scholarly journals A post-buckling compressive failure analysis framework for composite stiffened panels considering intra-, inter-laminar damage and stiffener debonding

2019 ◽  
Vol 13 ◽  
pp. 102205 ◽  
Author(s):  
Libin Zhao ◽  
Kangkang Wang ◽  
Fan Ding ◽  
Tianliang Qin ◽  
Jifeng Xu ◽  
...  
Keyword(s):  
Failure Analysis ◽  
Compressive Failure ◽  
Analysis Framework ◽  
Stiffened Panels ◽  
Post Buckling

The Effect of Stitching on Compression Behavior of Stiffened Composite Panels

2001 ◽  
Author(s):  
Sung S. Suh ◽  
H. Thomas Hahn ◽  
Nanlin Han ◽  
Jenn-Ming Yang
Keyword(s):  
Beneficial Effect ◽  
Compression Behavior ◽  
Stiffened Panels ◽  
Shell Elements ◽  
Stitch Density ◽  
Stiffened Composite Panels ◽  
Out Of Plane ◽  
Post Buckling ◽  
Post Impact ◽  
Good Agreement

Abstract Failure of stiffened panels under compression is preceded by buckling of their skin and hence is affected by the presence of out-of-plane stresses. One of the promising methods of preventing premature delamination is stitching. The present paper discusses the effect of such stitching on compression behavior of blade-stiffened panels that were fabricated from plain weave AS4/3501-6 through resin film infusion process. Kevlar 29 yarn was used at a stitch density of 9.92 stitches per cm2. Some of the panels were damaged by drop-weight impact before compression testing. For comparison purposes unstitched panels with the same materials and dimensions were also tested under the same loading conditions. Stitching resulted in a 10% improvement in strength in the absence of any intentional damage. The beneficial effect of stitching was most obvious when the panels were impacted on a flange: a 50% improvement was observed in post-impact strength. However, stitching could not prevent stiffener from failure when impacted directly. Thus stitching had no beneficial effect when impact occurred on a stiffener. A buckling and post-buckling analysis was carried out using 3-D shell elements on the Abaqus. Predictions were in fairly good agreement with the experimental data.

scholarly journals Buckling/post-buckling strength of friction stir welded aircraft stiffened panels

2012 ◽  
Vol 228 (2) ◽  
pp. 178-192 ◽  
Author(s):  
A Murphy ◽  
T Ekmekyapar ◽  
M Özakça ◽  
K Poston ◽  
G Moore ◽  
...  
Keyword(s):  
Stiffened Panels ◽  
Buckling Strength ◽  
Friction Stir ◽  
Post Buckling

scholarly journals Stability Analysis of Different Stiffened Plates in Thermal-Mechanical Coupling Environments

2020 ◽  
Vol 38 (1) ◽  
pp. 40-47
Author(s):  
Liang Ma ◽  
Yu'e Ma ◽  
Qiang Qin
Keyword(s):  
Mechanical Load ◽  
Maximum Load ◽  
Stiffened Panel ◽  
Stiffened Plate ◽  
Stiffened Panels ◽  
Mechanical Coupling ◽  
Cross Section Area ◽  
Out Of Plane ◽  
Post Buckling ◽  
Plane Displacement

In view of the structural stability problem of different typical stiffened panels under different loading conditions, ABAQUS software was used to build finite element models of four typical stiffened panels with the same cross section area. The buckling and post-buckling response of the stiffened panels was analyzed and buckling modes and deflection curves of stiffened panels under mechanical, temperature and thermal-mechanical coupling load were obtained. The result indicates that T type stiffened plate shows great stability under mechanical load, the maximum load is 281KN, which is much higher than that of other types of stiffened panels. The maximum load of a stiffened panel is little affected by the direction of the fillet, but reasonable layout of panels can greatly reduce the out-of-plane displacement of the stiffened panel. There is no obvious pre-buckling process when a panel is under thermal-mechanical coupling load and the post-buckling response is roughly similar as that under mechanical load. But the maximum load of a stiffened plate will decrease by 8%-15% due to the application of temperature load.

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