Abstract
According to motion characteristic of an asymmetric rolling missile with damage fin, a three-channel controlled model is established. The controller which is used to realize non-linear tracking and decoupling control of the roll and angle motion is introduced based on an improved trajectory linearization control method. The improved method is composed of the classic trajectory linearization control method and a compensation control law. The classic trajectory linearization control method is implemented in the time-scale separation principle. The Lipschitz non-linear state observer systematically obtained by solving the linear matrix inequality approach is provided to estimate state variables and unknown parameters, and then the compensation control law utilizing the estimated unknown parameters improves the TLC method. Simulation experiments show that the adaptive decoupling control ensure tracking performance, and the robustness and accuracy of missile attitude control are ensured under the condition of the system parameters uncertainty, random observation noise and external disturbance caused by damage fin.
Highlights
The structure or the aerodynamic asymmetric phenomenon is common for many rolling missiles.Such unintended asymmetric phenomenon is often caused by two reasons: machining or assembling misalignment and body or fin structural damage by large external forces during the launch or the flight.Because of uncertainty and random asymmetric factors, the asymmetric rolling missile system is a complex non-linear system with uncertainty parameters
Asymmetric aerodynamic characteristics were the first to be of concern, and wing bending and impact damage were studied by the use of wind tunnel experiments (Render et al 2007; Djellal and Ouibrahim 2008; Render et al 2009)
This paper aims at designing a good performance control system for asymmetric rolling missiles and developing an improved method for trajectory linearization control (TLC) algorithm
Summary
The structure or the aerodynamic asymmetric phenomenon is common for many rolling missiles. This paper aims at designing a good performance control system for asymmetric rolling missiles and developing an improved method for TLC algorithm. SLOW LOOP CONTROLLER DESIGN According to TLC method, linear time-varying proportionalintegral (PI) regulator is usually designed to track the augmented vector error. FAST LOOP CONTROLLER DESIGN Following the same method to define fast loop dynamics augmented vector error, the estimations of state variables and unknown parameters. The expected tracking states “command” in yaw, pitch and roll channels are βc, αc and pc, respectively Two different methods “TLC” and improved TLC which is named “TLC + adaptive compensation” are separately applied to control the missile attitudes to track the “command”. It means that TLC combined with Lipschitz adaptive compensation control law improves the β [rad]
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