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Intelligent Control,Guidance And Scene Simulation Of Intercept Missile Based On Side Jet/Aerodynamics Compound

Posted on:2008-08-16Degree:MasterType:Thesis
Country:ChinaCandidate:Q G LiFull Text:PDF
GTID:2132360215997201Subject:Control theory and control engineering
Abstract/Summary:PDF Full Text Request
This paper mainly works on the problems of modeling, control and guidance for an intercept missile based on side jet and aerodynamics compound control.In part one, the model of intercept missile with 6-DOF based on side jet and aerodynamics compound control is studied. This paper builds the mathematic model of aerodynamic force, moment, engine and rudders references to the datum of some missiles in domestic and foreign, and builds nonlinear mathematic model of the missile with append factor which conforms to the actual situation,based on analyzing the phenomenon of side jet interaction with external flow. Besides, the fire logic of attitude engines is designed.In part two, the control problem based on layered structure is researched. The control system of missile is divided into slow-loop and fast-loop by exploiting the different time scales of the missile dynamics. Because the dynamic inverse control needs the exact model, the nonlinear disturbance observer is used to overcome the influence of the internal modeling error and the external disturbance of the system. Furthermore compared to the pure aerodynamics control, compound control demonstrates more effective. Besides, for enhancing the robustness and fastness of the system, a proposed controller combining with fast terminal sliding-mode and adaptive fuzzy control is designed.In part three, the terminal guidance law of the intercept missile is investigated. Firstly, a kinematics model for 3D guidance problems is derived. And then the guidance law based on fuzzy adaptive fast terminal sliding mode is presented regarding target's acceleration as the extern disturbance. In virtue of the limited of the aim weaving in the actual systems, a novel fast adaptive terminal sliding mode guidance law is presented on condition that the estimation of the aim weaving is bound. The simulations show the effectiveness and robustness of the guidance law.In part four, based on Creaor/Vega and Visual C++, the 3D-visualization intercept missile platform is developed, which can show the process of missile pursuing target vividly.
Keywords/Search Tags:intercept missile, side jet, dynamic inverse, global fast terminal sliding mode control, nonlinear disturbance observer, adaptive fuzzy control, nonlinear sliding mode guidance law, scene simulation
PDF Full Text Request
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