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Adaptive Control Essay

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The aim of the paper is to control the path for nonlinear missile model in the pitch channel using Model Reference Adaptive Control (MRAC) and L1 Adaptive Control with Linear Quadratic Regulator Time Varying (LQRTV) strategy. Linear Time Varying (LTV) model that represents the closed approximation of nonlinear flying body is designed where the parameters of LTV model are varying with time. The equations of motion for nonlinear flying body and two structures of adaptive control (MRAC and L1 adaptive control) with LQRTV are modeled mathematically in Matlab-Simulink environment. LQRTV optimal control is designed using LTV model by online calculation of Riccati Equation to get time varying state feedback gain K(t). Adaptive control structures …show more content…

The designing for adaptive control with LQRTV strategy using a six degree of freedom (6-DOF) missile model in pitch channel will be addressed in this paper. The 6-DOF missile model is the solution to get true information for the missile path. The paper aims are (1) evolve a complicated mathematical model of flying path simulation for a missile in pitch channel, which is utilized as an algorithm sharing for designing, analyses, and growth the framework to perform the missile by Simulink to ease the designing for control structure (2) According to the system features and application environment required, the structures of adaptive control (MRAC and L1 adaptive control) with a linear quadratic regulator time varying (LQRTV) strategy is proposed to solve the missile attitude control problem, [1-3]. LQRTV optimal control is designed using linear time varying (LTV) model by online calculation of Riccati Equation to get time varying state feedback gain K(t). Adaptive control structures are designed using closed loop LTV model by online calculation of Lyapunov Equation to get time varying Lyapunov gain matrix P(t). Adaptive control structures with LQRTV controller is capable of recover the chains that represent natural boundaries of pitch angle actuators. The wind and different dynamic uncertainty percentages for 6-DOF missile aerodynamic coefficients are represented and their effects are studied. According to MacKenzie, guidance is defined as the

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