Modeling and computational simulation for supersonic flutter prediction of polymer/GNP/fiber laminated composite joined conical-conical shells |
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| Institution: | 1. Data Science & Computational Intelligence Research Group, Universitas Sumatera Utara, Medan, Indonesia;2. DS & CI Research Group, Universitas Medan Area, Medan, Indonesia;3. Faculty of Engineering, Universitas Medan Area, Medan, Indonesia;4. Department of Mechanical Engineering, Khomeinishahr Branch, Islamic Azad University, Khomeinishahr/Isfahan, Iran;5. Department of Mechanical Engineering, Abadeh Branch, Islamic Azad University, Abadeh, Iran;6. Department of Mathematics, Al-Aflaj College of Science and Humanities Studies, Prince Sattam bin Abdulaziz University, Al-Aflaj 710-11912, Saudi Arabia;7. Department of Mathematics, Suez Faculty of Science, Suez University, Egypt;8. Reserch Institute of Mechanical Engineering, Department of Vibration Testing and Equipment Condition Monitoring, South Ural State University, Lenin Prospect 76, Chelyabinsk 454080, Russian Federation;9. Faculty of Science and Natural Resources, Universiti Malaysia Sabah, 88400 Kota Kinabalu, Sabah, Malaysia;10. Department of Chemical Engineering, Ming Chi University of Technology, New Taipei City, Taiwan |
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| Abstract: | This paper is presented to study the supersonic flutter characteristics of laminated joined conical-conical shells made of epoxy as the matrix and fibers and graphene nanoplatelets (GNPs) as the reinforcements. The mathematical modeling of the shell and the aerodynamic pressure are performed sequentially using the first-order shear deformation theory (FSDT) and the supersonic piston theory incorporating the aerodynamic damping coefficient. The effective elasticity and shear modulus, Poisson’s ratios, and density are estimated using the rule of mixture, Halpin-Tsai model, and micromechanical relations. The governing equations and associated boundary and compatibility conditions are derived utilizing Hamilton’s principle and are solved in the circumferential direction and numerically in the meridional direction via the differential quadrature method (DQM). The natural frequencies and mode shapes are obtained, and the influences of various parameters on the flutter boundaries are examined including the geometrical characteristics of the shell segments, boundary conditions, circumferential wave number, and weight fractions of the GNPs and fibers. It is concluded that by increasing the weight fractions of the fibers and the GNPs, the natural frequencies grow and the aeroelastic stability improves. |
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| Keywords: | Flutter Aeroelastic stability Joined conical-conical shells Graphene nanoplatelets Three-phase material |
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