Fuzzy Logic-based Terminal Guidance with Impact Angle Control

Abstract

This paper presents a new formulation of terminal guidance law which controls the impact attitude angle while minimising the miss distance. The formulation is based on the fuzzy logiccontrol approach. Unlike many prevalent designs, the proposed guidance law does not require linearisation of missile-target engagement model. Numerical simulation results demonstrate that the proposed guidance law offers satisfactory performance, fulfilling its design goals.

A guidance law for avoiding specific approach angles against maneuvering targets

“…different ways: 1) optimal control and differential gamebased guidance [3]- [12], 2) sliding mode control-based guidance [13]- [16], and 3) proportional navigation (PN)-based guidance [17]- [23]. Several other methods like fuzzy logicbased formulation [24], relative circular navigation [25], [26] have also been used to accommodate impact angle constraints. It could be noted that most of the literature on impact angle have been focused on stationary targets, with some consideration for moving (but non-maneuvering) targets, but very few results exist in the literature which deal with the impact/approach angle problem against highly maneuvering targets.…”