Aligned Carbon Nanotube Reinforcement of Aerospace Carbon Fiber Composites: Substructural Strength Evaluation for Aerostructure Applications

https://www.aiaa.org/ProceedingsDetail.aspx?id=5776

Bibliographic Details
Main Authors: Guzman de Villoria, Roberto (Contributor), Ydrefors, L. (Author), Hallander, P. (Author), Ishiguro, Kyoko (Contributor), Nordin, P. (Author), Wardle, Brian L. (Contributor)
Other Authors: Massachusetts Institute of Technology. Department of Aeronautics and Astronautics (Contributor)
Format: Article
Language:English
Published: American Institute of Aeronautics and Astronautics, 2012-06-27T20:19:20Z.
Subjects:
Online Access:Get fulltext
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100 1 0 |a Guzman de Villoria, Roberto  |e author 
100 1 0 |a Massachusetts Institute of Technology. Department of Aeronautics and Astronautics  |e contributor 
100 1 0 |a Wardle, Brian L.  |e contributor 
100 1 0 |a Guzman de Villoria, Roberto  |e contributor 
100 1 0 |a Wardle, Brian L.  |e contributor 
100 1 0 |a Ishiguro, Kyoko  |e contributor 
700 1 0 |a Ydrefors, L.  |e author 
700 1 0 |a Hallander, P.  |e author 
700 1 0 |a Ishiguro, Kyoko  |e author 
700 1 0 |a Nordin, P.  |e author 
700 1 0 |a Wardle, Brian L.  |e author 
245 0 0 |a Aligned Carbon Nanotube Reinforcement of Aerospace Carbon Fiber Composites: Substructural Strength Evaluation for Aerostructure Applications 
260 |b American Institute of Aeronautics and Astronautics,   |c 2012-06-27T20:19:20Z. 
856 |z Get fulltext  |u http://hdl.handle.net/1721.1/71233 
520 |a https://www.aiaa.org/ProceedingsDetail.aspx?id=5776 
520 |a Vertically aligned carbon nanotubes (VACNTs) are placed between all plies in an aerospace carbon fiber reinforced plastic laminate (unidirectional plies, [(0/90/±45)2]s) to reinforce the interlaminar region in the z-direction. Significant improvement in Mode I and II interlaminar toughness have been observed previously. In this work, several substructural in-plane strength tests relevant to aerostructures were undertaken: bolt/tension-bearing, open hole compression, and L-shape laminate bending. Improvements are observed for the nanostitched samples: critical bearing strength by 30%, open-hole compression ultimate strength by 10%, and L-shape laminate energy (via increased deflection) of 40%. The mechanism of reinforcement is not compliant interlayer creation, but rather is a fiberstitching mechanism, as no increase in interlayer thickness occurs with the nanostitches. Unlike traditional (large-fiber/tow/pin) stitching or z-pinning techniques that damage inplane fibers and reduce laminate in-plane strengths, the nano-scale CNT-based 'stitches' improve in-plane strength, demonstrating the potential of such an architecture for aerospace structural applications. The quality of VACNT transfer to the prepreg laminates has not been optimized and therefore the noted enhancement to strength may be considered conservative. Ongoing work has been undertaken to both improve VACNT transfer and expand the data set. 
520 |a Massachusetts Institute of Technology (Nano-Engineered Composite aerospace STructures (NECST) Consortium) 
546 |a en_US 
655 7 |a Article 
773 |t 53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 2012