Deorbit Process Using Solar Radiation Force

摘要

The solar radiation force can be used as a propulsion source to assist in the deorbit process in three-axis stabilized satellites with the capability to move their solar panels. This is achieved by rotating the solar panels at appropriate times to achieve an effective increment in the semimajor axis during a full orbit. For a satellite with a total solar radiation force of 0.00026 N, a weight of 1280 kg, and assuming that 75% of the solar radiation force is concentrated on the solar panels, an average increment in the semimajor axis per day of 0.110 km and an annual increment of 40.23 km can be obtained. The growth rate of orbit perigee altitude will be constant and nearly the same as the growth rate of the semi-major axis when the initial eccentricity vector is properly chosen. The Inter-Agency Debris Coordination Committee recommends a disposal orbit with a perigee altitude higher than 235 km above the ideal geosynchronous radius of 42,164 km. At a perigee altitude growth rate of 40.23 km/year, it will take the satellite more than 5.8 years to reach the recommended orbit.