• Title/Summary/Keyword: Helicopter Noise

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Structural Vibration Analysis of Helicopter Search Light Considering Aerodynamic Buffet Load (공력 Buffet 하증을 고려한 헬리콥터 탐색등의 구조진동해석)

  • Kim, Yo-Han;Kim, Dong-Man;Kim, Dong-Hyun;Choi, Hui-Ju;Park, Yong-Suk;Kim, jong-Gun
    • Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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    • 2008.11a
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    • pp.175-179
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    • 2008

  • In this study, computational structural vibration analysis of helicopter search light exposing unsteady buffet load have been conducted using combined advanced numerical methods. Unsteady CFD method based on Navier-Stokes equations is used to predict viscous buffet load due to flow separation effects. Full three-dimensional finite element model is constructed in order to conduct static and structural dynamic analyses of the search light model for two different typical flight speeds. Also, the correct performance of the search light can be physically estimated to examine the actual lighting area considering the effects of structural deformations.

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Hub Parametric Investigation of Main Rotor Stability of Bearingless Helicopter (무베어링 헬리콥터 주 로터의 허브 파라미터 변화에 따른 로터 안정성 특성 해석)

  • Yun, Chul-Yong;Kee, Young-Jung;Kim, Tae-Joo;Kim, Deog-Kwan;Kim, Seung-Ho
    • Transactions of the Korean Society for Noise and Vibration Engineering
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    • v.22 no.8
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    • pp.784-790
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    • 2012

  • This paper describes a stability and dynamic characteristics of bearingless helicopter main rotor in hover. Baseline rotor configuration is defined and modal analysis for the configuration is taken to verify the dynamic characteristics. The kinematic pitch-lag couplings through ways of pitch link installation are analyzed to know effects on loads, frequencies and stability. The effects of pitch link attachments in spanwise direction and chordwise direction as well as pitch link inclination on thrust, power, flpa-lag-pitch mode frequencies and inplane damping are examined. Pitch link at trailing edge location in chordwise direction has influence on aeroelastic stability of the rotor. Also, the pitch link with negative inclination angle makes inplane damping increase.

  • https://doi.org/10.5050/KSNVE.2012.22.8.784 인용 PDF KSCI