Orbital interception correction based on impulsive control

In this paper, orbit interception correction strategy using fixed-time constraints is considered. This work developed an optimal method for the problem based on the linear quadratic with discrete-time impulsive control. The linearized model was set up using the perturbation guidance equation, and the control system model was simplified. The control strategy was obtained by discrete impulsive optimization based on the discrete Dynamic Programming method. The calculation for the controller was extended. A numerical case was simulated to validate the control strategy´s effectiveness. Since the simplified model and control method is easy to calculate, it is suitable for engineering application in midcourse interception guidance.