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fbtwitterlinkedinvimeoflicker grey 14rssslideshare1
Vali-Shariatpanahi, Sepideh; Noroozi, Siamak; Vinney, John
Languages: English
Types: Unknown
Subjects: ge
The first step in analysis composite joint is to have a correct and appropriate definition of properties of material used. The effect of fibre orientation and the interaction between them in the laminated composite play a key role in determining the laminate characteristics, the laminate mode of failure as well as the overall mode of joint failure. In order to study the failure of a new generation of composite laminate joints, sets of material properties are needed in three directions. This paper present the study of the in-plane (interlamina) shear properties and the behaviour of a specific Carbon Fibre Reinforced Plastic (CFRP) laminate with a particular balanced lay-up under compression load. This paper presents the continuation of a previous study by the author to study shear in a specific CFRP Ref [1]
  • The results below are discovered through our pilot algorithms. Let us know how we are doing!

    • 1- S.Vali-shariatpanahi “Evaluation of in-plane shear failure in composite laminates”, AIAA conference Illinois, 7-10 April 2008, 49th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
    • 2- ASTM D3846 -02 American Standard test method for In-Plane shear strength of Reinforced Plastics 2001.
    • 3- AECMA Standard prEN 2565 edition 2 May 1993, Aerospace series preparation of carbon fibre reinforced resin panels for test purposes.
    • 4- BS EN ISO 2818 British standard 1997, plastics preparation of test specimens by machining
    • 5- Patran/ Msc Nastran ( the McNeal -Schwendle cooperation) 2005
    • Notch depth is ½ specimen thickness, tolerance 0.2mm
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