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...

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...

The overload control of missile system is researched under the condition that the control direction is unknown. A nussbaum gain strategy is adopted to solve the unknown control direction problem for the linear model of missile motion of pitch channel . The backstepping technology and integral action are used to cope the system uncertainty. A novel type of control law, which is only consisted of...

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...

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. ...

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...

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...

Radar Seeker is used in missile system for detection and tracking a target. It will be integrated in the nose cone of the missile. During testing and launching of the missile all necessary important parameters and status of the seeker are collected for analysis to ascertain the health of the Seeker. Similarly the configuration and control of the seeker is to ensure the proper mode of operation ...

Due to their potential for reducing the weapon size and efficiency, design methods for realizing hitto-kill capabilities in missile systems are of significant research interest in the missile flight control community. As defined in this paper, hit-tokill capability requires the missile to consistently achieve point-mass miss distances less than half the minimum dimension of the target. It has b...

This investigation addresses a nonlinear terminal guidance/autopilot controller with pulse-type control inputs for intercepting a theater ballistic missile in the exoatmospheric region. Appropriate initial conditions on the terminal phase are assumed to apply after the end of the midcourse operation. Accordingly, the terminal controller seeks to minimize the distance between the commanded missi...