GLARE (glass-reinforced aluminum laminate) is a new class of fiber metal laminates for advanced aerospace structural applications. It consists of thin aluminum sheets bonded together with unidirectional or biaxially reinforced adhesive prepreg of high-strength glass fibers. GLARE laminates offer a unique combination of properties such as outstanding fatigue resistance, high specific static properties, excellent impact resistance, good residual and blunt notch strength, flame resistance and corrosion properties, and ease of manufacture and repair. GLARE laminates can be tailored to suit a wide variety of applications by varying the fiber/resin system, the alloy type and thickness, stacking sequence, fiber orientation, surface pretreatment technique, etc. This article presents a comprehensive overview of the mechanical properties of various GLARE laminates under different loading conditions.

The mechanical behavior of GLARE laminates for aircraft structures

Evaluation of burst pressure prediction models for line pipes

Laminated composites are designed to withstand significant loads thanks to the cooperation and interaction of plies with different orientations. Due to the growing use of these materials in industrial structures, their modeling constitutes an important scientific challenge. The damage mesomodel developed at LMT-Cachan, based on a micromechanical description, aims at predicting the evolution of damage in composite structures until failure. In this work, open-hole tensile tests performed on quasi-isotropic laminates are used to validate this model. Starting from Wisnom and Hallett’s work, a comparison between experimental and numerical results is carried out focusing on two main parameters: the ply’s thickness and the in-plane scaling effect.

On the validation of a damage mesomodel for laminated composites by means of open-hole tensile tests on quasi-isotropic laminates

Average shear stress yield criterion and its application to plastic collapse analysis of pipelines

A coupled strength and toughness criterion for the prediction of the open hole tensile strength of a composite plate

A comparative study on failure pressure estimations of unflawed cylindrical vessels

Notched tensile strength for long- and short-fiber reinforced polyamide

Residual strength of aluminum-lithium alloy center surface crack tension specimens at cryogenic temperatures

This paper improves the two stress fracture criteria proposed by Whitney and Nuismer (known as the point stress criterion and the average stress criterion) to predict the strength of composite laminates with a circular hole. In the point stress criterion, it is assumed that the failure occurs when the stress over some distance (d 0) away from the notch is equal to or greater than the un-notched laminate strength. In the average stress criterion it is assumed that failure occurs when the average stress over some distance (a 0) ahead of the notch equals the unnotched laminate strength. Both stress fracture criteria are two parameter models based on the unnotched strength (σ 0) and a characteristic dimension (d 0 ora 0). A simple relation is used for the characteristic length to improve the accuracy while evaluating the notched strength of carbon/epoxy composite laminates. The analytical results are compared well with the existing test results of AS4-carbon/948 Al epoxy [0/90]4s and [0/ ± 45/90]2S composite laminates with various hole diameters and specimen widths.

Notched strength of carbon fibre/epoxy composite laminates with a circular hole

This paper improves the stress fracture criteria proposed by Whitney–Nuismer known as the point stress criterion (PSC) and the average stress criterion (ASC), to predict the strength of composite laminates containing holes and slits. A simple relation is used for the characteristic length to improve the accuracy while evaluating the notched strength of laminates. The applicability of the proposed approach is examined by considering the notched strength data on carbon/epoxy and boron/aluminum laminates. The analytical results obtained in the present study correlate well with the test results of different notched configurations. This study confirms that the present modification in the stress fracture criteria can be used for notched strength evaluation of composite laminates.

P. K. Govindan Potti

Papers

A comparative study on failure pressure estimations of unflawed cylindrical vessels

Notched tensile strength for long- and short-fiber reinforced polyamide

Residual strength of aluminum-lithium alloy center surface crack tension specimens at cryogenic temperatures

Notched strength of carbon fibre/epoxy composite laminates with a circular hole

Tensile fracture strength of boron/aluminum laminates with holes and slits