Online Store: CAMX 2017 - Orlando, FL - December 11-14, 2017
Main Storefront


Item Options
Sign in for your pricing!
Price: $28.00
Quantity: *



Abstract: Corrugated structures are noted for their exhibition of extreme anisotropic stiffness properties deeming them particularly useful in aerospace applications. This paper presents the methodology of analytical design, manufacturing, and comparison of corrugated panel structures utilizing different composite materials to determine their mechanical properties for use in secondary aircraft structures. The proposed methodology and design optimization process to be analyzed for these sort of corrugated composite materials is for an aircraft floor and associated supports in the fuselage, where large distributed loads must be managed. Traditional metallic alloy construction proves to be both heavy, bulky and significantly less strong than composite counterparts within the fuselage. To do this, the goal was to design optimal corrugation geometry using theoretical analysis and to verify this geometry with multiple different composite materials. Panel samples were prepared with single and double cell trapezoidal corrugated layers. These panels were then tested in axial compression loading to not only confirm the geometry of the corrugation designed based on theoretical analysis but to analyze how both the number of cell corrugations and material selection varied their mechanical properties. Once these samples had been tested individually, the corrugation design was then integrated into a larger, more complex composite structure similar to that of the structural component of an aircraft fuselage floor. The hypothesized cause of material failure for this applied structure would be failure at the joints, specifically in the bonding of multiple corrugated panels of distinct orientations.  
To combat this stress concentration at the conjunction, the composite panel joint design was optimized through the investigation of several manufacturing techniques and bonding processes. It is shown that corrugation design methodology of the aircraft structure panel outlined in this paper significantly increases the compressive strength and stiffness of the fiber reinforced composites.    

Authors: Isaac Blundell, Riley Hilliker, Jalen Mano, Dr. Eltahry Elghandour, Dr. Faysal Kolkailah 


Conference: CAMX 2017 –Orlando


SKU/Code: TP17-0102


Pages: 14


Platinum Corporate Partners

Find Us

21680 Gateway Center Drive
Suite 300
Diamond Bar, CA 91765-2454

P: +1.626.521.9460