Error Analysis for Guidance Control Parameters of Air to Surface SAR Missile

To develop key design metrics for guidance control system of air to surface SAR missile, the relationship between guidance control parameters and measuring errors is analyzed. According to the non-linear model between guidance control parameters and measured motion parameters in the algorithm of optimal guidance law, linearization method is employed to build the relationship expression between guidance control parameters and measuring errors, thereby analyzing the influence on the accuracy of guidance control parameters by errors of radar's angular channel and range channel, and inertial navigation errors. Equal strength principle is applied to measuring errors allocation method. Through simulating computation, maximum allowable range for guidance control parameter errors and measuring errors are derived.