Design of Deorbit Parameters for BEIDOU MEO and IGSO Satellites Based on Long-Term Eccentricity Evolution

Abstract

Useless satellites permanently stay in operational orbit occupy valuable orbital resources, and that increase the collision risk of other active satellites. If the useless satellites breakup, the massive new space debris will have catastrophic effect on running circumstance of active satellites. Therefore it is important to take deorbit maneuver if the satellites are in the end of lifetime. Setting up reasonable deorbit parameters and avoiding secondary disasters is very crucial. The paper studies the long-term evolution of eccentricity and semi-major axis that result from a resonance of the third body and the nonspherical gravitational perturbation. On the basis of the phenomenon, analysis and calculates the biggest change in perigee attitude. According to the long-term variation of eccentricity, the MEO (Medium Earth Orbit) and IGSO (Inclined Geosynchronous Satellite Orbit) satellites in the BEIDOU navigation constellation studied. Designing the deorbit parameters to reduce their orbital lifetime or make sure that the perigee of disposal orbit is not below the protected region in 100 years. The simulation results show that the deorbit parameters are reasonable and meet the requirements of IADC (Inter-Agency Space Debris Coordination Committee). It can provide reference for the deorbit strategy of the BEIDOU navigation satellites and the other MEO or IGSO Satellites at the end of life.