Missile

About: Missile is a research topic. Over the lifetime, 12829 publications have been published within this topic receiving 94307 citations. The topic is also known as: guided missile & missiles.

Applying a novel extended Kalman filter to missile―target interception with APN guidance law: A benchmark case study

Abstract: This paper considers the estimation of the target acceleration with unknown dynamics along with other states of a benchmark example of a nonlinear 2D missile-target engagement system in presence of model uncertainties and measurement noises. The objective is to implement the augmented proportional navigation (APN) guidance law for the missile-target interception to minimize the distance between the missile and the target. The estimated target acceleration can be treated as an unknown input to the nonlinear 2D missile-target engagement system. A novel analytical recursive approach referred to as extended Kalman filter with unknown inputs without direct feedthrough (EKF- UI-WDF) is derived with the weighted least squares estimation for an extended state vector including states and unknown inputs which can be any type of signals without prior information. By applying the proposed EKF-UI-WDF approach to a 2D missile-target interception control system, simulation results demonstrate that this approach is capable of (i) estimating the states and unknown input (target acceleration) well, and (ii) achieving more reasonable interception performance comparing with the traditional extended Kalman filter (EKF) approach.

Missile Contagion: Cruise Missile Proliferation and the Threat to International Security

Abstract: Glossary Preface and Acknowledgments PART ONE The Proliferation Context Chapter 1 Introduction Chapter 2 The Ballistic Missile Context Chapter 3 Ballistic Missiles and Regional Competitions Chapter 4 Land-Attack Cruise Missiles Signs of Contagion Chapter 5 Regional Signs of Contagion PART TWO Proliferation Instrumentalities Chapter 6 Knowledge Chapter 7 Narrative Chapter 8 Norms PART THREE Policy Responses Chapter 9 Nonproliferation and Defense Policy Responses Appendix Selected Missile Programs Notes Select Bibliography

Nonlinear H-infinity optimal control for agile missiles

Abstract: Nonlinear #00 optimal control is used to design a pitch plane flight control system for a high-angle-of-attack agile missile. The nonlinear H^ control law is obtained by approximating the solution to the Hamilton-JacobiIsaacs equation. The solution to the partial differential equation is formed using the method of characteristics and is numerically approximated using successive approximations. Nonlinear simulation results using the nonlinear control law are presented. Simulation results testing the algorithms demonstrated excellent performance.