In this laboratory, we study the dynamics (astrodynamics) related to the trajectory and attitude of space probes and rockets, as well as related physics and mathematics. Utilizing my experience in actual space missions at JAXA, etc., I am working on real mission issues from both engineering and science. In terms of education, through activities such as graduation research, we strive to develop human resources who are capable of independently making plans and taking action, and who can think deeply about things. In addition, we aim to produce human resources who can play an active role globally by making use of our many years of overseas research experience at ESA.
Basic Information
Faculty name/Affiliation
Kenju Nakamiya / Department of Aerospace Engineering, Faculty of Faculty of Science and Engineering and Engineering
Specialized Fields
Orbit/attitude control, celestial mechanics
Research theme
Research on Orbit and Attitude Control of Space Probes
Research on mathematics and physics derived from space exploration mission design
Research keywords
Orbit design, 3-body problem, optimization problem, relativity, magnetism, group theory
Analysis of orbital dynamics in the circle-restricted three-body problem I am analyzing the orbital characteristics near the equilibrium point (Lagrange point) where the gravitational forces of two bodies are balanced in the circle-restricted three-body problem. The vicinity of the Lagrangian point is suitable for observing the sun and outer space because the relative position with respect to the sun and the earth does not change, and a stable thermal and gravitational environment can be obtained.・We are conducting observations (such as the James Webb Space Telescope, which is said to be the successor to the Hubble Space Telescope). The study of this research can contribute to missions near Lagrangian points, which are expected to increase in the future.
Multi-objective optimization problem in space exploration mission design For example, when flying a space probe from Earth to Mars, various points such as the fuel for orbit control going to Mars, the flight period until reaching Mars, the maximum power consumption of the probe, and the time that can be communicated with the ground station are taken into account. You have to design the mission by Therefore, we formulate a multi-objective trajectory optimization problem that seeks the optimal solution within the constraint conditions using these multiple items as objective functions, and select the desired values from the obtained design variable results (Pareto solution) and use them for space missions. We are studying the method of designing
