• Advances in aircraft and spacecraft science
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• 제2권4호
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• pp.403-425
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• 2015

This work is focused on the definition and the analysis of both complete and incomplete similitudes for the dynamic responses of thin shells. Previous numerical and experimental investigations on both structural and structural-acoustic systems motivated this further analysis, mainly centred on the incomplete (distorted) similitudes. These similitudes and the associated scaling laws are defined by using the classical modal approach (CMA) and by invoking also the Energy Distribution Approach (EDA) in order to take into account both the cinematic and energetic items. The whole procedure is named SAMSARA: Similitude and Asymptotic Models for Structural-Acoustic Research and Applications. A brief summary of the procedure is herein given and the attention is paid to the analytical models of thin stiffened and unstiffened cylindrical shells. By using the well-known smeared model, the stiffened cylinder equations are used as general framework to analyse the possibility to define exact (replicas) or distorted similitudes (avatars). Despite the extreme simplicity of the proposed models, the results are really encouraging. The final aim is to define equivalent models to be used in laboratory measurements.

• 동력기계공학회지
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• 제6권1호
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• pp.55-60
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• 2002

There has been no report on the life prediction for gas turbine materials at high temperatures based on the creep properties and their relationship with the AE(acoustic emission) properties as a means of real-time non-destructive testing. One of the important issues is thus to develop a reliable method of evaluating creep properties by the AE technique. In this paper, the real-time evaluation of high temperature creep time and AE cumulative counts for nickel-based superalloy Udimet 720 was performed on round-bar type specimens under pure load at the temperatures of 811, 922 and 977K. The total AE cumulative counts until the starting point of secondary creep($N_1$) and that of tertiary creep($N_2$) have quantitative relationship with the tertiary creep time and the rupture time. It is thus possible to construct the life prediction system based on creep and the prevention system of tertiary creep by using AE technique.

• 한국항공우주학회지
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• 제32권3호
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• pp.30-36
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• 2004

장섬유 복합재료는 항공우주 구조물, 로봇 팔 등의 구조물에 광범위하게 적용되고 있으며, 복합재료의 비파괴 검사방법에 대한 연구는 구조의 안전성과 신뢰성을 향상시키기 위하여 매우 중요한 연구 분야로 대두되고 있다. 본 논문에서는 AE 선호의 특정주파수 성분을 추출할 수 있는 풍조회로를 가진 AE 신호 분석 장비를 설계, 제작하였다. 제작된 AE 신호 분석 장비에 충격이나 기계적 진동 등과 같은 외란을 가하였을 때 제작된 AE 신호 분석 장비의 잡음레벨은 상용 AE 신호 분석 장비의 잡음레벨보다 매우 낮은 값을 나타내었다. 또한 복합재료 시편의 정, 동적 인장시험 하에서 제작된 AE 분석 장비는 상용 장비와 통일한 수준의 복합재료 파손감지능력을 나타냄을 확인할 수 있었다.

• 비파괴검사학회지
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• 제24권3호
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• pp.233-239
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• 2004

지능재료는 안경테, 치아 교정과 같은 의료용 재료, 각종 센서 및 밸브 등의 광범위한 분야에서 적용되고 있다. 이와 같은 지적재료의 형상기억효과를 이용한 지적복합재료는 항공기의 부품, 산업구조물 및 항공산업에서도 그들 시스템의 모니터링을 위하여 사용되어 질 수 있다. 그러나 지능복합재료의 형상기억효과에 대한 분석과 시뮬레이션은 대단히 어렵다. 본 연구에서는 유한요소법을 이용하여 기지재와 하나의 강화섬유에 대한 2차원의 축 대칭 모델에 대하여 분석하였다. 상온(293K)과 고온(363K)에서 각각 해석되었으며 해석결과와 실험결과와의 강도 값을 비교 검토하였다. 더불어 음향방출 기법을 이용하여 지능복합재료(TiNi/A16061)의 예변형률과 고온에서의 미시적 손상거동을 평가하였다.

• 비파괴검사학회지
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• 제23권3호
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• pp.246-253
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• 2003

항공기 구조를 모사하여 일련의 리벳 구멍을 갖는 AA2024-T3 박판 구조를 대상으로 피로하중에 의한 단균열(short crack)의 발생시점과 성장거동을 음향방출(AE)을 위주로 한 측정으로 평가하였다. AE 위치표정에 의해 단균열의 좌표를 정확하게 결정하였으며, 이동식 현미경으로 균열의 크기를 측정하였다. 누적 AE 발생수 곡선은 단균열의 발생과 성장에 따라 일정한 간격을 두고 급격히 증가하는 양상을 보임으로써 여러 차례의 계단식 곡선을 형성하였다. AE 위치표정에서는 리벳 구멍을 중심으로 파괴역학에 근거한 관심영역(ROI)을 설정하였으며, 웨이블릿변환 잡음제거 방법을 사용하여 위치표정의 정확도를 향상할 수 있었다. 실제로 탐지된 신호의 대부분이 단 균열의 발생 및 성장과 관계없는 외부 잡음신호로 나타났으며, ROI 내에서 발생한 AE 발생원의 위치도 구조의 기하학적 특징이나 신호대잡음비의 영향에 의해 왜곡될 수 있음을 알 수 있었다.

• 한국자동차공학회논문집
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• 제12권2호
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• pp.182-189
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• 2004

The application of adhesively bonded components is increasing in various industries such as automobile, aircraft, IC packages, and soldering techniques. In spite of such wide application in adhesively bonded components, nondestructive test techniques applying to adhesively bonded components have not been clearly established yet. In this paper, characteristics of ultrasonic test on interfaces of adhesively bonded components have been investigated by calculating transmission coefficient theoretically and experimentally. From the experimental results, the optimum conditions to establish frequencies for adhesively bonded homogeneous and dissimilar components are 4∼6 MHz and 2∼4 MHz, respectively.

• Advances in aircraft and spacecraft science
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• 제5권2호
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• pp.165-175
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• 2018

Jet Propulsion Laboratory has traditionally performed system level vibration testing of flight spacecraft. There have been many discussions in the aerospace community for more than a decade about spacecraft vibration testing benefits or lack thereof. The benefits and potential issues of fully assembled flight spacecraft vibration testing are discussed herein. The following specific topics are discussed: spacecraft screening test to uncover workmanship problems for launch dynamics environments, force- and moment-limited vibration testing, potential issues with structural frequency identification using base shake test data, and failures related to vibration shaker testing and ways to prevent them.

• Advances in aircraft and spacecraft science
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• 제5권2호
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• pp.277-294
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• 2018

In the space industry, structures undergo several vibration and acoustic tests in order to verify their design and give confidence that they will survive the launch and other critical in-orbit dynamic scenarios. At component level, vibration tests are conducted with the aim to reach local or global interface loads without exceeding the design loads. So, it is often necessary to control and limit the input based on a load criterion. This means the test engineer should be able to assess the interface loads, even when load cannot be measured. This paper presents various approaches to evaluate interface loads using measured accelerations and by referring to mass operators. Various methods, from curve fitting techniques to finite element-based methods are presented. The methods are compared using signals with known imperfection to identify strengths and weaknesses of each mass operator definition.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2001년도 춘계학술대회논문집
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• pp.457-464
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• 2001

The aeroacoustic phenomena in the simple rectangular open cavity are well published by many researchers. But the geometry shapes of aircraft landing gear wells, weapon bays, etc. are more complicate than that of the simple retangular cavity. They are more similar to the cavity having cover-plates at adges, or Helmholtz resonator. Therefore, the effects of cover-plates existing on edges of rectangular open cavity are numerically investigated in this paper. The compressible Navier-Stokes equations are solved for two-dimensional cavities with laminar boundary layers upstream. The high-order and high-resolution numerical schemes are used for the evaluation of spatial derivatives and the time integration. Physically correct numerical boundary conditions and buffer zone techniques are implemented to produce time-accurate solutions in the whole computation domain. The computational domain is large enough to directly resolve a portion of the radiated acoustic field. Results show that the cover-plates existing on edges of cavity reduce the noise convected from cavity, make the frequency of noise become higher, and change the directivity pattern. So these results can be used in the design of a low noise cavity.

• Advances in aircraft and spacecraft science
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• 제6권6호
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• pp.463-478
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• 2019

The present work investigates the effect on the flow-induced vibrations of the lay-up sequence of composite laminated axisymmetric structures, using an hybrid approach based on a wave finite element and a transfer matrix method. The structural vibrations, under deterministic distributed pressure loads, diffuse acoustic field and turbulent boundary layer excitations, are analysed and compared. A multi-scale approach is used for the dynamic analysis of finite structures, using an elementary periodic subsystem. Different flow regimes and shell curvatures are analysed and the computational efficiency is also discussed.