본 논문에서는 탄소섬유강화플라스틱 면재와 알루미늄 샌드위치 심재를 가지는 복합재 샌드위치의 제조와 3절점 굽힘 실험에 대해 연구하였다. 시편은 3가지 하니컴 종류(3.18 mm, 4.76 mm, 6.35 mm의 셀 크기)와 3가지 곡률 반지름(평판, r = 1.6 m, r = 1.3 m)을 가지도록 제작하였다. 샌드위치 곡률의 기준은 W-방향을 기준으로 제작 하였다. CFRP$2{\times}2$ 트윌의 인장에서 기계적 물성치(탄성계수, 강도, 푸아송 비)를 측정하여 그 값들을 다른 CFRP 섬유 적층판의 값과 비교하였다. 실험결과 평판 샌드위치 패널의 3절점 굽힘 실험에서 심재의 전단강도는 공개된 데이터에 비해 11-30% 낮게 나왔다. 제한된 시편 크기에서 1.3미터 곡률을 가지는 패널은 평판 패널에 비해 심재의 극한 전단강도가 0.8-3.8% 감소한 것으로 나타났다.
본 논문에서는 탄소섬유강화플라스틱 면재와 알루미늄 샌드위치 심재를 가지는 복합재 샌드위치의 제조와 3절점 굽힘 실험에 대해 연구하였다. 시편은 3가지 하니컴 종류(3.18 mm, 4.76 mm, 6.35 mm의 셀 크기)와 3가지 곡률 반지름(평판, r = 1.6 m, r = 1.3 m)을 가지도록 제작하였다. 샌드위치 곡률의 기준은 W-방향을 기준으로 제작 하였다. CFRP $2{\times}2$ 트윌의 인장에서 기계적 물성치(탄성계수, 강도, 푸아송 비)를 측정하여 그 값들을 다른 CFRP 섬유 적층판의 값과 비교하였다. 실험결과 평판 샌드위치 패널의 3절점 굽힘 실험에서 심재의 전단강도는 공개된 데이터에 비해 11-30% 낮게 나왔다. 제한된 시편 크기에서 1.3미터 곡률을 가지는 패널은 평판 패널에 비해 심재의 극한 전단강도가 0.8-3.8% 감소한 것으로 나타났다.
This paper presents the fabrication and 3-point flexion testing of carbon fiber reinforced polymer (CFRP) composite face/aluminum honeycomb core sandwich panels. Specimen sandwich panels were fabricated with three honeycomb types (3.18 mm, 4.76 mm, and 6.35 mm cell size) and three panel radii (flat,...
This paper presents the fabrication and 3-point flexion testing of carbon fiber reinforced polymer (CFRP) composite face/aluminum honeycomb core sandwich panels. Specimen sandwich panels were fabricated with three honeycomb types (3.18 mm, 4.76 mm, and 6.35 mm cell size) and three panel radii (flat, r = 1.6 m, r = 1.3 m). The curved sandwiches were fabricated normally with the core in the W-direction. The tensile mechanical properties of the CFRP $2{\times}2$ twill fabric face laminate were evaluated (modulus, strength, Poisson's ratio). The measured values are comparable to other CFRP fabric laminates. The flat sandwich 3-point flexion test core shear strength results were 11-30% lower than the manufacturer published data; the test set-up used may be the cause. With a limited sample size, the 1.3 meter panel curvature appeared to cause a 0.8-3.8% reduction in ultimate core shear strength compared to a flat panel.
This paper presents the fabrication and 3-point flexion testing of carbon fiber reinforced polymer (CFRP) composite face/aluminum honeycomb core sandwich panels. Specimen sandwich panels were fabricated with three honeycomb types (3.18 mm, 4.76 mm, and 6.35 mm cell size) and three panel radii (flat, r = 1.6 m, r = 1.3 m). The curved sandwiches were fabricated normally with the core in the W-direction. The tensile mechanical properties of the CFRP $2{\times}2$ twill fabric face laminate were evaluated (modulus, strength, Poisson's ratio). The measured values are comparable to other CFRP fabric laminates. The flat sandwich 3-point flexion test core shear strength results were 11-30% lower than the manufacturer published data; the test set-up used may be the cause. With a limited sample size, the 1.3 meter panel curvature appeared to cause a 0.8-3.8% reduction in ultimate core shear strength compared to a flat panel.
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제안 방법
8% reduction in ultimate core shear strength. Further tests are envisaged with different sandwich fabrication methods and a revised flexion test set-up.
In this study, aluminum honeycomb/CFRP composite sandwich panels were fabricated and tested inflexion. The tensile mechanical properties of the face laminate, a carbon/epoxy twill 2 × 2 fabric, were also evaluated.
Quasi-static 3-point flexural load testing of the panels was performed and the results are reported. The main objectives of this study were to characterize the tensile mechanical properties of the carbon/ epoxy fabric composite laminate; compare the core shear strength of the fabricated sandwich panels to manufacturer data; and verify the effect of curvature on the core shear strength of the sandwich. This study focused on initial material mechanical properties; galvanic corrosion concerns were disregarded.
The main objectives of this study were to characterize the tensile mechanical properties of the carbon/ epoxy fabric composite laminate; compare the core shear strength of the fabricated sandwich panels to manufacturer data; and verify the effect of curvature on the core shear strength of the sandwich. This study focused on initial material mechanical properties; galvanic corrosion concerns were disregarded.
대상 데이터
The aluminum honeycomb core material used was of the type PAMG-XR1 5052 with perforated walls manufactured by Plascore Inc., USA [2]. It’s an aerospace and military grade 5052 aluminum honeycomb core with a corrosion resistant coating.
This is most likely caused by some compaction of the last face cured on top of the honeycomb core. The flexion tests were performed using a universal testing press model LR 10K from Lloyd Instruments Ltd. equipped with a 10 kN load cell. Load was applied with a constant head displacement rate of 2 mm/min.
The 3 mm gage length gage was used to verify any influence on measurement scatter. The tensile tests were performed using a universal tension testing press model Instron 5582 from Illinois Tool Works Inc. with a 100 kN load cell. Load was applied through a constant head displacement rate of 2 mm/min.
이론/모형
The tensile properties of the carbon/epoxy fabric composite laminate were evaluated by ASTM D3039 [11]. Specimens in the 0o (warp), 45°, and 90° (fill) directions were cut from a 4-ply laminate ([0]4) with a diamond blade saw.
참고문헌 (19)
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