Hybrid-triggered orbit-attitude coupled station keeping control of a spacecraft with pure thrusters

Abstract

Abstract. This paper introduces a specialized attitude-orbit control system designed for three-axis stabilized micro-spacecraft facing the challenge of maintaining orbit radius near small asteroids. Utilizing a fixed main thruster and inclined small thrusters, the system addresses intense orbit-attitude coupling. An intermittent hybrid-triggered control method optimizes main thruster alignment with the asteroid's center of gravity and maintains the spacecraft's orbit within a specified range. The system responds to attitude deviations by activating only the inclined thrusters and triggers overall control for specified orbital conditions, ensuring spacecraft safety. Simulation results confirm the efficacy of the proposed control system.