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.

Extended state observer-based robust pitch autopilot design for tactical missiles

Abstract: In this article, a new design based on the extended state observer (ESO) technique for the pitch autopilot of a tail-controlled, skid-to-turn missile is proposed. The pitch-plane dynamics with the ...

Ship self-defense missile weapon system

Abstract: The present invention provides a ship self-defense missile (SSDM) weapon system for launching a plurality of light weight missiles from an existing vertical tube launch infrastructure. The system for vertically launching missiles from a ship comprises a plurality of tiers having a top tier and a bottom tier in which tier supports a plurality of missiles. The tiers are set into a launch canister having an interior wall to form a vertical stack in the launch canister. A launch means is used for selectively launching at least one of the plurality of missiles from the top tier. A means for ejecting ejects the top tier is depleted of missiles. A vertical movement means raises and lowers the tiers within the launch tube and the vertical movement means raises next tier in the vertical stack into a position to launch. Preferably, the vertical movement means is a jack screw threaded though each tier in the vertical stack and the means for ejecting involves screwing a depleted tier off the jack screw and initiating explosives at the base of the depleted tier to allow the next tier access to a ready to fire position.

Implementation of Optimal Guidance Laws Using Predicted Missile Velocity Profiles

Abstract: A class of weighted control-effort minimizing guidance laws are derived for missiles of varying velocity. As a practical weighting function, we consider a function of air density and missile velocity parameterized by positive real numbers. The resulting optimal guidance problem can be interpreted as the drag minimization problem for subsonic or supersonic missiles, depending on what parameters are used. This approach is extended easily to solve the drag minimization of a typical antiaircraft missile system with an arbitrary velocity proe le and arbitrary drag characteristics, as demonstrated by a simulation study. We also present analytical results on how the guidance gain of the optimal law varies according to the values of the parameters. Because the optimal guidance laws make use of the future missile velocity proe le, one critical issue is how to implement the laws. To avoid the dife culty that an inaccurately predicted missile velocity proe le causes the guidance command to blow up in the last part of the engagement, we suggest two simple on-line velocity-proe le updating schemes, which considerably alleviate the problem.

Nonlinear Autopilot Design for an Asymmetric Missile Using Robust Backstepping Control

Abstract: This paper deals with the design of a robust nonlinear controller for a highly maneuverable missile. Stabilization and tracking are achieved, exploiting a detailed nonlinear model of the six-degree-of-freedom, nonminimum phase, uncertain, and time-varying dynamics of a non-axial-symmetric air-to-air tail-controlled missile. A robust backstepping approach is applied to the multi-input/multi-output model to achieve both bank-to-turn and skid-to-turn maneuvers. Control objectives consist of following the reference signals in angle of attack, sideslip, and bank angle produced by the external guidance system, in order to pursue highly agile maneuvers. Uncertain terms, mostly due to aerodynamic coefficients and dynamic pressure, are suitably limited by bounding functions constructed using experience, a priori knowledge on system behavior, and a bit of conservatism. Robust sigmoidlike control functions are then used to dominate in size the uncertain terms. The whole control system is shown to be practically-robu...