Topic
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.
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Patent•
24 Mar 1998
TL;DR: In this article, a soft toy missile is presented, which when let fly by a player and then caught by a catcher, produces upon impact, sounds appropriate to the nature of the missile.
Abstract: A soft toy missile which when let fly by a player and then caught by a catcher, produces upon impact, sounds appropriate to the nature of the missile. When in the configuration of a humanoid figure, the missile includes a body defined by a fabric casing stuffed with a soft compressible filler, the face of the casing having printed thereon the head and torso of the figure. Embedded in the stuffing of the body is a sound-producing unit powered by a battery through an impact-sensitive switch whereby when the missile is caught. The switch turns the unit on to generate sounds that celebrate the catch. Hinged to the body of the figure and extending therefrom are arm and leg appendages, each formed by a fabric sock stuffed with soft compressible material. When the player grasps one of these appendages and whirls the missile to let it fly, the body of the figure then rotates in the course of flight, causing the appendages to stretch out from the body to stabilize the flight. Dispersed throughout the filler are plastic beads which impart to the body of the missile the feel of a bean bag.
40 citations
Patent•
25 May 2001
TL;DR: In this article, an array of barrel assemblies (11) is capable of selectively firing the projectiles from selected barrels whereby a missile is accelerated by the reactionary force generated by said firing of projectiles and the missile is deflected onto a new course or trajectory.
Abstract: Missile (10) includes one or more of barrel assemblies (11) which are displaced from the centre of gravity of missile (10). Each barrel assembly (11) includes a plurality of projectiles axially disposed within the barrel, and each projectiles is associated with a discrete propellant charge for propelling the projectile sequentially from the barrel. Each array of barrel assemblies (11) is capable of selectively firing the projectiles from selected barrels whereby missile (10) is accelerated by the reactionary force generated by said firing of projectiles and the missile is deflected onto a new course or trajectory. This enables missile (10) to be steered to intercept its target even if the target is undertaking evasive manoeuvre. Each barrel assembly (11) can include up to twelve projectiles.
40 citations
16 Aug 2004
TL;DR: In this paper, a new guidance law for intercepting targets in a novel head-pursuit engagement is presented, which positions the interceptor missile ahead of the target, on its flight trajectory, so that both fly in the same direction.
Abstract: *† A new guidance law for intercepting targets in a novel head-pursuit engagement is presented. The guidance law positions the interceptor missile ahead of the target, on its flight trajectory, so that both fly in the same direction. The missile speed is planned to be lower than that of the target, and therefore the target closes in on the interceptor missile. Using this approach the closing speed is significantly reduced relative to a head-on engagement; compared to a tail-chase engagement, the low closing speed is achieved with reduced energy requirements. The guidance law is similar to deviated pure pursuit but with a time varying lead angle. Analytic solutions of the relative trajectories and interception envelopes are given for the case of a non-maneuvering target. The performance of the new guidance law is studied through simulation for the case of a maneuvering target and interceptor employing a continuous or bang-bang maneuver device. The implementation of the new guidance scheme may dramatically reduce the requirements from missile subsystems for the interception of high speed targets, such as ballistic missiles.
40 citations
TL;DR: A framework to determine the performance or reliability of a complex system and a case study in missile reliability that focuses on the assessment of a high fidelity launch vehicle intended to emulate a ballistic missile threat is developed.
40 citations
TL;DR: It is shown, using Lyapunov stability theory, that the proposed robust adaptive control scheme can give sufficient tracking capability and stability for a feedback-linearized STT missile with aerodynamic uncertainties.
Abstract: A robust adaptive control scheme is proposed that can be applied to a practical autopilot design for feedback-linearized skid-to-turn (STT) missiles with aerodynamic uncertainties. The approach is to add a robust adaptive controller to a feedback-linearizing controller in order to reduce the influence of the aerodynamic uncertainties. The proposed robust adaptive control scheme is based on a sliding mode control technique with an adaptive law for estimating the unknown upper bounds of uncertain parameters. A feature of the proposed scheme is that missile systems with aerodynamic uncertainties can be controlled effectively over a wide operating range of flight conditions. It is shown, using Lyapunov stability theory, that the proposed scheme can give sufficient tracking capability and stability for a feedback-linearized STT missile with aerodynamic uncertainties. The six-degree-of-freedom nonlinear simulation results also show that good performance for several uncertainty models and engagement scenarios can be achieved by the proposed scheme in practical night conditions.
40 citations