IJE TRANSACTIONS A: Basics Vol. 28, No. 10 (October 2015) 1507-1514   

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A. M. Khoshnood and O. Kavianipour
( Received: March 26, 2014 – Accepted: September 03, 2015 )

Abstract    One of the main vibration problems of aerospace vehicles with liquid fuel propulsion system is fuel sloshing. This phenomenon is a low frequency vibrational challenge which can affect the motion of the vehicle and degrade the stability of the main control system. In this regards, the motion of the liquid will be very critical when the frequency of the sloshing is very close to the frequencies of the main dynamic system. In addition, dominant frequencies of the sloshing are varied due to the flight time in the aerospace vehicles. In this paper, an aerospace launch vehicle with fuel sloshing is considered as a multi body dynamic system and in order to reduce the undesired effects of the fuel vibration, a new subband adaptive filter based on the lyapunov theorem and the discrete fourier transform (DFT) is designed. In this way, the new control system is implemented on the attitude control of the vehicle and the simulation of the nonlinear model is carried out. Numerical results of the simulation show that the effects of the fuel sloshing on the vehicle are effectively omitted by means of the new subband adaptive controller.


Keywords    Fuel Sloshing; Vibration Control; Nonlinear Dynamics; Lyapunov Theorem; Subband Adaptive Filter.


چکیده    یکی از مسایل اصلی در ارتعاشات سیستم­های هوافضایی با سیستم پیشران مایع، تلاطم سیال مایع می­باشد. این پدیده یک چالش ارتعاشی فرکانس پایین است که می­تواند روی حرکت سیستم تاثیر گذاشته و پایداری سیستم اصلی کنترل را کاهش دهد. دراین خصوص، حرکت مایع زمانی خیلی بحرانی می­شود که فرکانس ارتعاشات تلاطم به فرکانس کاری سیستم اصلی بسیار نزدیک باشد. علاوه بر این، محدوده فرکانس­های تلاطم در یک سیستم هوافضایی با تغییر زمان تغییر می­کنند. در این مقاله، یک سیستم هوافضایی با سوخت مایع با دیدگاه چند جسمی مورد بررسی قرار گرفته و برای کاهش تاثیرات نامطلوب ارتعاش سوخت، یک فیلتر زیرباند تطبیقی جدید بر اساس تئوری لیاپانوف و تبدیل فوریه زمان گسسته طراحی شده است. در این زمینه، سیستم کنترل جدید روی کنترل وضعیت موجود سیستم هوافضایی پیاده سازی شده و شبیه سازی عددی استخراج شده است. نتایج عددی شبیه سازی نشان می­دهند که تاثیرات تلاطم سوخت بر روی سیستم با استفاده از سیستم کنترل تطبیقی زیرباند به طور موثری کاهش یافته است.



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