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http://dx.doi.org/10.5139/JKSAS.2022.50.3.181

Development and Verification of Active Vibration Control System for Helicopter  

Kim, Nam-Jo (Korea Aerospace Industries, LTD.)
Kwak, Dong-Il (Korea Aerospace Industries, LTD.)
Kang, Woo-Ram (Korea Aerospace Industries, LTD.)
Hwang, Yoo-Sang (Korea Aerospace Industries, LTD.)
Kim, Do-Hyung (Korea Aerospace Research Institute)
Kim, Chan-Dong (Korea Aerospace Industries, LTD.)
Lee, Ki-Jin (Korea Aerospace Industries, LTD.)
So, Hee-Soup (Kwangwoon University)
Publication Information
Journal of the Korean Society for Aeronautical & Space Sciences / v.50, no.3, 2022 , pp. 181-192 More about this Journal
Abstract
Active vibration control system(AVCS) for helicopter enables to control the vibration generated from the main rotor and has the superb vibration reduction performance with low weight compared passive vibration reduction device. In this paper, FxLMS algorithm-based vibration control software of the light civil helicopter tansmits the control command calculated using the signals of the tachometer and accelerometers to the circular force generator(CFG) is developed and verified. According to the RTCA DO-178C/DO-331, the vibration control software is developed through the model based design technique, and real-time operation performance is evaluated in PILS(processor in-the loop simulation) and HILS(hardware in-the loop simulation) environments. In particular, the reliability of the software is improved through the LDRA-based verification coverage in the PIL environments. In order to AVCS to light civil helicopter(LCH), the dynamic response characteristic model is obtained through the ground/flight tests. AVCS configuration which exhibits the optimal performance is determined using system optimization analysis and flight test and obtain STC certification.
Keywords
Active Vibration Control System; Model-Based Design; Hardware In-the Loop Simulation; Flight Test;
Citations & Related Records
Times Cited By KSCI : 3  (Citation Analysis)
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