OMOTENASHE and EQUULEUS are two 6-U CubeSats by JAXA and The University of Tokyo to be launched in 2019 onboard of NASA's Exploration Mission 1. This paper presents the nominal trajectories and an overview of the mission analysis work and approaches. EQUULEUS trajectory exploits the Earth -Sun -Moon dynamics to capture the spacecraft into a librati...
Conference Paper
Full-text available
With appropriate control algorithms, solar radiation pressure (SRP) can be effectively exploited as a source of orbit control force around asteroids. A concept of SRP-based orbit control utilizes the SRP acceleration for controlling spacecraft orbits by active attitude changes, for which the authors recently developed an optimal control law with an...
Conference Paper
Beta angle, an angle formed by the sunlight and a spacecraft orbital plane, is an important parameter for science orbit design at primitive bodies. This angle defines lighting conditions and eclipse occurrences and is then used for science observation planning. Not only is this parameter perturbed by the irregular gravity field of the body, it vari...
Conference Paper
Full-text available
With appropriate control algorithms, solar radiation pressure (SRP) can be effectively utilized as a source of orbit control force around asteroids. 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...
Conference Paper
Full-text available
Libration point orbits, in particular those in the Earth-Moon system, have been attracting attention for science and future human space exploration. EQUULEUS is a CubeSat planned to be launched by the NASA's SLS EM-1 vehicle and aims to reach and stay around the Earth-Moon L2 point with a purpose of scientific observation. As EQUULEUS is a piggybac...
Article
Full-text available
This paper describes development strategies and on-orbit results of the attitude determination and control system (ADCS) for the world's first interplanetary micro-spacecraft, PROCYON, whose advanced mission objectives are optical navigation or an asteroid close flyby. Although earth-orbiting micro-satellites already have ADCSs for practical missio...
Conference Paper
This paper presents precision evaluation of a reduced dynamics model for spinning solar sail spacecraft equipped with reflectivity control system. Since the first demonstration on orbit in 2010, the concept of combining reflectivity control system with solar sailing spacecraft has attracted a great deal of attention as a means of fuel-free space ex...
Poster
Full-text available
About mission concept and system design of the world-first cis-lunar space exploration CubeSat EQUULEUS, which will be launched by the SLS EM-1 vehicle of NASA
Conference Paper
Full-text available
This paper presents the time-optimal attitude control for spinning solar sail utilizing the controllability of the membrane reflectivity. Although solar sail is an ideal spacecraft due to its propellant-free acceleration by solar radiation pressure , conventional solar sails require fuel for its attitude control, which prevents completely propellan...

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Projects

Projects (4)
Project
PI: Prof. Jay McMahon, funded by NASA Innovative Advanced Concept (NIAC) program. Kenshiro Oguri is working on trajectory design and mission analysis of AoES spacecraft around small bodies such as Bennu and Itokawa