All-aspect near-optimal guidance law

Abstract

In this paper, a new guidance law known as the all-aspect proportional navigation (AAPN) guidance law is formulated. AAPN is a modification of traditional proportional navigation, with an additional term added to improve performance at large heading error angles. The missile guidance problem is first formulated as an optimal control problem and solved using a combined genetic algorithm-shooting method. The problem is repeatedly solved at various heading error angles. By employing Chebychev polynomial fitting, we can then determine the parameters of the AAPN. Subsequently, AAPN is compared against the proportional navigation guidance law as well as the optimal solution. The results clearly show that AAPN outperforms PN at large heading error angles. Also, its performance is only slightly inferior to the optimal solution.