Missile pose estimation in terminal guidance refers to the technique of estimating missile position and attitude by matching seeker images with pre stored reference images during the terminal phase of missile flight. This paper presents a method for estimating the position and orientation of the missile with respect to a known object using point correspondences between seeker and reference imag...

2 INTRODUCTION The guided missile provides military forces with the capability to deliver munitions rapidly and precisely to selected targets at a distance. This capability establishes an effective means to conduct a wide variety of military missions that range from denying the enemy communications or supply routes, to establishing air superiority, to performing anti-ship cruise missile or ball...

A new kind of adaptive backstepping method is proposed for simplified missile model of pitch channel with time-varying and uncertain parameters. Backstepping control is an effective method for coping with system uncertainties. Adaptive method is integrated with backstepping method and a Lyapunov function is constructed to guarantee the whole system is stable. Through the theoretical analysis an...

The application of a new nonlinear robust control strategy to the design of missile autopilots is presented. The control approach described and demonstrated here is based upon the numerical solution of the Hamilton-Jacobi-Isaacs equation by Successive Galerkin Approximation. Using this approach, feedback controllers are computed by an iterative application of a numerical Galerkin-type PDE solve...

This paper presents a new practical autopilot design approach to acceleration control for tail-controlled skid-to-turn (STT) missiles. The approach is novel in that the proposed parametric affine missile model adopts acceleration as the controlled output and considers the couplings between the forces as well as the moments and control fin deflections. The aerodynamic coefficients in the propose...

Lethality evaluation tests of anti-armor missile systems require flight-test of tactical missiles against threat targets under highly controlled impact conditions. Variables such as terminal dive angle, impact velocity, missile orientation at impact, hit-point on the target, and shot-line through the target all must be carefully controlled and documented to properly evaluate and analyze the dam...

The application of a new nonlinear robust control strategy to the design of missile autopilots is presented. The control approach described and demonstrated here is based upon the numerical solution of the Hamilton-Jacobi-Isaacs equation by Successive Galerkin Approximation. Using this approach, feedback controllers are computed by an iterative application of a numerical Galerkin-type PDE solve...

The fundamental objective of autopilot design for missile systems is to provide stability with satisfactory performance and robustness over the whole range of flight conditions throughout the entire flight envelope that missiles are required to operate in, during all probable engagements. Depending on the control mode (skid-to-turn or bank-to-turn), intercept scenario (such as surface to surfac...

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...