Optimal Guidance Law Considering Coupled Orbit-Attitude for Space Target

Space debris seriously threaten the safety of artificial spacecraft in orbit. To achieve the rapidity of space debris capturing and removal, an optimal guidance law considering coupled orbit-attitude for space non-cooperative target is proposed. Firstly, a relative kinematics model of the spacecraft and the target is constructed, and a coupling control strategy based on time-division multiplexing theory is designed. Then, the optimal guidance law with minimum energy consumption as the cost function is designed, and the acceleration command is adjusted through vector decomposition to reduce the impact of velocity leading angle on the deviation accuracy. Finally, the designed guidance law is simulated and verified in the case of thrust attenuation error, and compared with proportional guidance law. The results show that the proposed optimal guidance law can reduce energy consumption by 56.9% while satisfying the guidance accuracy.