The present invention discloses a method and
system for magnetically controlling solar capture of a
satellite's intermediate
inertia axis. When a
satellite enters a safety mode, the
solar angle of the
satellite's safety mode in a continuous time period is obtained, the solar state of the satellite's intermediate
inertia axis is determined based on the
solar angle, and the satellite is determined to enter a solar capture mode or a
spinning mode based on the solar state. When the satellite enters the solar capture mode, the solar state of the satellite's intermediate
inertia axis is determined based on the
solar angle of the main plane. When the intermediate inertia axis is within the solar range, the satellite's gyroscopic
angular velocity and solar angle are obtained, and whether the satellite enters a
spinning mode or remains in the solar capture mode is determined based on the gyroscopic
angular velocity and solar angle. The method enables the satellite to adopt a minimum control configuration and energy, controls the satellite's attitude based on the satellite's solar angle and gyroscopic
angular velocity, ensures that a sailboard in a sunlit area can efficiently capture the
solar energy of the intermediate inertia axis, and achieves rapid replenishment of satellite energy.