• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2013년도 추계학술대회 논문집
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• pp.214-215
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• 2013

The tapping test has simplicity of procedure for detection of the damage in aircraft structure. However, the result of tapping test depends on the subjective experience of inspector. In this paper, more objective tapping test has proposed. The impact force histories and tapping sounds are used as reference data to evaluate the delamination. The WT(wavelet transform) is used to decompose the test data. From the results, we could know that high frequency components of force and sound are reduced due to delamination in composite laminate. On these results, the tapping force and sound caused by tapping could be used for the reference data to evaluate the delamination in composite structure.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2001년도 추계학술대회논문집 II
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• pp.1197-1201
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• 2001

Flutter suppression of a wing/store model is investigated. An aircraft wing with a store is modeled as a 2-D typical section. Unsteady aerodynamics of the wing/store model are computed by using Doublet Hybrid Method(DHM) in the frequency-domain, and are approximated by Minimum-state(MS) approximation. LQG controller is used to suppress the flutter of the wing/store model and the aeroelastic characteristics of the closed-loop system are investigated. The flutter characteristics of the wing/store model are improved and the flutter speed is increased up to about 16 ％.

• 한국소음진동공학회논문집
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• 제12권7호
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• pp.493-501
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• 2002

Flutter suppression of a wing/store model is investigated. An aircraft wing with a store is modeled as a 2-D typical section. Unsteady aerodynamics of the wing/store model are computed by using doublet hybrid method(DHM) in the freauency-domain, and are approximated by minimumstate(MS) approximation. LQG controller is used to suppress the flutter of the wing/store model and the aeroelastic characteristics of the closed-loop system are investigated. The flutter characteristics of the wing/store model are improved and the flutter speed is increased up to about 24 %.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2005년도 추계학술대회논문집
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• pp.349-354
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• 2005

There are various types of noise around us such as road traffic noise, aircraft noise and floor impact sound, equipment noise etc. Recently researches on the criteria to evaluate the noises have been progressed, however, researches on the noise criteria and evaluation method for the diffuser noise of HVAC are insufficient. dB(A) and NC values represented in ASHRAE guide book are applied as a noise criteria for diffuser noise, which have some problems like that the values between dB(A) and NC have deviation even if the sound is same one. Therefore, the evaluation method should be considered and proposed based on the subjective responses. From these reasons, this study aimed to analyze the evaluation factors for the diffuser noise of HVAC reflected on the subjective responses by surveying vocabularies and grouping them with factor analysis.

• Advances in aircraft and spacecraft science
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• 제6권4호
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• pp.273-282
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• 2019

This article is concerned with the investigation of geometrically non-linear vibration response of refined thick porous nanobeams. To this end, non-local theory of elasticity has been adopted to provide the nanobeam formulation. Voids or pores can affect the material characteristics of the nanobeam. So, their effects have been considered in this research and also there are various void distributions. The closed form solution of the non-linear problem has been used that is adopted from previous articles. Then, it is focused on the impacts of non-local field, void distribution, void amount and geometrical properties on non-linear vibrational characteristic of a nano-size beam.

• Advances in aircraft and spacecraft science
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• 제11권2호
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• pp.105-128
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• 2024

Vibrations in aerodynamic systems can lead to significant structural and performance issues. This paper presents a novel theorem for actively controlling aerodynamic vibrations through parametric stability analysis. The proposed approach models the aerodynamic system as a dynamic system with parametric excitation, allowing for the identification of stable and unstable regions in the parameter space. By strategically adjusting the system parameters, the vibrations can be effectively suppressed, enhancing the overall reliability and performance of the aerodynamic system. The theoretical underpinnings of the theorem are discussed, and the effectiveness of the approach is demonstrated through numerical simulations and experimental validation. The results show the potential of this method for practical implementation in various aerodynamic applications, such as aerospace engineering and wind turbine design.

• International Journal of Aeronautical and Space Sciences
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• 제1권1호
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• pp.48-61
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• 2000

Korea Aerospace Research Institute (KARI) have gained experience with Helicopter Vibration Health Monitoring (VHM) System technology with the help of UK GKN-WHL. GKN-WHL have had many years of experience with the research and development of vibration analysis techniques to improve the health monitoring of helicopter transmissions. This activity was targeted at transmission rig testing at first, but the techniques have been progressively developed where they are now used as a part of integrated Health and Usage Monitoring (HUM) systems on many types of in-service and new helicopters. The technique development process has been considerably aided by an ever expanding database of transmission monitoring experience from both the rig testing and aircraft operations. This experience covers a wide range of failure types from naturally occurring faults to crack propagation studies and covering a wide range of transmission configurations. Primarily based on accelerometer signals GKN-WHL's vibration analysis methods have also been applied to a variety of other sensor types. The transition from an experimental environment to operational VHM systems has been a lengthy process, there being a need to demonstrate technique reliability as well as effectiveness to both regulatory (Airworthiness Authority) and commercial organizations. Another important feature of this process has been the development of close relationships with a number of VHM system hardware and software suppliers. Such an experienced GKN-WHL provides various raw vibration data which was acquired from transmission ground test rig and allow KARI to develop it's own analysis program. KARI made a program and then analyzed the data to coma pre with the results of GKN-WHL. The KARI's results both time domain signals and statistical values show comparable to GKN's.

• Structural Monitoring and Maintenance
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• 제5권2호
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• pp.297-311
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• 2018

Plate and shell structure is widely applied in engineering, i.e. building roofs, aircraft wings, ship platforms, and satellite solar arrays. Its vibration problem has become increasingly prominent due to the tendency of lightening, upsizing and flexibility. As a new smart material with great actuating force and toughness, macro-fiber composite (MFC) is composed of piezoelectric fiber and epoxy resin basal body, which can be directly pasted onto the surface of plate and shell and is suitable for vibration control. This paper deduces the actuation equation of MFC coupled plate in different boundary conditions, an equivalent finite element modeling method is proposed which uses MFC actuating force as the applied excitation, and on this basis the active control simulation and experiment of MFC over plate and shell structure vibration are accomplished. The results indicate that MFC is able to implement effective control over plate and shell structure vibration in multi-band range. The comparison between experiment and simulation proves that the actuation equation deduced herein, effective and practicable, can be applied into the simulation calculation of MFC vibration control over plate and shell structure.

• 한국전산구조공학회논문집
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• 제23권1호
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• pp.9-15
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• 2010

본 논문에서는 압전복합재 작동기가 표면에 부착된 Hull 구조물의 유한요소모델을 구성하여 동적 특성을 고찰하였으며, 구조물의 진동제어 특성을 평가하였다. Hull 구조물은 양 끝이 닫혀있는 실린더형 쉘 구조물을 고려하였으며, 항공기 동체나 잠수함과 같은 수중 구조물 등의 간단한 모델로 사용될 수 있다. 구조물의 진동제어를 위해 최근 NASA Langley 연구소에서 개발된 압전복합재인 Macro-Fiber Composite(MFC)를 적용하였다. MFC는 압전세라믹 섬유를 이용하여 유연성을 향상시키고, 맞물림 전극을 적용하여 면내 방향에서 큰 압전효과를 구현할 수 있도록 하였다. 유한요소모델을 바탕으로 구조물의 지배방정식을 도출하였으며, 동적 특성을 해석하여 실제 제작된 구조물의 실험결과와 비교 검증하였다. 최적제어 알고리즘을 구성하여 구조물의 진동제어 성능을 평가하였으며, 효과적으로 구조물의 진동을 제어할 수 있음을 확인하였다.

• 항공우주시스템공학회지
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• 제12권4호
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• pp.18-25
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• 2018

가공의 정밀도와 난삭재 가공이 요구되는 항공기부품용 공작기계의 헤드프레임 구조는 정밀 고속가공을 위해 경량화 및 절삭력에 의한 변형최소화가 필요하다. 본 논문에서는 고강성 경량화 구조 최적설계를 위해 유한요소해석을 수행하여 초기형상을 설계하였고, 컴플라이언스를 최소화하여 경량, 고강성 및 저진동 구조의 위상 최적화 설계를 수행하였다. 최적화 설계결과 프레임 중량은 17.3% 감소되었고, 최대 처짐량은 0.007 mm 이하, 고유진동수는 30.6% 증가되었다. 구조 정강성은 각 축 방향으로 증가되었고, 동강성은 축에 따라 상반된 결과를 나타내었다. 위상 최적화 설계 구조에서 저진동의 고강성을 갖는 최적화된 구조를 확인하였다.