Journal of the Korean Society for Aeronautical & Space Sciences (한국항공우주학회지)

The Korean Society for Aeronautical and Space Sciences (한국항공우주학회)
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Helicopter Active Airframe Vibration Control Simulations Using an Exhaustive Test Method

Exhaustive 시험 기법을 이용한 헬리콥터 능동 기체 진동 제어 시뮬레이션

  • Park, Byeong-Hyeon (Department of Aerospace Engineering, Chungnam National University) ;
  • Lee, Ye-Lin (Spacecraft Structure Team, Satrec Initiative) ;
  • Park, Jae-Sang (Department of Aerospace Engineering, Chungnam National University)
  • Received : 2022.06.18
  • Accepted : 2022.09.07
  • Published : 2022.11.01
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Abstract

The number and locations of force generators and their force directions of Active Vibration Control System(AVCS) are important to maximize the airframe vibration reduction performance of helicopters. The present AVCS simulation using an exhaustive test method attempts to determine the best number and locations of force generators and their force directions for maximization of the airframe vibration reduction performance of UH-60A helicopter at 158 knots. The 4P hub vibratory loads of the UH-60A helicopter are calculated using DYMORE II, a nonlinear multibody dynamics analysis code, and MSC.NASTRAN is used to predict the vibration responses of the UH-60A airframe. The AVCS framework with an exhaustive test method is constructed using MATLAB Simulink. As a result, when applying AVCS with the optimal combination of the force generators, the 4P airframe vibration responses of UH-60A helicopter are reduced by from 19.35% to 98.07% compared to the baseline results without AVCS.

능동 진동 제어 시스템(Active vibration control system, AVCS)을 이용하여 헬리콥터 기체의 능동 진동 제어 시 우수한 진동 제어 성능을 얻기 위하여서는 진동 상쇄 하중 발생기의 개수, 위치 및 하중 방향의 조합의 최적화가 중요하다. 따라서 고려 가능한 모든 하중 발생기의 조합에 대하여 헬리콥터 기체에 대한 AVCS의 진동 제어 성능을 조사하기 위해 Exhaustive 시험 기법을 적용한 AVCS 프레임워크를 구축하였다. 로터 진동 하중 해석, 기체 진동 응답 해석 및 AVCS 시뮬레이션 연구를 수행하기 위해 DYMORE II, MSC.NASTRAN 및 MATLAB Simulink 등 다양한 프로그램을 사용하였다. 이를 이용하여 비행 속도 158 knots의 UH-60A 헬리콥터에 대한 AVCS 적용을 위한 CRFG 조합을 최적화하였다. 최적의 CRFG 조합이 적용된 AVCS를 통해 UH-60A 헬리콥터의 4P 기체 진동 응답을 능동 제어한 결과, 기체의 주요 위치에서 4P 기체 진동 응답이 19.35~98.07%만큼 감소될 수 있었다.

Keywords

Acknowledgement

본 연구는 2020년도 정부(교육부)의 재원으로 한국연구재단의 기초연구사업의 지원을 받아 수행되었습니다(2020R1I1A3071793). 본 논문은 2021년도 정부(과학기술정보통신부)의 재원으로 한국연구재단의 지원을 받아 수행된 연구입니다(2021R1A5A1031868). 이 연구는 국방기술진흥연구소 핵심기술 연구개발과제 "중형헬기 진동저감을 위한 진동원(블레이드) 능동제어장치 SW 개발"(과제번호: 20-108-E00-018)의 지원으로 수행되었습니다.

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