Monte Carlo simulation of midcourse guidance system for medium-range air-to-air missiles

Our aim was to study the feasibility of using a midcourse guidance system, which was constructed from proportional guidance law and inexpensive SINS (strapdown inertial navigation system), to ensure the acquisition capability of medium-range air-to-air missiles. The essentials of midcourse guidance are studied and a simulation scheme is put forward for exploring the feasibility. The effect on the acquisition of initial misalignment, initial sensor errors, target position and velocity errors, target maneuvering uncertainty, seeker drift error, time delay error and altitude error is analyzed. The Monte Carlo simulation results show that the target acquisition can be guaranteed.