Repository logo

Mechanical Properties of Aerospace Composite Parts Made from Stitched Multilayer 3D Carbon Fibre Preforms

dc.contributor.authorAudette, Scott
dc.contributor.supervisorRobitaille, François
dc.date.accessioned2014-10-03T11:57:57Z
dc.date.available2015-03-30T08:00:07Z
dc.date.created2014
dc.date.issued2014
dc.degree.disciplineGénie / Engineering
dc.degree.levelmasters
dc.degree.nameMASc
dc.description.abstractProducing composite parts using low-cost processes such as resin transfer moulding (RTM) has received much interest in the aerospace industry. RTM manufactured components require near net shape preforms which closely fit mould cavities. To reduce labour costs associated with composite production, automated preforming processes must be utilized. However, obtaining reproducible high quality preforms is required for manufacturing consistent high quality parts. Stitched multilayer 3D non crimp fabric preforms are well suited for automation and an investigation into quality and performance of components manufactured from these preforms is required. This thesis provides an initial evaluation of quality and mechanical properties of components made from stitched multilayer 3D non crimp fabric preforms using RTM. Similar sized flat plates of varying fibre volume fractions were manufactured to evaluate flexural modulus and strength, short beam shear strength and drop weight impact resistance of the material. Also, integral reinforced panels (IRPs) featuring a reinforcing section joined to a flat plate of varying laminating sequences were manufactured to evaluate debonding strength between sections. Optical microscopy was performed on component samples to determine quality based on void content and was found to be within acceptable limits for production composites. Flexural moduli were found to be comparable with theoretical expected values, however flexural strength was limited by the presence of transverse stitches. Short beam shear strength results showed high consistency between specimens, however were lower than comparable values found in literature. Impact specimens showed consistency among specimens, with greater damage resistance than comparable values found in literature. Determining debonding strength proved difficult as different failure modes were observed between IRPs, however, initial baseline values were acquired.
dc.embargo.terms2015-03-30 00:00:00
dc.faculty.departmentGénie mécanique / Mechanical Engineering
dc.identifier.urihttp://hdl.handle.net/10393/31691
dc.identifier.urihttp://dx.doi.org/10.20381/ruor-4277
dc.language.isoen
dc.publisherUniversité d'Ottawa / University of Ottawa
dc.subjectPMC
dc.subjectCarbon Fibre
dc.subjectMechanical Properties
dc.subjectMechanical Testing
dc.subjectRTM
dc.subjectStitched Multilayer
dc.subjectNear Net Shape Preforms
dc.subject3D Preforms
dc.titleMechanical Properties of Aerospace Composite Parts Made from Stitched Multilayer 3D Carbon Fibre Preforms
dc.typeThesis
thesis.degree.disciplineGénie / Engineering
thesis.degree.levelMasters
thesis.degree.nameMASc
uottawa.departmentGénie mécanique / Mechanical Engineering

Files

Original bundle

Now showing 1 - 1 of 1
Loading...
Thumbnail ImageThumbnail Image
Name:
Audette_Scott_2014_thesis.pdf
Size:
295.06 MB
Format:
Adobe Portable Document Format

License bundle

Now showing 1 - 1 of 1
Loading...
Thumbnail ImageThumbnail Image
Name:
license.txt
Size:
4.07 KB
Format:
Item-specific license agreed upon to submission
Description: