Hybrid thrust optimization control for orbit interception correction

This paper considers a hybrid optimization control problem by mixing the low and impulsive (high) thrusts, which is a continuous and fixed-time interval control strategy for impulsive control of the orbit interception correction. Initially the linear system model is established and linearized by two-body equations of motion. The hybrid linear control system is analyzed and control law is obtained by solving hybrid Riccati algebraic equations. Finally, by simulation of a numerical example effectiveness of the method is validated. The results show that the hybrid control method combines the advantages of impulsive and low thrusts, giving comprehensive performance better than the method using impulsive thrust control alone.