مقالههای M.R Elhami
توجه: محتویات این صفحه به صورت خودکار پردازش شده و مقالههای نویسندگانی با تشابه اسمی، همگی در بخش یکسان نمایش داده میشوند.
اطلاعات انتشار: بیستمین کنفرانس سالانه مهندسی مکانیک، سال ۱۳۹۱
تعداد صفحات: ۴
This paper presents a Sliding Mode Control (SMC) system for the stabilization of an Aero–Servo–Elastic (ASE) system with structural nonlinearities at subsonic flight speed. For this research, a 2 DOF aero–elastic model of a wing section developed. For the aim of control, a single control surface associated with SMC technique is used. This control system suppresses flutter as well as the vibration level in sub–critical and postflutter speeds. For state–space representation of the model, the measured pitch angle, plunge displacement and their derivatives are allocated as state vector, andcontrol surface deflection as input command. For a given initial state conditions, two modes of open loop and closed loop control system are carried out. It is shown that the open loop system with a nonlinear structure in subsonic regimes is unstable with Limit Cycle Oscillations (LCOs). However, the closed loop system is asymptotically stable and converges to the origin. Therefore, the proposed approach has a good performance for suppressing flutter and LCOs, as well as short time response compared to other nonlinear methods such as State Dependence Riccati Equation or so–called SDRE method.<\div>
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