Realization and Simulation of Guidance Laws Applicable to Maneuvering Target Attacking

To make the missile obtain minimum miss distance at the limited time of terminal guidance while keeping the maneuvering acceleration within the missile's realistic acceleration capability,we studied the optimum guidance law suitable for attacking sinusoidal maneuvering targets and compensation guidance law for sinusoidal maneuvering.The realization method was analyzed,a Kalman filter was designed for estimating the target state information,and the homing guidance loop model was established.Simulation results indicated that the more accurate the measurement and the more information known,the better the estimate performance.The influence of the following factors on guidance precision was also studied: missile overload limit,measurement error,target state estimation precision and selection of guidance law.