Attitude control system of a space membrane using electromagnetic torque

抄録

This study proposes a novel attitude control method for a space membrane using electromagnetic torque in a space mission. Currently, an increasing number of satellites are presently utilizing extensible large area structures after launch in orbit. Previously, attitude control of a large deployed membrane has been achieved by thrusters. Although, the attitude can be controlled rapidly, the thrusters make the space system more complicated and lower reliable system. Moreover, the thrusters make the limitation of fuel, thus the attitude control operations should be carefully scheduled including contingency plans. As another attitude control system, attitude control using solar radiation pressure was also proposed. Although the system does not need fuel, the membrane needs longer period for attitude maneuvers with small solar radiation torque, since the membrane has a large angular momentum with spin angular velocity to keep the deployed membrane shape with central fugal force. In this study, electromagnetic wires placed on a membrane are utilized for attitude control by the interaction with an outer magnetic field. With the proposed system, the satellite can control its attitude without fuel, which makes space systems more simple and reliable. Furthermore, in this system, electrical wires placed on the edge of the membrane generate the hoop magnetic force to keep membrane shape without central fugal force by spin angular velocity. Thus, the membrane does not need to have spin angular velocity, which results in smaller angular momentum in the membrane. Therefore, with the proposed method, the membrane can achieve more rapid attitude control maneuver. Finally, numerical simulations are conducted to assess the usefulness of the proposed method using Particle-Based Model.