Close-Range Reconnaissance Control Method of Micro-Satellite with Hybrid Thrust Maneuver Configuration

In this paper, considering the thrust control problem of small satellites in GEO for close-Range reconnaissance, a control strategy based on hybrid thrust which integrates large impulse thrust with small continuous thrust is proposed. For pulse thruster, a multi-pulse thrust closed-loop control model based on the idea of switching control is constructed with maximum thrust constraint. Additionally, a genetic algorithm is introduced to realize the autonomous setting of the optimal parameter combination. Aiming at the the transition from the fly-around state to the hovering state, the fuel-optimized control method with limited fuel constraints is deduced based on a complex relative dynamics model incorporating continuous thrust integration. Then, according to the satellite hovering state characteristics, the finite thrust control model for hovering hold is derived to realize high-precision hovering observation. Finally, the simulation results of the 3D virtual platform and figures prove the feasibility and effectiveness of the hybrid thrust maneuver strategy for small satellites.