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.

Autopilot for Missiles Steered by Aerodynamic Lift and Divert Thrusters using Nonlinear Dynamic Sliding Manifolds

Abstract: A new approach to the design of a kinetic-kill longitudinal autopilot steering the missile trajectory by the combination of aerodynamic lift and divert-thrusters (dual-thrusters control) and with its attitude oriented by attitude-thrusters is presented. The proposed approach may increase the total divert acceleration capability by up to 100%, improving the “end-game” intercept accuracy, when such capability is required. The pitch plane autopilot design is based on second order sliding mode control using nonlinear dynamic sliding manifold technique. A robust, high accuracy tracking of the missile normal acceleration guidance command is achieved in presence of considerable model uncertainties created by the interactions between the airflow and the thrusters jets. Results of the computer simulation demonstrate excellent, robust, high accuracy tracking performance of the proposed design.

System and method for the defense of aircraft against missile attack

Abstract: A CM system for the defense of aircraft against missile attack leverages nanocrystal technology to provide safe and reliable protection. The CM system generally includes one or more ground-based laser emitter subsystems, one or more ground-based Doppler-sensitive radar subsystems, an aircraft-based nanocrystal dispenser subsystem, and an engagement control subsystem that governs the operation of the CM system. In response to the detection of a missile within an attack envelope, the engagement control subsystem instructs the dispenser subsystem to release nanocrystals into an area proximate the aircraft. In addition, the engagement control subsystem instructs one or more of the laser emitter subsystems to direct an excitation signal at the dispensed nanocrystal “cloud” to thereby cause the nanocrystals to emit infrared radiation that approximates that of jet engine exhaust. The properties of the nanocrystals and the excitation signal are selected to ensure that the emitted radiation provides an effective decoy for the missile seeker system.

Inference machine using adaptive polynomial networks

Abstract: An inference machine is described which comprises an adaptive polynomial network with the capability of implicitly inferring missing input information contained in time-dependent signals. The proposed network has wide applicability and is characterized by its ability to produce outputs within specified degrees of accuracy when, for example, only four out of ten input signals are available to the network. Specific applications include terminal guidance of a tactical missile when critical signals may be denied. A generic implementation is schematically illustrated.

The Free Flight Aerodynamics Range

Abstract: : The Free Flight Aerodynamic Range, on instrument designed to produce data for the empirical determination of the aerodynamic coefficients of a missile in free flight, is described. The operating techniques and associated experimental procedures used in the grange are given. Examples of air flow data obtained from the space photograph are given. The capabilities, limitations and accuracy of the range are discussed.

Nonlinear Aeroelastic Analysis of a Deployable Missile Control Fin

Abstract: The nonlinear aeroelastic characteristics of a deployable missile control fin have been investigated. Modes from free vibration analysis and a doublet-point method are used for the computation of supersonic unsteady aerodynamic forces. The minimum-state approximation is used to approximate the aerodynamic forces. The fictitious mass modal approach is applied to reduce the problem size and the computation time in the linear and nonlinear flutter analyses. For the nonlinear flutter analysis, the deployable hinge is represented by an asymmetric bilinear spring and is linearized using the dual-input describing function method. From the nonlinear flutter analysis, three different types of limit-cycle oscillations are observed in the wide range of airspeed over the linear flutter boundary. The aeroelastic characteristics of the missile control fin can become more stable due to the existence of the deployable hinge nonlinearity.