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.

Integral data acquisition capacity

Abstract: Provided is a modified configuration that permits operation of instrumentation onboard platforms that may experience severe environmental conditions. The instrumentation permits autonomous acquisition of performance data. Acquired data may be recorded for later playback as well as provided to the platform's operator in real time in multiple formats, such as warning lights, digital displays, video, or audio. An application would be for sensor systems used on an automobile to record performance data, providing a warning when routine maintenance is due or a catastrophic failure is imminent. A specific application uses a flight-certified missile launcher pod on an F/A-18 aircraft, as incorporated in the aircraft's wingtip and modified to hold instrumentation conforming, at least in part, to the launcher pod's internal dimensions. This arrangement enables autonomous onboard display and recording of data from the captive carry testing of an AIM-9X missile and follow-on designs that may be based on the AIM-9X.

Non-singular terminal dynamic surface control based integrated guidance and control design and simulation

Abstract: In this paper, a novel cascade type design model is transformed from the simulation model, which has a broader scope of application, for integrated guidance and control (IGC). A novel non-singular terminal dynamic surface control based IGC method is proposed. It can guarantee the missile with multiple disturbances fast hits the target with high accuracy, while considering the terminal impact angular constraint commendably. And the stability of the closed-loop system is strictly proved. The essence of integrated guidance and control design philosophy is reached that establishing a direct relation between guidance and attitude equations by “intermediate states” and then designing an IGC law for the obtained integrated cascade design model. Finally, a series of simulations and comparisons with a 6-DOF nonlinear missile that includes all aerodynamic effects are demonstrated to illustrate the effectiveness and advantage of the proposed IGC method.

Interceptor guidance for boost-phase missile defense

Abstract: A fire control system for a boost phase threat missile includes sensors for generating target-missile representative signals, and a multi-hypothesis track filter, which estimates the states of various target hypotheses. The estimated states are typed to generate hypotheses and their likelihoods. The states, hypotheses and likelihoods are applied to a multihypothesis track filter, and the resulting propagated states are applied to an engagement planner, together with the hypotheses and likelihoods. The engagement planner initializes the interceptor(s). Interceptor guidance uses the initialization and the propagated states and typing information to command the interceptor.

Jettisonable protective cover device

Abstract: An in-flight jettisonable protective cover device for protecting fragile, accurate, radomes or signal-responsive components for the major portion of a flight which is capable of being jettisoned in one piece at supersonic speeds from a guided missile, other air vehicles, or space vehicles. The cover device is for use, for example, in combination with a guided missile having a shell structure, a nose portion, and a radome in the missile nose. The cover device is attached to the missile nose for covering the radome such that an inner space is defined. A plurality of shear pins or other quick-release mechanisms attach and retain the cover device to the missile shell. A source of low pressure gas pressurizes the inner space to approximately 50 psi. A rapid-discharging, high pressure gas cartridge produces a high pressure gas for exerting a pressure force on the aft face of the cover device. The pressure forces are sufficient to shear the retaining pins and accelerate the cover device sufficiently forward to clear the missile body at supersonic speeds. The missile angle of attack creates lateral aerodynamic forces on the cover deivce to clear it from the missile. The sensitive radome can then be used for high precision detection and tracking as required at intercept.

Ramjet Powered Missile Design Using a Genetic Algorithm

Abstract: A methodology for developing optimized designs for symmetric - centerbody ramjet powered missiles, using genetic algorithms as the central driver for the system optimization process, has been developed. This paper contains discussion of that methodology and shows results for a typical design scenario.