In this paper we consider the problem of air to ground missile guidance system using fuzzy controller. The missile model is assumed as three degree of freedom (3DOF) (assuming the analysis in the vertical plane only).The homing guidance method is used. This paper presents numerical results for applying the fuzzy controller to the missile in different situations of control parameters in differen...

The missile autopilot was designed using linear parameter-varying (LPV) control techniques. The controller provides exponential stability guarantee and performance bound in terms of induced L2 norm for the missile plant. The systematic gain-scheduling approach is motivated by the recent development in LPV control theory and provides a well founded and systematic procedure for high performance m...

This technical memorandum describes a nonlinear guidance law for a single-missile single-target engagement. The guidance relies on the concepts of Lyapunov stability and backstepping, which are constructive methods in nonlinear control theory. The design of the guidance law allows taking into account the nonlinear relative kinematics between the missile and the target, and ensuring ultimate bou...

Discrete-time designs of flight control systems are required for implementation on missile-borne computers. While extensive literature is available on linear discrete-time control system design methods, nonlinear discrete-time control system design techniques have not been discussed to the same degree. This paper presents three nonlinear, discretetime control system design methods. These are th...

A facility was constructed for the study of waterentry, water-exit, and underwater trajectory behavior of small momentum-propelled missiles for varied trajectory launching angles, missile accelerations and velocities, wave fields and condi tions of cavitation. A unique feature is the electromagnetic missile propulsion system. The facility is made principally of non-magnetic and electrically non...

In this paper we consider the problem of air to ground missile guidance system using fuzzy controller which uses Proportional Navigation and Pure Pursuit methods. The fuzzy controller’s rules are defined using Tabu Search (TS). The missile model is assumed as three degree of freedom (3DOF) (assuming the analysis in the vertical plane only). This paper presents numerical results for applying the...

Boost-phase ballistic missile defense is alluring because rocket boosters are easy to detect and track, they are relatively vulnerable due to the large axial loads on a missile under powered flight, the entire payload (single or multiple warheads and midcourse penetration aids) may be destroyed in a single shot, and countermeasures to defeat boostphase defense are more difficult to devise than ...

In order to measure the velocity of a missile, several models have been discussed in this paper. It deals with the tracking and following of single/multiple missile in a sequence of frames and the velocity of the missile is determined. Algorithms have been developed for improving the image quality, segmentation, background subtraction, feature extraction and determining the velocity. Segmentati...

Most publications discussing missile interception systems assume a zero computer response time. This paper studies the impact of computer response time on single-missile single-target and multiplemissile multiple-target systems. Simulation results for the final miss distance as the computer response time increases are presented. A simple online cooperative adjustment model for multiple-missile ...

the guidance system. The types of steering commands vary depending on the phase of flight and the type of interceptor. For example, in the boost phase the flight control system may be designed to force the missile to track a desired flight-path angle or attitude. In the midcourse and terminal phases the system may be designed to track acceleration commands to effect an intercept of the target. ...