A new optimal guidance law for air-to-air missiles against evasive targets

A new optimal guidance law (OPG) for air-to-air missiles, based on the desi gn concept of decreasing the acceleration requirement commanded in the fina l phase of engagement, is presented. The closed-form solution of the OPG is derived analytically from the time-varying linear state equations composed of the line-of-sight angle and line-of-sight rate. The optimal proportiona l navigation law and augmented proportional navigation law, where both the navigation constants are 3, have been proven to be simplified versions of t he OPG. The performance of the OPG is evaluated and compared with that of t he true proportional navigation law (TPN) and augmented proportional naviga tion law (APN) in terms of the miss distance, interception time and energy expenditure.