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- 저자 : 권진희 ( Jin Hwe Kweon ) (검색결과 5 건)
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AE 기법을 이용한 외부수압을 받는 복합재 원통의 균열 검출
박진하 ( Jin Ha Park ),최진호 ( Jin Ho Choi ),권진희 ( Jin Hwe Kweon ) 한국복합재료학회 2011 Composites research Vol.24 No.3
복합재료의 비파괴 검사 방법에 관한 연구는 복합재료의 신뢰성 및 안전성을 개선시키는데 매우 중요하다. AE기법은 소성변형, 섬유파손, 모재균열 또는 박리에 의해 생성되는 탄성파에서 감지되는 변형 에너지를 감지하여 결함을 평가 하는 기법이다. 본 논문에서는 외부 수압을 받는 필라멘트 와인딩 복합재 원통과 샌드위치 원통의 수압시험이 수행되었고, PVDF센서로부터 측정된 AE 신호특성을 분석하였다. 또한, L-C 동조회로와 Band-pass filter 회로를 가진 AE 신호분석기를 설계, 제작 하였으며, 필라멘트 와인딩 원통과 샌드위치 원통에 대한 수압실험에서 제작된 AE 신호분석기의 균열 검출 능력을 평가하였다. The studies on the non-destructive testing methods of the composite materials are very important for improving their reliability and safety. AE(Acoustic Emission) can evaluate the defects by detecting the emitting strain energy when elastic waves are generated by the generation and growth of a crack, plastic deformation, fiber breakage, matrix cleavage or delamination. In this paper, the AE signals of the filament wound composite cylinder and sandwich cylinder during the pressure test were measured and analyzed. The signal characteristics of PVDF sensors were measured, and an AE signal analyzer which had the band-pass filter and L-C resonance filter were designed and fabricated. Also, the crack detection capability of the fabricated AE signal analyzer wes evaluated during the pressure tests of the filament wound composite cylinder and the sandwich cylinder.
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금속 핀으로 보강된 복합재 단일겹침 체결부의 강도 연구
이병희 ( Byeong Hee Lee ),박용빈 ( Yong Bin Park ),권진희 ( Jin Hwe Kweon ),최진호 ( Jin Ho Choi ),최익현 ( Ik Hyeon Choi ),장성태 ( Sung Tae Chang ) 한국복합재료학회 2012 Composites research Vol.25 No.3
The main objective of this study is to investigate the effect of metal z-pinning on the failure behavior of cocured composite single-lap joints. Three different pin diameters (0.3, 0.5, and 0.7 mm) and three pin areal densities (0.5, 2.0, and 4.0%) were examined. The specimens were fabricated by T700-12K-31E#2510 unidirectional prepreg from Toray. Stainless steel pins were used for z-pinning. Test results showed that except one case with extremely low pin density of 0.5%, all other z-pinned joints exhibited lower initial crack stresses than those of the unpinned joint. However the ultimate strength of the z-pinned joint increased up to 45% at most. Furthermore, even after the complete failure of the joint, the z-pins sustained the carried load to a certain degree experiencing large deformation and provided the stable fracture behavior for the composite joint.
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권진희 慶尙大學校 1999 論文集 Vol.38 No.-
A nonlinear finite element method is presented for the crippling analysis of graphite/epoxy composite channel beams which are widely applied to the aircraft stringers. Channel beams are idealized using nine-node degenerated shell element. To simulate the structural stiffness degradation after local failure, complete unloading model is introduced into the fi-nite element method. A modified Riks method is used to trace the post-failure equilibrium path after local buckling. Finite element results are compared with previous experimental results and show the excellent agreement. As numerical examples, Z-section composite channel beams are considered. The numerical results show that the most important par-ameter affecting the crippling stress of channel beams is the flange width. In terms of stacking sequence, the highest crippling stress is found at the stringer with [±45/0/90]s lamination.
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권진희 慶尙大學校 1998 論文集 Vol.37 No.-
The light aircraft, "Comet" with twin seats was developed with the fuselage made of 4130 steel tube. In this paper, the stress analysis results of the fuselage are presented. For the stress analysis, three load cases are considered based on the 4.4g symmetric pull-up, -1.8g symmetric push-over, and balanced landing conditions. The fuselage structures are idealized by the truss and bar elements. MSC/PATRAN and MSC/NASTRAN were utilized as the pre/post-processor and the solver. Margins of safety of the structures are estimated based on the static strength and the Euler buckling stress. In the first design, some elements showed the negative margins of safety by the column buckling for the load conditions 1 and 3. Finally the elements were modified to have positive values. Verification of the structural safety of the fuselage will be conducted by the flight test of the prototype.
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