arXiv subjects

Shinji Hokamoto

Publications and source records attributed to Shinji Hokamoto.

2 recordsLinked to original sources

arXiv2026

Design of low-energy transfers in cislunar space using sequences of lobe dynamics

Dynamical structures in the circular restricted three-body problem (CR3BP) are fundamental for designing low-energy transfers, as they aid in analyzing phase space transport and designing desirable trajectories. One of these dynamical structures, lobe dynamics, can be exploited to achieve local chaotic transport around celestial bodies. This study proposes and fully validates a systematic method for designing low-energy transfers by combining multiple sequences of lobe dynamics, building upon the authors' prior preliminary framework. A graph-based framework is developed to explore possible transfer paths between departure and arrival orbits, reducing the complexity of the combinatorial optimization problem for fuel-efficient transfer design. Using this graph, low-energy transfer trajectories are constructed by connecting chaotic orbits within lobes. The resulting optimal trajectory in the Earth--Moon CR3BP is then converted into an optimal transfer in the bicircular restricted four-body problem via multiple shooting. This transfer is compared with existing optimal solutions to demonstrate the effectiveness of the proposed method.

nlin.CD↗

arXiv2025

Attitude Control of Spacecraft for Autonomous Attenuation of Unknown Periodic Disturbance Torque

Recently, deep space exploration, especially focusing on halo orbits, the periodic orbits of the Moon, has been widely studied. The spacecraft in halo orbits performs periodic orbital motion, which affects the attitude motion by periodic disturbances. The conventional attitude control method, PD control, is widely used, but its application to periodic disturbance attenuation is inefficient. To address these challenges, this study proposes a predictive Repetitive Control (RC) approach that addresses periodic disturbances, particularly GG torque, by exploiting the periodic nature of the system dynamics. The proposed method is also applied to the case of using a Reaction Wheel (RW) as an attitude control actuator. Despite the inherent challenges posed by RW limitations, including saturation torque and transmission delay, our predictive RC approach effectively mitigates these effects. Numerical simulations demonstrate the robust performance of the proposed method in maintaining attitude control for spacecraft traversing halo orbits near the Earth-Moon $L_2$ point, validating its potential for future deep space exploration missions.

astro-ph.EP↗