The Effect of Viscoelasticity on the Life Expectancy of Light Composite Aircraft
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In modern aircraft, polymer matrix composites (PMC) are becoming more prevalent in both primary and secondary structures due to their high strength and stiffness to weight ratios. The scope of this thesis is to predict the service life of the Diamond DA-20 Katana based on the viscoelastic properties of the MSG L285/H287 epoxy matrix. The prediction methodology is applied to the composite wing spar because the spar bears the majority of the load during flight. The methodology requires the experimental characterization of the epoxy matrix using the time-temperature superposition principle. The results were then applied to the spar to determine its long term response using the Classical Lamination Theory applied to complex geometries. Failure was determined based on the Tsai-Hill and maximum stain failure theory or if the compressive flange buckles under the load.
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Copyright © 2015 the author(s). Theses may be used for non-commercial research, educational, or related academic purposes only. Such uses include personal study, research, scholarship, and teaching. Theses may only be shared by linking to Carleton University Institutional Repository and no part may be used without proper attribution to the author. No part may be used for commercial purposes directly or indirectly via a for-profit platform; no adaptation or derivative works are permitted without consent from the copyright owner.
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goudie-theeffectofvisoelaticityonthelifeexpectancy.pdf | 2023-05-04 | Public | Download |