Abstract:

The impulse force control guidance system belongs to the complex hybrid control system due to the discreteness of impulse force control and the continuity of missile dynamics. A dynamics model of impulse force control missile is established. And, varying period discrete modeling of the impulse force control guidance loop is completed by finding the equivalence between the impulse force control guidance system and the amplitude pulse frequency modulator (APF-M) control system. Then, the impact of pulse jet impulse, pulse jet ignition waiting time and gravity on the guidance loop is obtained via analyzing the guidance loop stability using the slidingmode control theory. Moreover, a bias threshold gravity compensation method is proposed and then simulated. The simulation results verify the gravity compensation method, and demonstrate the conclusion that increase pulse jet impulse and decrease pulse jet ignition waiting time can slow down the speed of boresight error divergence.