Multi-Objective Optimisation (Weight and Cost Oriented) of Impact Damage Resistant Stiffened Composite Panels

The compressive response of thin-skin stiffened composite panels with low velocity impact damage is examined. The finite element method together with the Soutis-Fleck fracture mechanics model is used to predict damage initiation in the form of fibre microbuckling in the 0° plies, propagation and final failure; in the model the impact damage is replaced with an equivalent circular or elliptical open hole. Theoretical results are compared to experimental data and found in good agreement.

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Impact Damage Tolerance Analysis of Stiffened Composite Panels

Journal of Composite Materials ◽

10.1177/002199801772661489 ◽

2001 ◽

Vol 35 (20) ◽

pp. 1844-1867 ◽

Cited By ~ 2

Author(s):

Puhui Chen ◽

Zhen Shen ◽

Junyang Wang

Keyword(s):

Damage Tolerance ◽

Impact Damage ◽

Tolerance Analysis ◽

Composite Panels ◽

Stiffened Composite Panels ◽

Damage Tolerance Analysis

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Experimental and numerical analysis for the post-buckling behavior of stiffened composite panels with impact damage

Composite Structures ◽

10.1016/j.compstruct.2015.08.019 ◽

2015 ◽

Vol 133 ◽

pp. 840-846 ◽

Cited By ~ 28

Author(s):

X.M. Wang ◽

W. Cao ◽

C.H. Deng ◽

P.Y. Wang ◽

Z.F. Yue

Keyword(s):

Numerical Analysis ◽

Impact Damage ◽

Composite Panels ◽

Buckling Behavior ◽

Stiffened Composite Panels ◽

Post Buckling

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Impact Damage Management of Composite Laminated Structures by a Probabilistic Approach

The Open Materials Science Journal ◽

10.2174/1874088x01307010008 ◽

2013 ◽

Vol 7 (1) ◽

pp. 8-22 ◽

Cited By ~ 6

Author(s):

A. Riccio ◽

T. Russo ◽

F. Scaramuzzino

Keyword(s):

Impact Damage ◽

Probabilistic Approach ◽

Numerical Procedure ◽

Added Value ◽

Composite Panels ◽

Damage Resistance ◽

Impact Location ◽

Stiffened Composite Panels ◽

Aircraft Component ◽

Laminated Structures

A numerical procedure for the design of impact damage resistant composite laminated structures is proposed in the present paper. This procedure, based on probabilistic analyses, is able to support the design of complex composite laminated structures by accounting for the scatter in composite materials' mechanical properties (related to the mutable environmental conditions experienced by an aircraft component during its service life) and by accounting for the uncertainty on accidental impacts locations. A failure criterion, based on the determination of the threshold critical impact energy for impact induced delaminations’ onset, is adopted for the evaluation of the damage resistance of composite laminated structures, in the frame of the introduced probabilistic analyses. The proposed procedure has been implemented into a commercial FEM platform and composite panels have been used as numerical benchmarks to investigate the influence of the combined material properties and impact location uncertainties on composite laminated structures’ impact damage resistance. A further comparison between two different stiffened composite panels designs have been introduced to highlight the added value of the proposed impact damage resistance probabilistic approach in terms of safety and effectiveness, with respect to the standard deterministic tools.

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