Buckling and post-buckling of a composite C-section with cutout and flange reinforcement

Abstract

a b s t r a c tThis paper presents an investigation into the effect of cutout and flange reinforcement on the buckling and post-buckling behaviour of a carbon/epoxy composite C-section structure. The C-section having a cutout in the web is clamped at one end and subjected to a shear load at the other free end. Three different stiffener reinforcements were investigated in finite element analysis by using MSC Nastran. Buckling load was predicted by using both linear and nonlinear FE analysis. Experiments were carried out to validate the numerical model and results. Subsequently post-buckling analysis was carried out by predicting the load-deflection response of the C-section beam in nonlinear analysis. Tsai-Wu failure criterion was used to detect the first-play-failure load. The effect of circular and diamond cutout shape and effective flange reinforcements were investigated. The results show that the cutout and reinforcement have little effect on the buckling stability. However an L-shape stiffener to reinforce the C-section flange can improve the critical failure load by 20.9%.

Magnet assisted composite manufacturing: A novel fabrication technique for high‐quality composite laminates

“…The thickness of the lay‐up decreases during cure, so the magnetic pressure will increase gradually. According to the previously published literature, the thicknesses of the fabricated carbon fiber‐epoxy prepreg laminates for 8, 16, and 20 plies are ∼2.1–4.3 mm . Considering these thicknesses, the N38EH magnets are capable of generating a maximum pressure of 0.21–0.31 MPa (30–45 psi).…”

Analisis Kekuatan Struktur Komposit Dengan Ply Drop-off Pada Roda Pendarat Utama Pesawat Nir Awak Menggunakan Metode Elemen Hingga

“…F 5: , F 5; , F 6: , F 6; adalah kekuatan lamina longitudinal arah-1 dan transversal arah-2; F 7 adalah kekuatan geser dan G bernilai=-0.5 (Guo, et al, 2014) Nilai di bawah satu pada nilai indeks kegagalan menandakan struktur komposit tersebut aman ketika menerima beban. Sedangkan nilai satu menandakan tepat gagal dan nilai lebih dari satu menandakan kegagalan.…”

A comprehensive study on the buckling behaviour of woven composite plates with major aerospace cutouts under uniaxial loading

“…Their research showed that it is possible to design and manufacture composite panels whose buckling and first-ply failure responses are insensitive to the existence of a central hole. Guo et al [17] studied composite C-section structure having circular and diamond shape cutout with flange reinforcements. They revealed that both cutout and reinforcement has little effect on the buckling stability of C-section structure.…”

“…From the above literature review, it was found that even though theoretical formulations of solving critical buckling loads of structures are successful [4,5] but plates with cutouts have got limitations [1][2][3]. Based on Finite Element formulations and experimental studies, plates with different cutout shapes [6][7][8][9][10][11][12][13][19][20][21][22][23][24][25][26][27][28][29] and reinforcements [15][16][17][18] were studied but comprehensive studies based on all major cutouts are notably limited. This paper addresses the effect of all major cutout shapes (circular, square, horizontal ellipse, vertical ellipse and diamond) and sizes, plate aspect ratio, ply thickness and fiber orientation angle on the buckling behavior of E-glass composite plate.…”