Event Title
Composite Laminate Design for Improved Open-Hole Compression Strength Using Non-Standard Ply Angles and Customized Stacking Sequences Characterized By [D] Matrix
Faculty Mentor
Dr. Tahsin Khajah
Document Type
Oral Presentation
Date of Publication
April 2021
Abstract
The design of the composite materials in this study is used stacking sequences and ply angles. This research study is used non-standard ply angle designs and flipped angle designs to improve the open-hole compression strength of composite laminates with stiffness. Non-standard angle designs have the possibility to reduce the weight, less sensitivity to the hole, and better efficiency to the small load misalignment. Flipped angle designs improve the open-hole compression failure strength using the non-standard and standard ply angles by up to 33%. Stacking sequences of the composite laminates were optimized to reduce the ply thickness under in-plane uniaxial and multi-axial. This design is shifting from fiber fracture to shear fracture mechanisms for un-flipped angle and predicting Tr [D*] matrix from Classical Laminate Theory (CLT) which is characterized by [D] matrix.
Zoom Link
https://uttyler.zoom.us/j/93328029750?pwd=dFM0blRnRHVCNTVxTXljWFFEcVdKUT09 (passcode: lyceum)
Keywords
Non-standard angle, Flipped Angle, Open-hole compression, Stacking sequence
Persistent Identifier
http://hdl.handle.net/10950/3131
Composite Laminate Design for Improved Open-Hole Compression Strength Using Non-Standard Ply Angles and Customized Stacking Sequences Characterized By [D] Matrix
The design of the composite materials in this study is used stacking sequences and ply angles. This research study is used non-standard ply angle designs and flipped angle designs to improve the open-hole compression strength of composite laminates with stiffness. Non-standard angle designs have the possibility to reduce the weight, less sensitivity to the hole, and better efficiency to the small load misalignment. Flipped angle designs improve the open-hole compression failure strength using the non-standard and standard ply angles by up to 33%. Stacking sequences of the composite laminates were optimized to reduce the ply thickness under in-plane uniaxial and multi-axial. This design is shifting from fiber fracture to shear fracture mechanisms for un-flipped angle and predicting Tr [D*] matrix from Classical Laminate Theory (CLT) which is characterized by [D] matrix.