This paper shows; that, in some conditions we can obtain the exact solution for a missile and an aircraft differential games which minimizes and maximizes the essential pay-off of the problem: the miss distance, without employing any linearized approximation. The idea of our method is, by starting from the aircraft one-sided optimal control solution against a PNG missile, which maximizes the mi...

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 ...

25­ INTRODUCTION The key objective of this article is to provide a broad conceptual foundation with respect to homing guidance but with sufficient depth to adequately support the articles that follow. During guidance analysis, it is typical to assume that the missile is on a near-collision course with the target. The implications of this and other assumptions are discussed in the first section,...

The principle of dynamic programming is used to develop a digital computer software package for determining for each of several subsystems the optimal numerical integration algorithm from among given candidate techniques. As by-products, the corresponding optimal step sizes and error contributions of the subsystems are provided to the user. The deveiloped program minimizes subsystem sum-squared...

This paper addresses the problem of bearings only and bearings and extent tracking for closed loop missile guidance systems using particle methods compared with derivative free methods. Lack of observability is a typical phenomenon for the bearings only tracking problem. We demonstrate that exploiting angular extent information does help mitigating the lack of observability issues. The simulati...

A capture region for missile guidance laws under field-of-view constraint is analyzed. To make a missile intercept a non-maneuvering target, physical constraints including seeker`s field-of-view and acceleration limit should be considered, because these constraints may restrict maneuver of the interceptor. The characteristics of look-angle constraint guidance laws is studied, and feasible traje...