A midcourse guidance law for air-to-air missiles

Abstract

A near-optimal midcourse guidance law incorporating a linear combination of flight time and terminal specific energy as the performance index is derived using singular perturbation theory. The reducedorder model consists of the down range, cross range, specific energy and the heading angle state variables. Two approaches are developed to account for altitude and flight path angle neglected in the reducedorder solution. Implementation logic and simulation results are .given.