Relative Control Deployment Strategy of Continuous Low-thrust Satellites in Mage-constellation

Abstract

Abstract The semimajor axis relative control strategy is mostly used in the deployment of mage-constellation satellites. This paper proposes the single orbit element relative control method and the multiple orbit elements relative control method. The first method accumulates the semimajor axis difference and the inclination difference in the time domain to generate the required difference at the Right Ascension of Ascending Node (RAAN) and calculates the mathematical limit to distinguish the high and low inclination when the energy consumption is the least. The second method uses the Hamilton function to deduce the motion characteristics of the satellite under continuous low-thrust, obtains the mathematical models of the optimal transfer of speed and inclination, speed and RAAN, and gives the continuous maneuver strategy of the small satellite. Finally, based on the TLE data of the Starlink satellite, an example is analyzed, and the two control strategies are simulated and compared. The simulation results show that the multi-orbit element simultaneous control is superior to the single-orbit element control in deployment efficiency, and the time cost is lower in engineering practice.