Postbuckling behavior of selected flat stiffened graphite-epoxy panels loaded in compression

Starnes, James H.; Knight, Norman F.; Rouse, Marshall

doi:10.2514/6.1982-777

Cited by 16 publications

(8 citation statements)

References 9 publications

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“…The general issues are impact damage resistance and impact damage tolerance . The impact resistance and tolerance of composite structures have been reported in the literature . It has been reported that catastrophic failure can occur when loaded panels are subjected to impact.…”

Section: Introductionmentioning

confidence: 99%

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Water absorption and low‐energy impact and their role in the failure of ±45° carbon fibre composites

2016

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Defects in polymer composites associated with in-service damage induced by impact and those produced by environmental degradation due moisture absorption can have a significant influence on the mechanical properties and failure modes of the structures. This study evaluates the flexural characteristics and failure modes of 6458 carbon/ epoxy laminates under different conditions. The flexural strength and stiffness of these composites were inspected before and after subjecting to water absorption, drying, re-drying and low energy impact. It was observed that both absorbed water and low energy impact caused significant deformations and fractures which drastically reduced the load carrying ability of the 6458 carbon/epoxy laminates. Re-drying slightly improved the properties and reversed the effects of water. POLYM. COMPOS., 00:000-000, 2016.

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Section: Introductionmentioning

confidence: 99%

“…It has been reported that catastrophic failure can occur when loaded panels are subjected to impact. This phenomenon has been proved by the investigation of impact resistance and tolerance of a range of tensile and compressive preloaded structures .…”

Section: Introductionmentioning

confidence: 99%

Water absorption and low‐energy impact and their role in the failure of ±45° carbon fibre composites

2016

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“…Previous investigators have researched dynamic properties of composite-stiffened panels systematically. [11][12][13][14][15][16][17][18][19][20][21][22] Guo 11 studied buckling and post-buckling performance of a composite C-section with cutout and flange reinforcement. The effect of circular and diamond cutout shapes and effective flange reinforcements were investigated.…”

Section: Introductionmentioning

confidence: 99%

Effect of hygrothermal condition on buckling and post-buckling performance of CCF300/5228A aero composite stiffened panel under axial compression

Feng

et al. 2015

Journal of Reinforced Plastics and Composites

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CCF300/5228A aero composite stiffened panels achieved absorbing saturation in hygrothermal condition (70 C distilled water), whose absorbing process followed the Fick law. Many debonding and gaps of matrix to fibers could be observed after hygrothermal exposure by scanning electron microscope (SEM). Compressive experiments were conducted on unaged and aged composite stiffened panels. Failure modes of the two types of specimens are quite similar with several major ways, including the debonding and fracture of stiffeners together with the splitting and ripping of panel. Buckling patterns for both types of specimens are similar and characterized by buckling of panels between stiffeners and buckling of the middle two stiffeners. However, the bending direction of buckling mid-panel for aged specimens is opposite to that of the unaged at same position panel, which shows that hygrothermal condition influences the bending direction of buckling mid-panels seriously. There still exists a post-buckling process for aged specimens under axial compression, whose average buckling load and failure load decrease by 3.1% and 22.2% respectively, comparing to that of unaged specimens.

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“…However, when the spacing of stiffeners becomes large enough in order to allow the skin to buckle at loadings lower than their ultimate load, the equivalent orthotropic shell model becomes questionable in representing the true structural behavior of stiffened shells [Ji and Yeh (1090)]. Finite element modeling of stiffened panels can be created by discretizing both the skin and the stiffeners with plate and shell elements [Starnes et al (1985;1995)]. However, in the absence of repeated symmetry conditions the finite element method becomes very demanding because of the extensive number of elements.…”

Section: Introductionmentioning

confidence: 99%

Aeroelastic Analysis of Rotor Blades Using Three Dimensional Flexible Multibody Dynamic Analysis

Das

2007

48th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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for their valuable suggestions while serving in the committee. It was very kind of Dr. Friedrich K. Straub to have arranged the trips to The Boeing Company, Mesa. These trips were very informative and so was Dr. Straub's presence in the committee. I wish to express my deepest gratitude to Professors Atila Barut and Ibrahim Guven for their expert advice. Dr. Barut was present every time I needed a jump start or some extra fuel. Starting from linear static to nonlinear dynamic problems, Dr. Barut was instrumental in eradicating the dark spots in my knowledge in these subjects. Finally, I would like to thank all the members of my group for providing a constant supply of energy and making the journey less monotonous. I was fortunately enough to have interacted with Bahattin Kilic and Erkan Oterkus. Our discussion on topics ranging from mechanics to politics ensured that my mind was always active and aware of the surroundings. Several accidents were averted because of their friendship.

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Postbuckling behavior of selected flat stiffened graphite-epoxy panels loaded in compression

Cited by 16 publications

References 9 publications

Water absorption and low‐energy impact and their role in the failure of ±45° carbon fibre composites

Water absorption and low‐energy impact and their role in the failure of ±45° carbon fibre composites

Effect of hygrothermal condition on buckling and post-buckling performance of CCF300/5228A aero composite stiffened panel under axial compression

Aeroelastic Analysis of Rotor Blades Using Three Dimensional Flexible Multibody Dynamic Analysis

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