• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.3
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• pp.37-43
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• 2006

Six types of hat stiffened composite panels were manufactured with different bonding methods and stiffener section shapes and compression testing of these panels were performed. The panels showed similar behaviors in bucking and postbuckling region before a skin-stiffener separation failure occurred. Although all the separation failures occurred at the same locations of stiffener flanges close by skin buckling crests, the separation loads, separation failure growth behaviors and final collapse loads were different with respect to bonding methods and stiffener section shapes. As the separation failure initiated early and propagated larger area, collapse loads and structural efficiency of the panels decreased.

• Proceedings of the Korean Society of Precision Engineering Conference
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• 2001.10a
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• pp.239-243
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• 2001

본 연구에서는 절삭중 공구파손을 실시간으로 검출할 수있는 시스템을 구성하기 위한 일환으로 일차로 AE(acoustic emission)센서를 사용하여 mechanism의 특성과 공구파손에 따른 주파수 특성을 해석했고, 차후 연구로서 AE센서가 아닌 가속도센서와 전류센서 및 공작기계의 절삭동력계를 이용한 복합계측시 스템을 구성하여 절삭특성 및 공구파손이 발생할 때의 신호특성을 해석했다.

• Proceedings of the Korean Society of Precision Engineering Conference
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• 1993.10a
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• pp.79-82
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• 1993

본 연구는 드릴가공중 발생하는 드릴비트(Drill Bit)의 파손검출에 적합한 센서를 선택하고, 드릴비트 파손시 나타나는 센서신호의 특성에 대한 연구를 수행했다. 연구결과 이송축 전류신호 및 주축진동신호가 절삭시 나타나는 Power 및 진동의 특성을 잘 나타내고 있으며, 드릴비트의 파손을 판단할 수 있는 특징의 보완적 요소가 강하다는 결론을 얻었다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.1
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• pp.25-33
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• 2003

The failure load and mode of the unidirectional and fabric hybrid composite laminate joints are studied by test and finite element analysis. Test is conducted for the specimens with nine various geometries under pin loading. Finite element analysis is performed considering the contact and friction effects between the pin and laminate by MSC/NASTRAN. Failure is estimated by Tsai-Wu and Yamada-Sun criteria on the characteristic curve. While the failure of the specimens with the small width and edge length are much affected by the joint geometry, the geometry effects are negligible in the specimens with large width and edge length. Finite element analysis based on the characteristic length method reasonably predicts the failure load and mode of the joints.

• Proceedings of the KIEE Conference
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• 2000.11c
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• pp.575-577
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• 2000

(100) single crystal Si은 좋은 anisotropy etching 성질과 기계적 강도를 가지고 있어 MEMS 구조용 소재로 사용되고 있다. (100) Si의 신뢰성 평가를 위하여 필요한 탄성계수를 측정하고 반복동작에 의한 응력에 의한 파손특성을 평가하기 위하여 micromachining을 통해 resonator를 제작하였다. Resonator의 공진주파수를 분석함으로써 탄성계수를 추하고자 하였으며 반복응력에 대한 파괴특성을 평가하기 위하여 공진 상태에서 파괴가 일어날 때까지의 사이를 수를 측정함으로써 반복음력에 대한 Si의 피로특성을 평가하고자 하였다. 실험 결과 (100) Si의 <110> 방향으로의 탄성 개수를 측정할 수 있었으며 Si의 미세파손의 응력에 대한 의존성을 평가할 수 있었다. 평가결과 Si의 미세파손 메커니즘은 억제된 균열의 진전에 의한 subcritical crack에 의한 피로파괴 현상보다는 과도한 스트레스에 의한 순간적인 균열전파에 의해 지배됨을 관찰할 수 있었다.

• Journal of the KSME
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• v.32 no.1
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• pp.4-17
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• 1992

이 글에서는 복합적층판의 역학적 특성인 층간분리, 모재균열, 초기파손 후의 거동에 대한 문헌을 간단히 서술하고 그 특성을 살펴 보았다. 이상에서 살펴본 바와 같이 이방성인 층으로 구성된 복합적층 구조의 역학적 특성은 균질인 단일구조와 달리 각층의 재료상수가 달라층과 층 사이의 층간응력이 존재하여 층간분리현상이 발생하지 않도록 섬유방향뿐만 아니라 적층순서를 중요한 설계변수로 고려하여야 한다. 또한 모재균열로 인한 기계적 거동의 변화를 이해하고 초기파손 후의 손상을 고려한 해석을 수행하여 복합적층 구조의 응력해석 및 파손, 강도예측을 한다.

• Journal of Aerospace System Engineering
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• v.16 no.5
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• pp.35-42
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• 2022

This paper deals with predicting comparable mechanical properties of laminated composite plates. The stiffness of an equivalent anisotropic composite plate is derived based on classical lamination theory. A novel failure criterion is defined to describe the failure behaviour of laminated composite plates based on micro-mechanics failure criteria. Finally, the theory's validation of finite element analysis results was verified. We concluded that this theory is very suitable for failure analysis of laminated composite plates for aerospace applications due to their relative simplicity and computational efficiency.

• Composites Research
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• v.16 no.3
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• pp.58-67
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• 2003

To perform the realtime strain and fracture monitoring of the smart composite structures, two optical fiber sensor systems are proposed. The two types of the coherent sources were used for fracture signal detection - EDFA with FBG and EDFA with Fabry-Perot filter. These sources were coupled to EFPI sensors imbedded in composite specimens. To understand the characteristics of matrix crack signals, at first, we performed tensile tests using surface attached PZT sensors by changing the thickness and width of the specimens. This paper describes the implementation of time-frequency analysis such as short time Fourier transform (STFT) and wavelet transform (WT) for the quantitative evaluation of fracture signals. The experimental result shows the distinctive signal features in frequency domain due to the different specimen shapes. And, from the test of tensile load monitoring using optical fiber sensor systems, measured strain agreed with the value of electric strain gage and the fracture detection system could detect the moment of damage with high sensitivity to recognize the onset of micro-crack fracture signal.

• Transactions of the Korean Society of Mechanical Engineers
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• v.10 no.1
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• pp.157-163
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• 1986

A method to improve the Finite Elements Model and to identify structure stiffness damages utilizing measured dynamic characteristics is suggested. In order to show the effectiveness of the proposed method, a sample structure is adopted and tested. It is found that; (1) the Finite Elements Model can be improved with experimentally obtained dynamic characteristics satisfactorily and (2) the test results are also very helpful to search the stiffness damaged part of the sample structure via plotting the error matrix[E], especially it is aboved that the weighted error matrix is very effective to detect even the stiffness changes are relatively small.

• Composites Research
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• v.20 no.6
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• pp.8-14
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• 2007

Debonding failure characteristics of the composite skin-stiffener specimens were experimentally investigated. The influences of bonding methods, types of stiffener shape and various secondary bonding parameters were evaluated. Present test results combined with the previous test results[1] showed that the failure displacement of the skin-stiffener specimens well evaluates the skin-stiffener debonding failure strength of the composite stiffened panels. The specimens with an open type stiffener had lower bending stiffness and larger failure displacement than those with a closed type stiffener. Secondary bonding and co-curing with adhesive had better failure strength than co-curing without adhesive film. Secondary bonded specimens failed by adhesive failure and co-cured specimens failed by delamination failure. As the bondline thickness was thinner, the skin-stiffener specimens had higher failure strength. The fillets had no influence on failure strength of the specimens. The influence of the surface roughness was shown according to types of stiffener shape.