• 한국항공우주학회지
• /
• 제48권2호
• /
• pp.127-134
• /
• 2020

고초음속 항공기는 초음속 비행 중 공력 가열에 의하여 높은 온도 환경에 노출되기 때문에 동체 및 날개 구조물은 더블 패널 형태의 열 차폐 구조로 설계하여 기체 내부로 높은 온도의 열이 전달되는 것을 막는다. 얇은 두께의 더블 패널 외피는 초음속 항공기의 고출력 엔진 소음과 제트 유동에 의한 음향 하중에 노출되어 음향 피로 손상이 발생할 수 있다. 따라서 열음향 복합 하중을 받는 초음속 항공기 외피 구조의 거동 확인과 피로수명 예측이 필요하다. 본 논문에서는 열음향 복합 하중을 모사할 수 있는 열음향 시험 장치를 설계/제작하여 열음향 하중이 적용되는 티타늄 시편의 열음향 시험을 수행하였다. 열음향 복합 하중에 의한 구조물의 동적 거동을 확인하였으며, 시편 단위 열음향 시험 결과와 유한요소해석 결과를 비교하여 해석 모델을 검증하였다.

• Journal of Mechanical Science and Technology
• /
• 제17권3호
• /
• pp.391-399
• /
• 2003

The thermo-acoustic emission (AE) technique has been applied for nondestructive characterization of composite laminates subjected to cryogenic cooling. Thermo-AE events during heating and cooling cycles showed a Kaiser effect. An analysis of the thermo-AE behavior obtained during the 1st heating period suggested a method for determining the stress-free temperature of the composite laminates. Three different thermo-AE types classified by a short-time Fourier transform of AE signals enabled to offer a nondestructive estimation of the cryogenic damages of the composites, in that the different thermo-AE types corresponded to secondary microfracturing in the matrix contacting between crack surfaces and some abrasive contact between broken fiber ends during thermal load cycles.

• 한국복합재료학회:학술대회논문집
• /
• 한국복합재료학회 2001년도 추계학술발표대회 논문집
• /
• pp.111-115
• /
• 2001

Thermo-acoustic emission (AE) from composite laminates under the repetitive thermal cyclic loads have been quantitatively analyzed in consideration of AE source mechanisms. The repetitive thermal load brought about a large reduction, i.e. an exponential decrease in AE total ringdown counts and AE amplitudes. It was thought that generation of thermo-AE during the first thermal cycle was not caused by crack propagation but by secondary microfracturing due to abrasive contact between crack surfaces.

• 한국군사과학기술학회지
• /
• 제23권6호
• /
• pp.533-541
• /
• 2020

This study using ABAQUS investigates the nonlinear vibration responses when thermal and random acoustic loads are applied simultaneously to the stiffened composite panels. The nonlinear vibration analyses are performed with changing the number of stiffeners, and layup condition of the skin panel. The panel and stiffeners both are modeled using shell elements. Thermal load (ΔT) is assumed to have the temperature gradient through the thickness direction of the stiffened composite panel. The random acoustic load is represented as stationary white-Gaussian random pressure with zero mean and uniform magnitude over the panels. The thermal postbuckling analysis is conducted using RIKS method, and the nonlinear dynamic analysis is performed using Hilber-HughesTaylor time integration method. When ΔT = 25.18 ℃ and SPL = 105 dB are applied to the stiffened composite panel, the effect of the number of stiffener is investigated, and the snap-through responses are observed for composite panels without stiffeners and with 1 and 3 stiffeners. For investigation of the effect of layup condition of the skin panel, when ΔT = 38.53 ℃ and SPL = 110 dB are applied to the stiffened composite panel, the snap-through responses are shown when the fiber angle of the skin panel is 0°, 30°, and 60°.

• Steel and Composite Structures
• /
• 제44권6호
• /
• pp.829-843
• /
• 2022

This manuscript work presents a comprehensive continuum model capable to investigate the effect of porosity on vibro-acoustic behaviour of functionally graded (FG) beams resting on an elastic foundation subjected to thermal and mechanical loadings. Effects of uniform temperature rise and edge compressive load on the sound radiation characteristics are studied in a comparative manner. The numerical analysis is carried out by combining finite element method with Rayleigh's integral. Detailed parametric studies are accomplished, and influences of power law index, porosity volume, porosity distribution and boundary conditions on the vibro-acoustic response characteristics are analyzed. It is found that the vibro-acoustic response under mechanical edge compression is entirely different compared to from that under the thermal load. Furthermore, nature of grading of porosity affects the sound radiation behaviour for both the loads. The proposed model can be used to obtain the suppression performance of vibration and noise FG porous beams under thermal and mechanical loads.

• 한국소음진동공학회:학술대회논문집
• /
• 한국소음진동공학회 2006년도 추계학술대회논문집
• /
• pp.235-238
• /
• 2006

For high-speed aircraft and high-speed civil transport planes, certain structural skin components are subjected to very large acoustic loads in an elevated thermal environment. In this study, we used the single-mode Fokker-Panck distribution to predict displacements of isotropic plates subject to thermo-acoustic combined load. The single mode was formulated to predict the nonlinear dynamic responses of postbuckled plates under acoustic random excitation. Acoustic random excitation was used with Gauss distribution. Some important effects of the snap-through motion on the dynamic responses of the postbuckled plates are described.

• Composites Research
• /
• 제14권5호
• /
• pp.38-45
• /
• 2001

복합적층판에 반복 열부하사이클을 부여하여 열-음향방출(thermo-AE)신호의 카이저효과Kaiser effects)를 정량적으로 분석하고 이 거동을 음향방출의 발생원인과 관련시켜 해명하였다. 열부하사이클을 반복함에 따라 음향 방출의 총 링다운 카운트수 및 진폭이 급격히 감소하는 카이저 효과를 나타냈다. 이 카이저 효과는 총 링다운 카운트 수의 지수함수로 표현되었다. 열부하 사이클 시에 발생하는 AE는 균열진전에 의만 것이 아니라, 굴곡진 균열면간의 접촉에 의만 마모 및 2차적 미세손상의 발생과 관련되며, 2차 이후의 열부하 사이클 시에는 균열면간의 마찰적 미끄러짐으로 보다 약한 AE가 적은 사상수로 발생했던 것으로 추정되었다 이러한 열-음향방출 거동은 시험편의 종류 및 열부하 시의 최고온도에 따라 다른 특성을 보였다

• 한국군사과학기술학회지
• /
• 제24권1호
• /
• pp.1-11
• /
• 2021

Thermal protection system structures such as double-panel structures are used on the skin of the fuselage and wings to prevent the transfer of high heat into the interior of an high supersonic/hypersonic aircraft. The thin-walled double-panel skin can be exposed to acoustic loads by high power engine noise and jet flow noise, which can cause sonic fatigue damage. In order to predict the fatigue life of the skin, the octave bandwidth SPL should be calculated as narrow bandwidth PSD or acoustic load history using interpolation method. In this paper, a method of converting the octave bandwidth SPL acoustic load into a narrow bandwidth PSD and reconstructed acoustic load history was investigated. The octave bandwidth SPL was converted to the narrow bandwidth PSD using various interpolation methods such as flat, log and linear scale, and the probabilistic characteristics and fatigue damage results were compared. It was found that average error of fatigue damage index by the log scale interpolation method was relatively small among three methods.

• 비파괴검사학회지
• /
• 제21권3호
• /
• pp.261-268
• /
• 2001

열-음향방출(thermo-AE) 기법을 이용하여 두께 3mm, $[+45_6/-45_6]_s$ 복합재료 적층판의 열응력 유기 손상에 대한 비파괴평가의 유효성을 연구하였다. 반복적인 열부하 사이클에 의해서 thermo-AE 사상수가 감소하는 경향이 뚜렷하게 나타나서 열부하에 따른 카이저효과가 관찰되었다. 열부하사이클중의 thermo-AE거동을 분석하여 복합재료의 응력자유온도를 결정할 수 있었다. 초음파 C스캔, 광학현미경, 주사형 전자현미경을 통해 섬유파단과 모재파손이 관찰되었으며, 이들 파손 인자는 thermo-AE 신호의 단시간 퓨리에 변환처리에 의해 생성된 3종류의 서로 다른 시간-주파수 특성과 대응하였나 이 특성을 이용하여 복합재료의 냉각열처리 및 반복 열부하사이클시의 손상발생과정 및 내부 마찰거동 내역을 추적할 수 있었다.

• 한국초전도ㆍ저온공학회논문지
• /
• 제4권2호
• /
• pp.52-57
• /
• 2002

In this study, a thermoacoustic refrigerator, using a resonant standing acoustic wave. has been built. The refrigerant is helium gas. The description of thermoacoustic refrigerator was Presented. The temperature ratio (cold part temperature over hot part temperature) and the COP (Coefficient of Performance) that normalized by carnot's COP are plotted versus the thermal load applied to the cold end, for- various speaker power.