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.

Application of Sliding Mode Control to Bank-To-Turn Missile Systems

Abstract: Sliding mode control is applied to design autopilot for HAVE DASH II bank-to-turn-(BTT) missile systems. The design is evaluated using six degree of freedom simulation and shows a significant improvement over the feedback linearization approach.

Design of three-dimensional missile guidance law via tunable nonlinear H/sub /spl infin// control with saturation constraint

Abstract: The three-dimensional missile guidance law with saturating actuator is proposed for the pursuit of an unpredictably manoeuvring target. The proposed guidance law achieves a satisfactorily robust performance without having to solve a complicated nonlinear Hamilton–Jacobi partial differential inequality and without relying on Takagi–Sugeno linear fuzzy models. In the proposed guidance scheme, the nonlinear part of the relative motion equations between the missile and target is first cancelled. Then, a tunable state feedback guidance law is designed to eliminate the effect of external disturbance. The conditions of tunable parameters are also proved to achieve the desired goal. The proposed guidance law can achieve reduced interception time than others, yet it is considerably simpler. An example is proposed to confirm it.

Computational Comparisons of the Interaction of a Lateral Jet on a Supersonic Generic Missile

Abstract: *† ‡ The paper deals with the comparison of computations made at DLR and ISL on the interaction between a lateral jet issuing from a generic missile body and the oncoming supersonic cross-flow. Steady-state numerical simulations are carried out by 3D, viscous, turbulent, Reynolds-Averaged Navier-Stokes codes; at DLR, a hybrid mesh is used for the TAU calculation, whereas at ISL a hexahedral mesh is used for the CFX computation. Experimental data acquired in the DLR wind tunnel TMK in Cologne act as references for the computations. Calculations are made for a cross-flow Mach number of 2.8, for angles of attack of -5, 0 and 10 degrees and for a jet ejection pressure ratio of 100. The test model is a cone-cylinder-flare body with a side-jet nozzle located in the cylindrical part, representing a simple generic high-speed missile configuration. Surface pressure measurements were carried out in order to validate the corresponding computations. The agreement between the computations and the experiments in terms of pressure distribution is obtained with a high degree of accuracy by the codes, in spite of some small discrepancies.

Missile guidance with constrained terminal body angle

Abstract: A novel missile guidance law that simultaneously minimizes the miss distance and imposes a predetermined terminal body angle is presented. The guidance law is derived by analyzing an interception scenario within the framework of a linear quadratic (LQ) terminal control problem. The derivation is for first order linear missile dynamics and a non-maneuvering target. The performance of the proposed guidance law is demonstrated in a planar interception scenario.