A numerical and experimental investigation on composite stiffened panels into post-buckling

Lanzi, Luca

doi:10.1016/j.tws.2004.06.001

Cited by 56 publications

(33 citation statements)

References 25 publications

(26 reference statements)

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“…One of the main reasons that could have led to this lack of information in reference books is that, the finite element methodologies for the stability analysis of composites have been continuously enhanced in the last two decades, having been them object of research. This is also demonstrated by the numbers of papers [9][10][11][12] or collections of papers [13] dedicated to this topic. However, each of these research papers is focused on a specific application and emphasizes only the innovative aspects of the particular procedure related to the problem of interest.…”

mentioning

confidence: 90%

“…However, each of these research papers is focused on a specific application and emphasizes only the innovative aspects of the particular procedure related to the problem of interest. Therefore, a gap exists between the reference books [1][2][3][4][5][6][7][8] and the advanced outcomes published in research-oriented papers [9][10][11][12][13] in terms of the basic finite element methodologies for the analysis of the stability of composite structures.…”

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confidence: 99%

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Finite Element Analysis of the Stability (Buckling and Post-Buckling) of Composite Laminated Structures: Well Established Procedures and Challenges

Pietropaoli

Riccio

2010

Appl Compos Mater

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Finite element procedures for the analysis of composite structures under compressive loads (buckling and post-buckling) generally are not deployed in books because they are still considered object of research whereas they are deemed as assessed by researchers that focus their papers on restricted audience topics. Therefore, regarding these procedures, a gap exists in literature between what researchers consider as well established and what has been already published. The aim of this paper is to contribute to close this gap by providing an insight in linear and non-linear buckling analyses and in their use with composite structures. Both modelling and analysis considerations are presented and discussed, focusing on what can be considered as best practice when dealing with this kind of problems. Applications (to a stiffened panel and to a wing box) are provided for demonstrating the effectiveness of the procedures presented.

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confidence: 90%

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confidence: 99%

Finite Element Analysis of the Stability (Buckling and Post-Buckling) of Composite Laminated Structures: Well Established Procedures and Challenges

Pietropaoli

Riccio

2010

Appl Compos Mater

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“…Following the results obtained in previous works (Lanzi 2004), full non-linear analyses were performed by using the arch-length method proposed by Riks (1972Riks ( , 1979. Stiffened panels were modeled by 4-nodes shells, reduced integration, with six degrees of freedom at each node.…”

Section: Finite Element Modelmentioning

confidence: 99%

“…Three integration points along the thickness for each homogenized ply were used. After a preliminary sensitivity study on the element size and basing on the experience gained in previous works (Lanzi 2004), the dimensions of shell elements were assumed of about 8 × 8 mm.…”

Section: Finite Element Modelmentioning

confidence: 99%

Application of an iterative global approximation technique to structural optimizations

2008

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An iterative global approximation technique based on the Kriging method is proposed. The technique is validated through analytical test cases and then applied to solve two practical optimization problems: the optimization of aluminium-foam filled absorbers against crashworthiness requirements and the optimization of composite stiffened panels against buckling and strength constraints. The absorbers of the first application consist of two co-axial aluminium alloy tubes filled with lightweight aluminium foam. They were optimized to collapse at a controlled force level and to be the lightest possible. Explicit Finite element analyses were performed to evaluate the structural behavior of the absorbers in the sample points used to build the approximation. In the second application stiffened panels were optimized against buckling and strength constraints. The Tsai-Wu criterion was used to estimate first-ply failures as strength limit of the structure. Non-linear Riks analyses were performed with ABAQUS/Standard to evaluate the shell behavior in the sample points used to build the response surfaces. Basing on the obtained results the proposed iterative procedure seems a promising alternative to the classic a-priori building of response surface allowing better accuracy and saving of sample points.

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“…Furthermore, numerous experimentations on stiffened panels [3][4][5] and closed form configurations [6] had been conducted to get an insight into the complex post-buckling phenomenon. The high cost of manufacturing prototype composite structures and the difficulty to set up high fidelity tests with a complete set of measurements, make these tests quite complex and expensive to execute.…”

Section: Introductionmentioning

confidence: 99%

The post-buckling response of stiffened CFRP panels using a single-stringer compression specimen (SSCS): a numerical investigation

Sadiq¹,

Qing²

2015

Computational Methods and Experimental Measurements XVII

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The safe exploitation of the post-buckling region of CFRP panels in aerospace applications is of prime interest here. Due to the long computational time of finite element analysis for the post-buckling response of CFRP panels, there is a need to devise some efficient procedures. Skin/stringer debonding is primarily responsible for the collapse of the stiffened panels under compressive loading. In this study a simplified approach based on a single-stringer compression specimen (SSCS) has been employed to gain an insight into the post-buckling behaviour of CFRP panels under axial compression. A progressive damage model is used to get more accurate numerical results of the post-buckling response of SSCS. The outcomes of the study are compared with the published results and a fair agreement is found. In addition, a comparative study of open-and closed-section stringer stiffened panels based on a global-local approach for predicting pre-buckling, post-buckling and mode shapes is carried out. As the simplified model is used in this study so detailed damage models can be constructed to account for all damage modes: matrix cracking, fibre kinking, fibre fracture, and delamination. The study can be employed as a global-local approach to get the post-buckling response of CFRP stiffened panels. Furthermore, it also provides an efficient mean for the design optimization of CFRP structures in the post-buckling regime.

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A numerical and experimental investigation on composite stiffened panels into post-buckling

Cited by 56 publications

References 25 publications

Finite Element Analysis of the Stability (Buckling and Post-Buckling) of Composite Laminated Structures: Well Established Procedures and Challenges

Finite Element Analysis of the Stability (Buckling and Post-Buckling) of Composite Laminated Structures: Well Established Procedures and Challenges

Application of an iterative global approximation technique to structural optimizations

The post-buckling response of stiffened CFRP panels using a single-stringer compression specimen (SSCS): a numerical investigation

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