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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TL;DR: The effectiveness and robustness of the proposed integrated guidance and control algorithm are verified through numerical simulations and the finite-time stability of the closed-loop system is proven based on Lyapunov theory.
Abstract: In this paper, considering a class of skid-to-turn (STT) missile with impact angle constraint to intercept the maneuvering target, a three-dimensional integrated guidance and control law based on the fractional integral terminal sliding mode control (FITSMC) scheme is proposed. Firstly, a three-dimensional integrated guidance and control model is established for missile-target relative motion and nonlinear missile dynamics with multiple system uncertainties and unknown disturbances. Secondly, in order to achieve the desired impact angle in finite-time without singularity, a novel nonsingular FITSMC scheme is employed to construct the sliding surface, and a modified filter is applied to dynamic surface control design. Also, an extended state observer is introduced to estimate and compensate the system uncertainties and unknown disturbances. Then, a robust integrated guidance and control scheme with impact angle constraint is developed using aforementioned techniques. Furthermore, the finite-time stability of the closed-loop system is proven based on Lyapunov theory. Finally, the effectiveness and robustness of the proposed integrated guidance and control algorithm are verified through numerical simulations.
21 citations
Patent•
22 Feb 1977
TL;DR: In this article, the ejection of a head by the detonation of a charge exerts a backward reaction force upon the envelope, causing its load to move forward therein whereby the partitions are disengaged from the two half-shells and allow them to flip apart.
Abstract: A subcaliber missile to be launched from a barrel, in order to serve as a carrier for satellite missiles of other ejectable bodies, has an envelope divided into two half-shells of tapering configuration which are articulated to the missile bottom and are held together by a missile head and by internal partitions separating the ejectable bodies from one another. When the missile is in flight, the ejection of the head by the detonation of a charge exerts a backward reaction force upon the envelope, causing its load to move forward therein whereby the partitions are disengaged from the two half-shells and allow them to flip apart. The half-shells are provided with slots for a recessed tail-wing assembly and with back fins which, like the missile bottom, conform to the caliber of the barrel.
21 citations
Patent•
23 May 1996
TL;DR: In this paper, a nonlinear sorting and filtering procedure was used to reject the unusable error sources among the six potential error sources, and thresholds against too little information were established.
Abstract: Missile motion information from an inertial measurement set and the angle-to-target information from a seeker/sensor is used to estimate range and/or time to go on a homing missile without a direct measurement of range or range rate. Up to six comparisons of spectrally matched linear and angular measurements, corrected by target state estimates and analytical coupling terms, are used to determine the error in the range estimate. A nonlinear sorting and filtering procedure rejects the unusable error sources among the six potential error sources, and thresholds against too little information. The stability margin in the missile guidance loop is used as a sensor indicator for excessive estimated range.
21 citations
Patent•
10 Jun 2004TL;DR: In this article, a system and method for an aircraft that provides an IR decoy (12) for an incoming missile to track instead of an engine ( 14 ) of the aircraft (10 ) is disclosed.
Abstract: A system and method for an aircraft ( 10 ) that provides an IR decoy ( 12 ) for an incoming missile ( 18 ) to track instead of an engine ( 14 ) of the aircraft ( 10 ) is disclosed. The IR decoy ( 12 ) is deployed during or just after take off, and prior to landing to provide a signature ( 16 ) for any incoming missile ( 18 ). The IR decoy ( 12 ) provides a heat source ( 16 ) that has a higher radiant intensity than the hottest heat source on the aircraft ( 10 ), which is typically the engine ( 14 ), thereby providing a more attractive heat source for the missile ( 18 ). In another embodiment, a warning system ( 20 ) for an aircraft ( 10 ) detects an incoming missile ( 18 ), and deploys IR decoy ( 12 ) and creates an engine mask ( 22 ) by injecting an additive into the exhaust stream of the engine ( 14 ), thereby obscuring the radiation emanating from the engine ( 14 ).
21 citations
TL;DR: The idea of prescribed performance function is incorporated into the control design, such that both the steady-state and transient control performance can be strictly guaranteed, and a recently proposed systematic control design procedure is tailored using the transformed tracking error dynamics, which provides a proportional-like control action.
Abstract: This paper presents a robust prescribed performance control approach and its application to nonlinear tail-controlled missile systems with unknown dynamics and uncertainties. The idea of prescribed...
21 citations