توجه: محتویات این صفحه به صورت خودکار پردازش شده و مقاله‌های نویسندگانی با تشابه اسمی، همگی در بخش یکسان نمایش داده می‌شوند.
۱LQR MATRIX TUNING WITH ICA OPTIMIZATION ALGORITHM FOR MICRO AERIAL VEHICLE (SAMARAI MONO–COPTER)
نویسنده(ها): ، ،
اطلاعات انتشار: کنفرانس ملی مهندسی مکانیک ایران، سال
تعداد صفحات: ۱۰
In this paper, a newmicro unmanned aerial system is an emerging class of vehicles uniquely suited to performing covert missions. A linear model for the dynamics of a robotic samara (winged seed) in hovering flight is investigated. An efficient strategy based on LQR controller and ICA optimization is proposed to design the altitude hold mode autopilot. A novel cost function that comprises undershoot, overshoot, rise time, settling time, steady state error and stability are considered to estimate LQR gains optimality. Simulation results show that the proposed strategy performances are desirable in terms of the time response and error.<\div>

۲NOVEL NONLINEAR CLOSED–LOOP OPTIMAL CONTROL ALGORITHM WITH ICA OPTIMIZATION ALGORITHM FOR SPACE MISSINS
نویسنده(ها): ، ،
اطلاعات انتشار: کنفرانس ملی مهندسی مکانیک ایران، سال
تعداد صفحات: ۱۰
The present research is intended to present an algorithm for solving the nonlinear closed–loop optimal control problem with regard to space trajectory design viewpoint. To do so, issues such as optimal control theory, three–dimensional Fourier series and evolutionary optimization as Imperialist competitive algorithm (ICA) are utilized. Attempts have been made to introduce a new and comprehensive algorithm to cover free–time problems in the optimal control theory for space manoeuvres. The algorithm presented was solved and validated for the Edelbaum orbital transfer problem as a case study in which nonlinear dynamic equations were included. Results regarding to the three–dimensional Fourier series and the optimization method as ICA are achieved. This novel method provides an accurate and precise solution for this particular closed–loop orbital optimal control problem, which satisfies the objective of this work. Finally, this novel and new method is introduced for space mission designers as efficient method to achieve closed–loop guidance.<\div>
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