Orbital attitude control device, satellite, orbital attitude control method, and recording medium

An orbital attitude control method for orbital transfer toward a geostationary orbit for a satellite including a solar array panel and an attitude control actuator, the orbital attitude control method comprising:

• calculating, during the orbital transfer of the satellite toward the geostationary orbit, an ideal thrust axis direction based on information of a predetermined orbit of the satellite;
• calculating, during the orbital transfer of the satellite toward the geostationary orbit, an ideal attitude of the satellite based on the ideal thrust axis direction and a solar direction;
• and
• calculating, during the orbital transfer of the satellite toward the geostationary orbit, a control torque to control the attitude control actuator based on an estimation attitude of the satellite, the solar direction, a drive constraint of the attitude control actuator, and the ideal attitude, wherein
• the calculating of the control torque during the orbital transfer of the satellite toward the geostationary orbit includes calculating an ideal control torque that makes the attitude of the satellite follow the ideal attitude and a torque restraint plane in which the solar direction is orthogonal to a rotational axis of the solar array panel, defining an evaluation function obtained by weighting a distance from the ideal control torque and a distance from the torque restraint plane and then summing the weighted distances, and calculating the control torque that allows the drive constraint to be satisfied and the evaluation function to be minimized.

A non-transitory computer-readable recording medium storing a program, the program causing a computer for controlling, for orbital transfer toward a geostationary orbit, an orbit and an attitude of a satellite including a solar array panel and an attitude control actuator to function as:

• an ideal thrust axis direction calculator to calculate, during the orbital transfer of the satellite toward the geostationary orbit, an ideal thrust axis direction based on information of a predetermined orbit of the satellite;
• an ideal attitude calculator to calculate, during the orbital transfer of the satellite toward the geostationary orbit, an ideal attitude of the satellite based on the ideal thrust axis direction and a solar direction;
• and
• a control torque calculator to calculate, during the orbital transfer of the satellite toward the geostationary orbit, a control torque to control the attitude control actuator based on an estimation attitude of the satellite, the solar direction, a drive constraint of the attitude control actuator, and the ideal attitude, wherein
• the control torque calculator calculates an ideal control torque that makes the attitude of the satellite follow the ideal attitude and a torque restraint plane in which the solar direction is orthogonal to a rotational axis of the solar array panel, defines an evaluation function obtained by weighting a distance from the ideal control torque and a distance from the torque restraint plane and then summing the weighted distances, and calculates the control torque that allows the drive constraint to be satisfied and the evaluation function to be minimized.