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.

The lessons and non-lessons of the air and missile campaign in Kosovo

Abstract: The Lessons and Non-Lessons of the NATO Air and Missile Campaign in Kosovo The Historical Background: The Course and Character of the NATO Campaign The Grand Strategic Aspects of Kosovo: The "Whys" and "Hows" of the War and the Implications for Strategy and Force Planning The Strategic Impact and Military Effectiveness of the Air and Missile Campaign The Problems of "Perfect" and "Bloodless" War NATO Reporting on the Effectiveness of the Air and Missile Campaign Strategic Bombing The Air and Missile War and Serbian Air and Land Force Targets The "Ground Option": The Possible Impact of NATO Planning for an Invasion The "Ground Option": The Role of the KLA Detailed Lessons and Issues of the Air and Missile Campaign Beyond Air and Missile Power: The Ground Phase of Kosovo, Nation-Building, and Continuing Instability in the Balkans

Impact of Solid Missiles on Concrete Barriers

Abstract: Semianalytical formulas are developed to predict scabbing and perforation thicknesses for reinforced concrete panels subjected to impacts by solid steel missiles. The scabbing thickness is defined as the thickness that is just enough to prevent the peeling off of the back face of the panel opposite to the face of impact; perforation thickness is defined as the thickness that is just enough to allow a missile to pass through the panel without exit velocity. In the development of these formulas, simplified models for scabbing and for perforation were assumed; engineering mechanics principles were applied in the formulation, and the Bayesian statistics were utilized to determine coefficients in these formulas. The Bayesian approach was used because it can handle the estimation of parameters better than the classicial statistical method when suitable data are limited, as is presently the case in low velocity missile impact on concrete panels.

Hybrid Guidance Law for Approach Angle and Time-of-Arrival Control

Abstract: A new derivation of an optimal missile guidance law is presented. The guidance law derived is an extension of previously published versions of explicit guidance in that gravity compensation is incorporated in an optimal fashion. Performance of the extended guidance law is demonstrated via simulation comparisons with generalized vector explicit guidance andKappa guidance, both of which have appeared previously in the literature. The new law is then incorporated into a hybrid guidance scheme that allows the specification and satisfaction of a desired time-of-arrival constraint. Performance of this capability is also demonstrated via simulation examples. Finally, an approach to coordinating desired times of arrival among a group of cooperatingmissiles to achieve simultaneous target intercepts or missile rendezvous is presented.

Compound Control Methodology for Flight Vehicles

Abstract: Overview of Sliding Mode Control.- Overview of Active Disturbance Rejection Control.- Overview of Flight Vehicle Control.- The Descriptions of Flight Vehicle.- SMC for Missile Systems Based on Back-Stepping and ESO Techniques.- Adaptive SMC for Attitude Stabilization in Presence of Actuator Saturation.- Adaptive Nonsingular Terminal Sliding Mode Control for Rigid Spacecraft.- Attitude Tracking of Rigid Spacecraft with Uncertainties and Disturbances.- SMC for Attitude Tracking of Rigid Spacecraft with Disturbances.- Missile Guidance Law Based on ESO Techniques.- Missile Guidance Laws Based on SMC and FTC Techniques.- Cooperative Attack of Multiple Missiles Based on Optimal Guidance Law.

Geometric analysis of flight control command for tactical missile guidance

Abstract: In this paper, unlike other developments in missile guidance which rely on solving a system of coupled nonlinear differential equations, an innovative approach is presented for studying tactical missile guidance. The moving orthogonal coordinate system of classical geometric curve theory is similar to the stability axis system used in atmospheric flight mechanics. Based on this similarity, the Frenet-Serret formula of classical geometric curve theory together with the concept of a pseudo-missile pointing velocity vector are used to analyze and design a missile guidance law. The capture capability of this guidance law is qualitatively studied by comparing the rotations of the velocity vectors of missile and target relative to the line of sight vector. Sufficient initial conditions for capture are found by following sequences of engagement geometry with different initial conditions.