توجه: محتویات این صفحه به صورت خودکار پردازش شده و مقاله‌های نویسندگانی با تشابه اسمی، همگی در بخش یکسان نمایش داده می‌شوند.
۱The Design of the Aircraft Longitudinal Axis Autopilot using Finite–Time Proportional–Integral Sliding Mode controller under parametric uncertainty
نویسنده(ها): ، ،
اطلاعات انتشار: اولین کنفرانس بین المللی دستاوردهای نوین پژوهشی در مهندسی برق و کامپیوتر، سال
تعداد صفحات: ۵
In this paper, design of the aircraft longitudinal axis autopilot using finite–time PI sliding mode controller under parametric uncertainty. It has two inputs and two outputs for the system design and the order of two and a 50% random uncertainty affecting the aerodynamic coefficients of a nonlinear controller is designed to be resistant. The design of the controller to follow the desired path and the aircraft is capable of error close to zero and stability in the presence of uncertainty. To ensure system stability is used by the Case Study Lyapunov. In this study due to high non–linearity of the system input and uncertainties. PI sliding mode controller compared with the Finite–time PI sliding mode that in addition to withstand uncertainty, has other advantages such as insensitivity to external disturbances, fast transient response and simplicity of design and implementation. The results PI sliding mode control with Finite–time PI sliding mode comparing and show improving results in the Finite–Time PI sliding mode.<\div>
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