• 한국복합재료학회:학술대회논문집
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• 한국복합재료학회 2001년도 춘계학술발표대회 논문집
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• pp.69-73
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• 2001

Damage induced by low-velocity impact on the curved composite laminates was experimentally evaluated for CFRP cylindrical shells with the radius of curvatures of 50, 150, 300, and 500 mm. The result was then compared with that of flat laminates. The radius of curvatures and the effective shell stiffness appeared to considerably affect the dynamic impact response of curved shells. Under the same impact energy level, the maximum contact force increased with the decreasing radius of curvatures, with reaching 1.5 times that for plates at the radius of curvature of 50 mm. Since the maximum contact force is directly related to the impact damage, curved laminates can be more susceptible to delamination and less resistant to the low-velocity impact damage. The distribution of delamination along the thickness direction of curved laminates are also different from that of flat plates. Delamination was distributed rather even]y at each interface along the thickness direction of curved laminates. This implies that the effect of curvatures has to be considered for the design of a curved composite laminate.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2004년도 춘계학술대회
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• pp.162-167
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• 2004

The low velocity impact characteristics of composite laminate curved beams are investigated to increase damage tolerance and reduce the deflection. Drop weight impact tests of the composite curved beam were performed with respect to pre-load, then the damage after impact was measured by macrography. Also, finite element analyses were performed using ABAQUS to investigate the stress state of composite curved beam with respect to pre-load and impact. From the investigation, it was found that pre-load of the composite curved beams had much influence on impact damage of the curved beam, which showed good agreement with the experiment results.

• Steel and Composite Structures
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• 제19권5호
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• pp.1095-1113
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• 2015

In order to determine the mechanical behavior of the curved laminates in practical applications, three right-angled composite brackets with different lay-ups were investigated both experimentally and numerically. In the experimental, quasi-static tests on both unidirectional and multidirectional curved composite brackets were conducted to study the progressive failure and failure modes of the curved laminates. In the numerical modeling, three-dimensional finite element analysis was used to simulate the mechanical behavior of the laminates. Here, a strength-based failure criterion, namely the Ye criterion, was used to predict the delamination failure in the composite curved laminates. The mechanical responses of the laminate subjected to off-axis tensile loading were analyzed, which include the progressive failure, the failure locations, the load-displacement relationships, the load-strain relationships, and the stress distribution around the curved region of the angled bracket. Subsequently, the effects of stacking sequence and thickness on the load carrying capacity and the stiffness of the laminates were discussed in detail. Through the experimental observation and analysis, it was found that the failure mode of all the specimens is delamination, which is initiated abruptly and develops unstably on the symmetric plane, close to the inner surface, and about $29^{\circ}$ along the circumferential direction. It was also found that the stacking sequence and the thickness have significant influences on both the load carrying capacity and the stiffness of the laminates. However, the thickness effect is less than that on the curved aluminum plate.

• Composites Research
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• 제14권2호
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• pp.22-32
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• 2001

유한한 곡률을 가진 적층복합재 구조의 저속충격손상을 평가하기 위하여 곡률반경이 각각 50, 150, 300, 500 mm인 쉘 형태의 시편을 CFRP로 제작하여 충격실험을 행하고, 충격거동과 충격손상을 평판의 경우와 비교하여 고찰하였다. 실험결과는 비선형 유한요소해석의 결과와 비교하였다. 충격손상의 평가를 위해 충격거동을 측정한 결과 강성과 곡률반경이 쉘의 동적 충격거동에 큰 영향을 미치는 것을 확인하였으며, 충격거동과 충격손상은 밀접한 상호관계가 있으므로 구조의 곡률반경을 독립변수로 선정하여 충격손상을 평가하였다. 곡률반경이 감소하면서 복합재 쉘에는 동일한 충격조건에서 더 큰 최대 접촉력이 발생하였고, 가장 곡률이 심한 곡률반경 50 mm의 쉘에서는 평판의 약 1.5배에 이르는 최대 접촉력을 나타내었다. 따라서 동일한 충격조건 하에서 곡률반경 50 mm의 쉘에서는 평판의 경우보다 약 2.7때정도 더 큰 층간분리가 내부에 발생하였으며, 층간분리의 분포 또한 평판의 경우와는 달리 충격면에 가까운 계면에도 광범위하게 발생하는 경향이 곡륜반경이 감소할수록 더욱 현저하였다. 이는 곡률을 가진 구조가 평판 구조보다 손상저항성이 더 작은 것을 의미하므로 복합재료 설계 시 구조의 기하학적 형상을 반드시 고려하여야 한다.

• 대한기계학회논문집A
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• 제25권10호
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• pp.1514-1519
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• 2001

This paper is concerned with design, manufacturing and performance test of LIPCA ( Lightweight Piezo- composite Curved Actuator) using a top carbon fiber composite layer with near -zero CTE(coefficient of thermal expansion), a middle PZT ceramic wafer and a bottom glass/epoxy layer with high CTE. The main point of this design is to replace the heavy metal layers of THUNDER by thigh tweight fiber reinforced plastic layers without losing capabilities to generate high force and large displacement. It is possible to save weight up to about 30% if we replace the metallic backing material by the light fiber composite layer. We can also have design flexibility by selecting the fiber direction and the size of prepreg layers. In addition to the lightweight advantage and design flexibility, the proposed device can be manufactured without adhesive layers when we use epoxy resin prepreg system. Glass/epoxy prepregs, a ceramic wafer with electrode surfaces, and a graphite/epoxy prepreg were simply stacked and cured at an elevated temperature (177 $^{circ}C$ after following an autoclave bagging process. It was found that the manufactured composite laminate device had a sufficient curvature after detached from a flat mold. The analysis method of the cure curvature of LIPCA using the classical lamination theory is presented. The predicted curvatures are fairly in agreement with the experimental ones. In order to investigate the merits of LIPCA, a performance test of both LIPCA and THUNDE$^{TM}$ were conducted under the same boundary conditions. From the experimental actuation tests, it was observed that the developed actuator could generate larger actuation displacement than THUNDERT$^{TM}$.

• 한국복합재료학회:학술대회논문집
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• 한국복합재료학회 2000년도 춘계학술발표대회 논문집
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• pp.135-138
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• 2000

본 논문에서는 열팽창계수(CTE)가 거의 없는 카본게폭시, PZT 세라믹 박판, 그리고 열팽창계수가 큰 글래스/에폭시 층으로 이루어진 곡면형 복합재료 작동기(LIPCA)의 설계, 제작 및 성능실험에 대한 연구성과를 제시하고 있다. LIPCA의 른 요점은 기존 THUNDER의 성능을 유지하면서 이를 경량화 하기 위하여 THUNDER의 금속 층을 상대적으로 가벼운 섬유 강화 복합재료로 대체하는 것이다. 이러한 경량화 작업으로 LIPCA는 기존 THUNDER 보다 약 30~40% 정도의 무게를 감소시킬 수 있으며, 복합재료의 특성에 따라 설계의 유연성을 가질 수 있는 장점이 있다. 또한, 에폭시 수지를 사용함으로써 접착제 없이 평판 몰드에서 오토클레이브에서 177$^{\circ}C$로 경화되어, 탈형된 후 충분한 곡률을 형성하였다. 작동 성능 실험에서, LIPCA는 기존 THUNDER보다 작동변위가 향상됨을 보였다.

• Advances in nano research
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• 제14권2호
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• pp.141-154
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• 2023

Effects of viscoelastic foundation on vibration of curved-beam structure with clamped and simply-supported boundary conditions is investigated in this study. In doing so, a micro-scale laminate composite beam with two piezoelectric face layer with a carbon nanotube reinforces composite core is considered. The whole beam structure is laid on a viscoelastic substrate which normally occurred in actual conditions. Due to small scale of the structure non-classical elasticity theory provided more accurate results. Therefore, nonlocal strain gradient theory is employed here to capture both nano-scale effects on carbon nanotubes and microscale effects because of overall scale of the structure. Equivalent homogenous properties of the composite core is obtained using Halpin-Tsai equation. The equations of motion is derived considering energy terms of the beam and variational principle in minimizing total energy. The boundary condition is assumed to be clamped at one end and simply supported at the other end. Due to nonlinear terms in the equations of motion, semi-analytical method of general differential quadrature method is engaged to solve the equations. In addition, due to complexity in developing and solving equations of motion of arches, an artificial neural network is design and implemented to capture effects of different parameters on the inplane vibration of sandwich arches. At the end, effects of several parameters including nonlocal and gradient parameters, geometrical aspect ratios and substrate constants of the structure on the natural frequency and amplitude is derived. It is observed that increasing nonlocal and gradient parameters have contradictory effects of the amplitude and frequency of vibration of the laminate beam.

• International Journal of Aeronautical and Space Sciences
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• 제15권1호
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• pp.32-43
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• 2014

Automatic fiber placement (AFP) has become a popular processing technique for composites in the aerospace industry, due to its ability to place prepregs or tapes precisely in the exact position when complex parts are being manufactured. This paper presents the design, analysis, and manufacture of an AFP mandrel for composite aircraft fuselage skin fabrication. According to the design requirements, an AFP mandrel was developed and a numerical study was performed through the finite element method. Linear static load analyses were performed considering the mandrel structure self-weight and a 2940 N load from the AFP machine head. Modal analysis was also performed to determine the mandrel's natural frequencies. These analyses confirmed that the proposed mandrel meets the design requirements. A prototype mandrel was then manufactured and used to fabricate a composite fuselage skin. Material load tests were conducted on the AFP fuselage skin curved laminates, equivalent flat AFP, and hand layup laminates. The flat AFP and hand layup laminates showed almost identical strength results in tension and compression. Compared to hand layup, the flat AFP laminate modulus was 5.2% higher in tension and 12.6% lower in compression. The AFP curved laminates had an ultimate compressive strength of 1.6% to 8.7% higher than flat laminates. The FEM simulation predicted strengths were 4% higher in tension and 11% higher in compression than the flat laminate test results.

• 한국해양공학회지
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• 제18권5호
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• pp.36-42
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• 2004

Orthotropic laminates, such as [$0^{\circ}6$/$90^{\circ}6$]s and [$90^{\circ}6$/$0^{\circ}6$]s, were performed, using a commercial nonlinear finite element method. Interlaminar stress distributions, around the hole curve free-edge, were calculated. The delamination bearing strengths of pin joints were predicted, using the modified delamination failure criterion. These stress distributions were presented along the radial lines and around the free-edge of the hole. Further, three-dimensional non-linear contact analysis of orthotropic laminates was conducted to investigate the effect of friction. In this paper, laminates with a circular hole were taken to study interlaminar stresses the curved edge. This study may assist in the design of a thick composite laminate with mechanically pin joints.

• Composites Research
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• 제19권1호
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• pp.15-21
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• 2006

일방향 섬유로 보강된 고성능 복합재료의 경우 모든 방향에서 곡률을 가지는 구조물의 제작에 용이하지 않다. 본 연구에서는 높은 비강성, 비강도를 가지는 일방향으로 보강된 AS4/PEEK 프리프레그 테이프를 이용한 축소 시제 복합재료 접시형 안테나 반사판의 개발 결과를 보여준다. 개발을 위해서 유한요소법을 통한 적층인자 연구를 통한 저열팽창/등방변형의 반사판 설계기법을 확립하였으며, Fiber Placement System을 통한 자동섬유적층법을 이용하여 접시형 안테나 반사판이 제작되었다. 제작된 반사판은 Full Bridge Circuit의 Strain Cage를 이용한 열변형 실험법으로 열팽창 거동에 대한 실험을 수행하였으며, 열변형 해석결과와의 비교를 통하여 제작된 구조물을 검증하였다.