Title: Design of Variable Stiffness Cylinder with Holes Under Bending for Maximum Buckling Load Using Lamination Parameters

Authors: Mazen A. Albazzan, Brian F. Tatting, Ramy Harik, Zafer Gürdal, Adriana W. Blom-Schieber, Mostafa Rassaian, and Steven Wanthal

DOI: 10.33599/nasampe/s.19.1378

Abstract: Fiber-reinforced composite laminates in the aerospace industry are primarily manufactured using conventional constant stiffness laminates with constant fiber orientation angles. Research over the last decade has shown that substantial gains may be achieved by using nonconventional variable stiffness laminates with steered fiber orientation angles. To demonstrate these benefits for fuselage structures, a composite cylindrical shell with holes under bending is designed for maximum buckling load. A two-step optimization framework is utilized to obtain optimal steered fiber orientation angle designs while reducing the optimization complexity. Lamination parameters are used as intermediate design variables at the first optimization step to achieve a convex optimum laminate stiffness design. A design-manufacturing mesh is introduced to model the spatial stiffness variation of the cylinder in ABAQUS®. Circumferential and longitudinal stiffness variations are considered globally and locally around the holes to study their effect on the buckling load. A well-discretized optimum lamination parameter distribution alters the local buckling modes and shows an 83% increase in linear buckling load of the variable stiffness cylinder compared to a quasi-isotropic design. The optimal fiber orientation angle distributions matching the optimum stiffness properties are then retrieved at the second optimization step using a genetic algorithm, while satisfying laminate design guidelines.

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Conference: SAMPE 2019 - Charlotte, NC

Publication Date: 2019/05/20

SKU: TP19--1378

Pages: 18

Price: FREE