Computer simulation of impact damage on thin-skinned carbon fibre composite panels

1996 ◽  
Vol 1 (3) ◽  
pp. 295-304 ◽  
Author(s):  
Alan K.H. Cheung ◽  
Murray L. Scott
Keyword(s):  
Computer Simulation ◽  
Carbon Fibre ◽  
Impact Damage ◽  
Fibre Composite ◽  
Composite Panels ◽  
Carbon Fibre Composite

Acoustic Emission Monitoring of Defects in Buckling CFRP Composite Panels

2006 ◽  
Vol 13-14 ◽  
pp. 259-266 ◽  
Author(s):  
Mark J. Eaton ◽  
Karen M. Holford ◽  
C.A. Featherston ◽  
Rhys Pullin
Keyword(s):  
Acoustic Emission ◽  
Carbon Fibre ◽  
Optical Measurement ◽  
Impact Damage ◽  
Fibre Composite ◽  
Carbon Fibre Composite ◽  
Premature Failure ◽  
Full Field ◽  
Cfrp Composite ◽  
Acoustic Emission Sensors

The presence of impact damage in a carbon fibre composite can reduce its capacity to support an in-plane load, which can lead to an unexpected or premature failure. This paper reports on an investigation into two slender carbon/fibre epoxy panels, one un-damaged and one with an artificial delamination introduced using an embedded section of PTFE. The reported tests form part of a larger series of investigations using differing sizes of artificial delamination and real impact damage. An investigation of wave velocity propagation at varying angles to the composite lay up was completed to assist in source location. The specimens were loaded under, uniaxial in-plane loading and monitored using four resonant acoustic emission sensors. A full field optical measurement system was used to measure the global displacement of the specimens. Analysis of AE waveforms and AE hit rate were used to assess the buckling of the panel. The results compared favourably with the optical measurement results.

On the self-piercing riveting of aluminium blanks and carbon fibre composite panels

2011 ◽  
Vol 6 (1) ◽  
pp. 137-144 ◽  
Author(s):  
Giuseppe Di Franco ◽  
Livan Fratini ◽  
Antonino Pasta ◽  
Vincenzo F. Ruisi
Keyword(s):  
Carbon Fibre ◽  
Fibre Composite ◽  
The Self ◽  
Composite Panels ◽  
Carbon Fibre Composite

On the self-piercing riveting of aluminium blanks and carbon fibre composite panels

2010 ◽  
Vol 3 (S1) ◽  
pp. 1035-1038 ◽  
Author(s):  
G. Di Franco ◽  
L. Fratini ◽  
A. Pasta ◽  
A. F. Ruisi
Keyword(s):  
Carbon Fibre ◽  
Fibre Composite ◽  
The Self ◽  
Composite Panels ◽  
Carbon Fibre Composite

Fatigue behaviour of self-piercing riveting of aluminium blanks and carbon fibre composite panels

2012 ◽  
Vol 226 (3) ◽  
pp. 230-241 ◽  
Author(s):  
Giuseppe Di Franco ◽  
Livan Fratini ◽  
Antonino Pasta
Keyword(s):  
Finite Element Method ◽  
Finite Element ◽  
Carbon Fibre ◽  
Mechanical Behaviour ◽  
Fibre Composite ◽  
Experimental Tests ◽  
Fatigue Behaviour ◽  
Process Conditions ◽  
Composite Panels ◽  
Carbon Fibre Composite

In this article, the fatigue behaviour of self-piercing riveted joints in 2024-T6 aluminium sheets and carbon fibre composite panels is studied through experimental tests and numerical simulations. This study, aimed to evaluate the best process conditions and the mechanical behaviour of the joint itself, can be divided into few phases: the first one in which the static mechanical behaviour was investigated in order to evaluate the best process conditions (such as the best value of oil pressure of the riveting system) and the second one which had the purpose to determine the fatigue behaviour of the joint. Finally, a finite element method analysis of the riveting process was developed in order to compare the obtained results with the experimental ones. The joining process was simulated using a finite element method code specific for plastic deformation processes, namely DEFORM™, to predict the deformed shape and mechanical fastening mechanism. Results showed how this procedure can be a powerful tool to carry out a proper computer-aided process engineering. The experimental tests showed that the hybrid joint (metal/composite) has good mechanical characteristics both under static and fatigue loads.

scholarly journals A repairable carbon nanotube web-based electro-thermal heater and damage sensor for aerospace applications

2021 ◽  
pp. 1-11
Author(s):  
X. Yao ◽  
S.C. Hawkins ◽  
B.G. Falzon
Keyword(s):  
Carbon Nanotube ◽  
Carbon Fibre ◽  
Infrared Imaging ◽  
Impact Damage ◽  
Fibre Composite ◽  
Leading Edge ◽  
Cold Spot ◽  
Loss Of Function ◽  
Carbon Fibre Composite ◽  
Web Based

ABSTRACT We previously described an efficient, lightweight and flexible electro-thermal system, based on directly drawn carbon nanotube web (CNT web), as part of an icing protection system for carbon fibre reinforced polymer (CFRP) composite aircraft structures. The location of the heating elements on critical lifting surface leading edges or nacelle intake lips makes them particularly susceptible to impact damage, which may leave no visible mark. This makes it desirable to have both a mechanism for identifying the location of damage to the CNT structure (and by inference, potential damage to the underlying CFRP) and a process for restoring the CNT heater to full operation. With the CNT web acting as a sensor, impact damage is identified by an increase in electrical resistance and, particularly, by infrared imaging, which reveals a cold spot or zone depending upon the CNT web layup. Whereas a unidirectional CNT web layup exhibits a large increase in resistance and loss of a full width band of operation, a cross ply quasi-isotropic CNT web arrangement suffers only a small increase in resistance and a loss of function that is highly localised to the damaged area. A novel methodology, based on dispersed CNT in resin, is described for repairing and reconnecting the CNT structure and restoring functionality. A CNT web-based electro-thermal element was applied to the leading edge of a representative carbon-fibre composite wing section to demonstrate the flexibility of this system.

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