Postbuckling Strength of Stiffened Composite Plates with Impact Damage

Kong, Cheol-Won; Hong, Chang Sun; Kim, Chun-Gon

doi:10.2514/2.851

Cited by 8 publications

(3 citation statements)

References 23 publications

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“…Impact damage seems to have a marginal influence on the buckling load of plain laminates with all sides supported, except when significant portions of the width are affected by fibre fracture, Olsson(1999), or when the boundary conditions are relaxed by impact close to edges with strong rotational constraint, Nilsson(1994). Similar conclusions can be drawn from experiments on stiffened panels by Kong, Hong & Kim(2000), Wiggenraad, Greenhalgh & Olsson(2002) and Greenhalgh et al(2003). There exists a strong interaction between global skin buckling modes and impact location.…”

Section: The Aeronautical Journal November 2004supporting

confidence: 78%

“…In contrast, tensile tests on coupons can be expected to be generally relevant for structures, provided a similar damage is present and that the ratio of coupon width to damage width is sufficient to ignore finite width effects. Experimental studies of the failure mechanisms of stiffened panels have been presented by Wiggenraad, Zhang & Davies(1999), Rosseau, Baker & Hethcock(2000), Kong, Hong & Kim(2000), Wiggenraad, Greenhalgh & Olsson(2002) and Greenhalgh et al(2003). Impact damage seems to have a marginal influence on the buckling load of plain laminates with all sides supported, except when significant portions of the width are affected by fibre fracture, Olsson(1999), or when the boundary conditions are relaxed by impact close to edges with strong rotational constraint, Nilsson(1994).…”

Section: The Aeronautical Journal November 2004mentioning

confidence: 98%

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Impact on composite structures

2004

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The problem of impact damage in laminated composite structures, and the consequent reduction in residual strength, has been a topic of continual research for over two decades. The number of journal papers on the subject now runs into four figures and most have been conscientiously reviewed by Abrate(1991, 1994, 1998). This review is not intended to be in the academic tradition, with emphasis on acknowledging the authorship of all the various research initiatives. Instead we present our opinions so that the reader can appreciate our current understanding of the problem, our capability of predicting by analysis, and the scope of the design tools for avoiding structural damage, or at least designing damage tolerant aerospace structures.

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Section: The Aeronautical Journal November 2004supporting

confidence: 78%

Section: The Aeronautical Journal November 2004mentioning

confidence: 98%

Impact on composite structures

2004

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“…The phenomenon is even more complex when fatigue loads are considered in the postbuckling regime and when defects such as impact damage are present. However, few experimental studies that consider the postbuckling behavior of composite stiffened panels with impact damage under static and fatigue loads 1–10 are available in the literature, mostly because these tests are complex and expensive to conduct.…”

Section: Introductionmentioning

confidence: 99%

Fatigue life and damage tolerance of postbuckled composite stiffened structures with indentation damage

Dávila

Bisagni

2017

Journal of Composite Materials

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The fatigue life and damage tolerance of composite stiffened panels with indentation damage are investigated experimentally using single-stringer compression specimens. The indentation damage was induced to one of the two flanges of the stringer of every panel. The advantages of indentation compared to impact are the simplicity of application, less dependence on boundary conditions, better controllability, and repeatability of the imparted damage. The tests were conducted using advanced instrumentation, including digital image correlation, passive thermography, and in situ ultrasonic scanning. Specimens with initial indentation damage ranging between 32 and 56 mm in length were tested quasi-statically and in fatigue, and the effects of cyclic load amplitude and damage size were studied. A means of comparison of the damage propagation rates and collapse loads based on a stress intensity measure and the Paris law is proposed. The stress intensity measure provides the means to compare the collapse loads of specimens with different damage types and damage sizes, while the Paris law is used to compare the damage propagation rates in specimens subjected to different cyclic loads. This approach enables a comparison of different tests and the potential identification of the effects that influence the fatigue lives and damage tolerance of postbuckled structures with defects.

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Numerical analysis of delamination growth for stiffened composite laminated plates

Bai

Chen

2004

Appl Math Mech

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A study of postbuckling and delamination propagation behavior in delaminated stiffened composite plates was presented. A methodology was proposed for simulating the multi-failure responses, such as initial and postbuckling, delamination onset and propagation, etc. A finite element analysis was conducted on the basis of the Mindlin first order shear effect theory and the von-Kdrmdn nonlinear deformation assumption. The total energy release rate used as the criteria of delamination growth was estimated with virtual crack closure technique (VCCT). A self-adaptive grid moving technology was adopted to model the delamination growth process. Moreover, the contact effect along delamination front was also considered during the numerical simulation process. By some numerical examples, the influence of distribution and location of stiffener, configuration and size of the delamination, boundary condition and contact effect upon the delamination growth behavior of the stiffened composite plates were investigated. The method and numerical conclusion provided should be of great value to engineers dealing with composite structures.

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Postbuckling Strength of Stiffened Composite Plates with Impact Damage

Cited by 8 publications

References 23 publications

Impact on composite structures

Impact on composite structures

Fatigue life and damage tolerance of postbuckled composite stiffened structures with indentation damage

Numerical analysis of delamination growth for stiffened composite laminated plates

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