COCOMAT—improved material exploitation of composite airframe structures by accurate simulation of postbuckling and collapse

Degenhardt, Richard; Rolfes, Raimund; Zimmermann, Rolf; Rohwer, K.

doi:10.1016/j.compstruct.2005.11.042

Cited by 119 publications

(50 citation statements)

References 1 publication

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“…This fuselage was made from frames and stringers and was dedicated to commercial transport aircraft. POSICOSS program [2] was undertaken at the same time as TANGO, but was followed by COCOMAT program [3] which undertook deeper studies of the dimensioning methods. These study were mostly dedicated to increase the onset of degradation allowed during post-buckling of composite stiffened panels above the ultimate load.…”

Section: Introductionmentioning

confidence: 99%

Global behaviour of a composite stiffened panel in buckling. Part 1: Numerical modelling

Perret¹,

Mistou²,

Fazzini³

2011

Composite Structures

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a b s t r a c tThe present study analyses an aircraft composite fuselage structure manufactured by the Liquid Resin Infusion (LRI) process and subjected to a compressive load. LRI is based on the moulding of high performance composite parts by infusing liquid resin on dry fibres instead of prepreg fabrics or Resin Transfer Moulding (RTM). Actual industrial projects face composite integrated structure issues as a number of structures (stiffeners, . . .) are more and more integrated onto the skins of aircraft fuselage. A representative panel of a composite fuselage to be tested in buckling is studied numerically. This paper studies which of the real behaviours of the integrated structures are to be observed during this test. Numerical models are studied at a global scale of the composite stiffened panel. Linear and non linear analyses are conducted. The Tsai-Wu criterion with a progressive failure analysis is implemented, to describe the global behaviour of the panel up to collapse. Also, three stiffener connection methods are compared at the intersection between two types of integrated structures. Load shortening curves permit to estimate the expected load and displacements.

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Section: Introductionmentioning

confidence: 99%

Global behaviour of a composite stiffened panel in buckling. Part 1: Numerical modelling

Perret¹,

Mistou²,

Fazzini³

2011

Composite Structures

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“…The main structures of an aircraft are usually made of stiffened panels, which are designed for maximum strength, stiffness and buckling load. However, it is well-known that the buckling load does not represent the maximum load that the structure can bear, indeed it may hold several times the first buckling load withouth any damage (Stevens et al (1995), Zimmermann and Rolfes (2006), Degenhardt et al (2006)). Consequently some panels are designed to work in the post-buckling regime due to their high slenderness and that the post-buckling extra strength has potential to achieve lighter and more economic designs.…”

Section: Introductionmentioning

confidence: 99%

Reliability-based design optimization of composite stiffened panels in post-buckling regime

López

Bacarreza

Baldomir

et al. 2016

Struct Multidisc Optim

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This paper focuses on Deterministic and Reliability Based Design Optimization (DO and RBDO) of composite stiffened panels considering post-buckling regime and progressive failure analysis. The ultimate load that a post-buckled panel can hold is to be maximised by changing the stacking sequence of both skin and stringers composite layups. The RBDO problem looks for a design that collapses beyond the shortening of failure obtained in the DO phase with a target reliability while considering uncertainty in the elastic properties of the composite material. The RBDO algorithm proposed is decoupled and hence separates the Reliability Analysis (RA) from the deterministic optimization. The main code to drive both the DO and RBDO approaches is written in MATLAB and employs Genetic Algorithms (GA) to solve the DO loops because discrete design variables and highly nonlinear response functions are expected. The code is linked with Abaqus to perform parallel explicit nonlinear finite element analyses in order to obtain the structural responses at each generation. The RA is solved through an inverse Most Probable failure Point (MPP) search algorithm that benefits from a Poly-

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“…in Degenhardt et.al. [3]. Furthermore, we mention a general survey on the computation of interlaminar stress concentrations, see Mittelstedt and Becker [4].…”

Section: Introductionmentioning

confidence: 99%

An enhanced FSDT model for the calculation of interlaminar shear stresses in composite plate structures

2009

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Summary In this paper a procedure is proposed to calculate the interlaminar shear stresses in layered composite plates. The transverse shear stresses are obtained via the constitutive law and derivatives of some warping functions. For 4-node elements the derivatives of curvatures and strains of the reference surface with respect to the in-plane coordinates are determined through a system of four equations. Hence the equilibrium equations lead to a coupled system of ordinary differential equations, which are solved applying a displacement method. The resulting interlaminar shear stresses are continuous at the layer boundaries. The quality of the obtained results is demonstrated within several plate examples with symmetric and unsymmetric lay-ups. Comparisons with two other approaches using 9-node elements and a solid shell formulation together with a three-dimensional material law show good accuracy and efficiency of the proposed algorithm.

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COCOMAT—improved material exploitation of composite airframe structures by accurate simulation of postbuckling and collapse

Cited by 119 publications

References 1 publication

Global behaviour of a composite stiffened panel in buckling. Part 1: Numerical modelling

Global behaviour of a composite stiffened panel in buckling. Part 1: Numerical modelling

Reliability-based design optimization of composite stiffened panels in post-buckling regime

An enhanced FSDT model for the calculation of interlaminar shear stresses in composite plate structures

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