Search results

1 – 4 of 4
Per page
102050
Citations:
Loading...
Access Restricted. View access options
Article
Publication date: 9 April 2018

Krzysztof Majerski, Barbara Surowska, Jaroslaw Bienias and Jaroslaw Szusta

The purpose of this study is to investigate the results of reinforcing fibre metal laminates with glass fibres under low-cycle fatigue conditions in a limited number of cycles.

160

Abstract

Purpose

The purpose of this study is to investigate the results of reinforcing fibre metal laminates with glass fibres under low-cycle fatigue conditions in a limited number of cycles.

Design/methodology/approach

The tests were carried out on open-hole rectangular specimens loaded in tension-tension at high load ranges of 80 and 85 per cent of maximum force determined in static test, correspondingly. The number of cycles for destruction has been determined experimentally.

Findings

By means of microscopic observations, it was possible to determine the moment of crack initiation and their growth rate. Furthermore, it was possible to identify the impact of reinforcing fibre orientation in composite layers, material creating the metal layers, on fatigue life and on nature of crack propagation.

Practical implications

This work validates the possibility of increasing the resistance of fibre metal laminates to low-cycle fatigue by modifying the structure of the laminate.

Originality/value

The resistance of fibre metal laminates on low-cycle fatigue is not widely described and the phenomena occurring during degradation are poorly understood.

Details

Aircraft Engineering and Aerospace Technology, vol. 90 no. 3
Type: Research Article
ISSN: 1748-8842

Keywords

Access Restricted. View access options
Article
Publication date: 1 July 2014

Krzysztof Majerski, Barbara Surowska, Jarosław Bieniaś, Patryk Jakubczak and Monika Ostapiuk

The purpose of this paper is to present microstructural and fractographic analysis of damage in aluminum (2024T3)/carbon-fiber reinforced laminates (AlC) after static tensile…

298

Abstract

Purpose

The purpose of this paper is to present microstructural and fractographic analysis of damage in aluminum (2024T3)/carbon-fiber reinforced laminates (AlC) after static tensile test. The influence of fiber orientation on the failure was studied and discussed.

Design/methodology/approach

The subject of examination was AlC. The fiber–metal laminates (FMLs) were manufactured by stacking alternating layers of 2024-T3 aluminum alloy (0.3 mm per sheets) and carbon/epoxy composites made of unidirectional prepreg tape HexPly system (Hexcel, USA) in [0], [± 45] and [0/90]S configuration. The fractographic analysis was carried out after static tensile test on the damage area of the specimens. The mechanical tests have been performed in accordance to ASTM D3039. The microstructural and fractographic analysis of FMLs were studied using optical (Nikon SMZ1500, Japan) and scanning electron microscope (Zeiss Ultra Plus, Germany).

Findings

FMLs based on aluminum and carbon/epoxy composite are characterized by high tensile properties depending on their individual components and the orientation of the reinforcing fibers, failure of hybrid laminates indicates the complexity process of degradation of these materials. The nature of damage in FML layers is similar to that typical in polymer composites with interlaminar delaminations, transverse cracks of the composite layers, degradation of fiber/matrix interface, damage process in FMLs is also associated mainly with interface between metal and fiber reinforced composite. The mixed damage – cohesive and adhesive – was observed.

Originality/value

One of the most important aspect in the designing and manufacturing process in the service life of composite structures is damage mechanisms. The damage processes in composite materials, particularly in FMLs, are more complex in comparison to metal materials and fiber reinforced polymers.

Details

Aircraft Engineering and Aerospace Technology: An International Journal, vol. 86 no. 4
Type: Research Article
ISSN: 0002-2667

Keywords

Access Restricted. View access options
Article
Publication date: 1 July 2014

Patryk Jakubczak, Jaroslaw Bieniaś, Krzysztof Majerski, Monika Ostapiuk and Barbara Surowska

The purpose of this study was to carry out the analysis of impact resistance for aluminum hybrid laminates and polymer matrix composites reinforced with glass and carbon fibers…

472

Abstract

Purpose

The purpose of this study was to carry out the analysis of impact resistance for aluminum hybrid laminates and polymer matrix composites reinforced with glass and carbon fibers. Damage modes and damages process under varied impact energies are also presented and discussed.

Design/methodology/approach

The subject of examination were fiber metal laminates – FMLs (Al/CFRP and Al/GFRP). The samples were subjected to low-velocity impact by using a drop-weight impact tester. The specimens after impact were examined using non-destructive and destructive inspection techniques.

Findings

The hybrid laminates are characterized by higher resistance to impact in comparison to the conventional laminates. The delaminations between composite layers as well as the delaminations on metal/composite interface and lateral cracks are the prevailing type of destruction mechanisms. No significant relationships between metal volume friction coefficient vs response to the impact were recorded for the hybrid laminates under tests.

Practical implications

The understanding of impact behavior of FMLs is particularly important for selecting these materials and their designing, in damage tolerance philosophy aspect in aerospace industry as well as in searching the methods of predicting of FML hybrid materials resistance to impact. The test results might be useful for the validation of simulations using numerical methods.

Originality/value

The paper presents the impact resistance of new hybrid laminates for aerospace applications. The identification of damage character and failure mechanisms as well as the relationships between damage and impact responses of aluminum/carbon and aluminum/glass hybrid laminates were estimated.

Details

Aircraft Engineering and Aerospace Technology: An International Journal, vol. 86 no. 4
Type: Research Article
ISSN: 0002-2667

Keywords

Available. Content available
Article
Publication date: 9 April 2018

Richard Degenhardt and Leslie J. Cohen

444

Abstract

Details

Aircraft Engineering and Aerospace Technology, vol. 90 no. 3
Type: Research Article
ISSN: 1748-8842

1 – 4 of 4
Per page
102050