Control policy design for missile using impulsive attitude control motors

Four factors are used to describe the influence of jet interaction for the missile using impulse attitude control motors in the equations of motion. Considering quick response with little sacrifice on steady state tracking accuracy, a control policy is designed in pitch plane. The command to ignite motors is issued periodically. After analyzing the dynamics of the missile during one ignition period, the Lyapunov function is used to get the discrete elevator command and ignition command. Simulation results show that the miss when using impulsive attitude control motors is more less than that when aero-fin used alone, and hence the efficiency of control strategy and the superiority of using lateral thrust are verified.