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The Design of Controler and Guidance of Short-Range Air-To-Ground Missile

Author: ZuoHongJun
Tutor: HuangXianLin
School: Harbin Institute of Technology
Course: Control Science and Engineering
Keywords: Ground missiles Gain scheduling LPV Over gravity compensation
CLC: TJ765
Type: Master's thesis
Year: 2009
Downloads: 205
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Abstract


In the short-range ground missile during flight, attitude stabilization system to overcome missile brings gesture jitter of the missile body posture quickly stabilize to the desired attitude angle, and to ensure stable operation of the engine and the high-thrust segment seeker is locked target state ; autopilot requires guided missile body posture segment to ensure stable and accurate, fast track guidance control system provides guidance commands; guidance control system requires real-time measurement of missiles and target information, according to the measured information combined with the corresponding guidance law for auto autopilot to provide guidance commands. Missile in flight is a nonlinear time-varying system stronger, gain scheduling method can overcome a fixed controller is used to change the operating point in a wide range of nonlinear systems performance brought conservative, and easy to implement in engineering, for many years come in practice has been widely used. This article will break down the attitude control missile motion, autopilot and guidance and control systems of three parts. First, the use of classical gain scheduling methods are designed to pitch, yaw and roll attitude stabilization system with three channels and autopilot. The nonlinear model of the missile in the corresponding operating point of the linear feature into a linear model, linear systems using frequency domain controller design methods, and then by fitting way to get gain scheduling controller. Secondly, the guided missile segment parameters rapidly changing, resulting in classical gain scheduling method does not guarantee overall system performance issues, using LPV gain scheduling method is designed autopilot. The missile is still divided into pitch, yaw and roll channels were designed, the missile through nonlinear equations corresponding linearized into a standard LPV system, and then based on H_ ∞ theory, application LMI algorithm design LPV output feedback controller. Then, in the missile guidance and control system of proportional guidance law for hitting the target requires a greater angle over the case, the use of over-the ratio of gravity compensation guidance law. In this paper, the missile and the target relative motion equation and pushed out the selected scale factor and over gravity compensation coefficient based on the formulas. Finally, in the application of nonlinear systems, respectively, the classical method and the LPV gain scheduling autopilot designed for simulation, simulation results show that the design method can guarantee the system's performance. And using different scale factors and different systems over the gravity compensation coefficients were simulation, comparative analysis, summed up the scale factor and over-gravity compensation coefficient on missile-related performance, gives the ideal range.

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CLC: > Industrial Technology > Arms industry > Rockets, missiles > Missile > Guidance and Control
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