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Study On Guidance Control Of Air To Air Missile And Chattering Suppression

Posted on:2011-10-29Degree:MasterType:Thesis
Country:ChinaCandidate:Y WangFull Text:PDF
GTID:2232330395458522Subject:Navigation, guidance and control
Abstract/Summary:PDF Full Text Request
With the rapid development of the guidance and control of missile technology, the attitude control of air to air missile becomes more and more important, and there are more and higher requirements of stability and pointing accuracy problem of air to air missile. The guidance and control system of missile plays an important role in missile system. So the design of guidance and control system is a meaningful work. The paper deals with the guidance and control system of air to air missile in the sliding mode variable structure, and improves the traditional methods of the chattering phenomenon.Main research is listed as follows:Summarize the development and research of the guidance and control theory of air to air missile, and introduce some control methods of air to air missile.The necessary coordination systems are defined and the transformation relations among them are given. The force and moment are analyzed, kinematics, kinetics, quality and maneuvering relation equations are given. So, the mathematical model of missile is completely set up.According to the characteristic of the air to air missile, for the accuracy and engineering application, robustness of the sliding-mode variable structure theory is insensitivity to uncertainty, the adaptive sliding-mode guidance law is designed. The simulation results show that high precision can be obtained with the two guidance laws and can achieve performance satisfactorily.Based on the established missile mathematical model, it could be simplified in some circumstances. The control model of air to air missile is proposed. Designs variable structure controller with integral term using variable structure control theory. The simulation result indicates that the variable structure controller has excellent robustness to system uncertainties and external disturbance and has good dynamic property which meets the design requirements.The chattering Phenomenon of VSC is studied in this dissertation. The causes of the chattering phenomenon are systematically analysis, and the study status of the chattering phenomenon and the main methods to eliminate the chattering are elaborated. For the deficiencies of traditional methods, a improved method is developed, which is improved exponent reaching law solution.At last, summarize the works of this paper, and point out the direction for further research.
Keywords/Search Tags:Air to Air Missile, Guidance Law, Guidance and Control System, Sliding ModeVariable Structure Control, Chattering Suppression
PDF Full Text Request
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