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|Title: ||Damage assessment in CFRP laminates exposed to impact fatigue loading|
|Authors: ||Tsigkourakos, George|
Silberschmidt, Vadim V.
Ashcroft, Ian A.
|Keywords: ||Impact fatigue|
|Issue Date: ||2011|
|Publisher: ||© IOP Publishing Ltd|
|Citation: ||TSIGKOURAKOS, G., SILBERSCHMIDT, V.V. and ASHCROFT, I.A. , 2011. Damage assessment in CFRP laminates exposed to impact fatigue loading. Journal of Physics: Conference Series, 305 (1), 012047|
|Abstract: ||Demand for advanced engineering composites in the aerospace industry is
increasing continuously. Lately, carbon fibre reinforced polymers (CFRPs) became one of the
most important structural materials in the industry due to a combination of characteristics such
as: excellent stiffness, high strength-to-weight ratio, and ease of manufacture according to
application. In service, aerospace composite components and structures are exposed to various
transient loads, some of which can propagate in them as cyclic impacts. A typical example is
an effect of the wind gusts during flight.
This type of loading is known as impact fatigue (IF); it is a repetition of low-energy impacts.
Such loads can cause various types of damage in composites: fibre breaking, transverse matrix
cracking, de-bonding between fibres and matrix and delamination resulting in reduction of
residual stiffness and loss of functionality. Furthermore, this damage is often sub-surface,
which reinforces the need for more regular inspection.
The effects of IF are of major importance due its detrimental effect on the structural integrity of
components that can be generated after relatively few impacts at low force levels compared to
those in a standard fatigue regime. This study utilises an innovative testing system with the
capability of subjecting specimens to a series of repetitive impacts. The primary subject of this
paper is to assess the damaging effect of IF on the behaviour of drilled CFRP specimens,
exposed to such loading. A detailed damage analysis is implemented utilising an X-ray micro
computed tomography system. The main findings suggested that at early stages of life damage
is governed by o degree splits along the length of the specimens resulting in a 20% reduction of
stiffness. The final failure damage scenario indicated that transverse crasks in the 90 degree
plies are the main reason for complete delamination which can be translated to a 50% stiffness
|Description: ||This is a journal article. It was published in the serial, Journal of Physics: Conference Series [© IOP Publishing Ltd] and the definitive version is available at: http://iopscience.iop.org/1742-6596/305/1/012047|
|Version: ||Accepted for publication|
|Publisher Link: ||http://iopscience.iop.org/1742-6596/305/1/012047|
|Appears in Collections:||Published Articles (Mechanical and Manufacturing Engineering)|
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