AERO-THERMO-MECHANICAL CHARACTERISTICS OF SHAPE MEMORY ALLOY HYBRID COMPOSITE PANELS WITH GEOMETRIC IMPERFECTION
H., I., M., T. (2008). AERO-THERMO-MECHANICAL CHARACTERISTICS OF SHAPE MEMORY ALLOY HYBRID COMPOSITE PANELS WITH GEOMETRIC IMPERFECTION. EKB Journal Management System, 13(13th International Conference on Applied Mechanics and Mechanical Engineering.), 163-176. doi: 10.21608/amme.2008.39405
IBRAHIM H. H.; TAWFIK M.. "AERO-THERMO-MECHANICAL CHARACTERISTICS OF SHAPE MEMORY ALLOY HYBRID COMPOSITE PANELS WITH GEOMETRIC IMPERFECTION". EKB Journal Management System, 13, 13th International Conference on Applied Mechanics and Mechanical Engineering., 2008, 163-176. doi: 10.21608/amme.2008.39405
H., I., M., T. (2008). 'AERO-THERMO-MECHANICAL CHARACTERISTICS OF SHAPE MEMORY ALLOY HYBRID COMPOSITE PANELS WITH GEOMETRIC IMPERFECTION', EKB Journal Management System, 13(13th International Conference on Applied Mechanics and Mechanical Engineering.), pp. 163-176. doi: 10.21608/amme.2008.39405
H., I., M., T. AERO-THERMO-MECHANICAL CHARACTERISTICS OF SHAPE MEMORY ALLOY HYBRID COMPOSITE PANELS WITH GEOMETRIC IMPERFECTION. EKB Journal Management System, 2008; 13(13th International Conference on Applied Mechanics and Mechanical Engineering.): 163-176. doi: 10.21608/amme.2008.39405

AERO-THERMO-MECHANICAL CHARACTERISTICS OF SHAPE MEMORY ALLOY HYBRID COMPOSITE PANELS WITH GEOMETRIC IMPERFECTION

The International Conference on Applied Mechanics and Mechanical Engineering
Article 83, Volume 13, 13th International Conference on Applied Mechanics and Mechanical Engineering., May 2008, Page 163-176  XML PDF (388 K)
Document Type: Original Article
DOI: 10.21608/amme.2008.39405
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Authors
IBRAHIM H. H.1; TAWFIK M.2
1Assistant Professor, Space Division, National Authority for Remote Sensing and Space Sciences, Cairo, Egypt.
2Assistant Professor, Mechanical Department, British University in Egypt, Cairo, Egypt.
Abstract
ABSTRACT
A new nonlinear finite element model is presented for the static aero-thermal deflection
of a shape memory alloy (SMA) hybrid composite panel with initial geometric
imperfection and under the combined effect of thermal and aerodynamic loads. The
nonlinear governing equations are obtained using Marguerre curved plate theory and
the principle of virtual work. The effect of large deflection is included in the formulation
through the von Karman nonlinear strain-displacement relations. To account for the
temperature dependence of material properties, the thermal strain is stated as an
integral quantity of the thermal expansion coefficient with respect to temperature. The
aerodynamic pressure is modeled using the quasi-steady first-order piston theory. The
Newton-Raphson iteration method is employed to obtain the nonlinear aero-thermal
deflections, while an Eigen value problem is solved at each temperature and static
aerodynamic load to predict the free vibration frequencies about the deflected
equilibrium position. Finally, the nonlinear deflection and free vibration characteristics of
a SMA hybrid composite panel are presented, illustrating the effect of SMA fiber
embeddings, temperature rise, dynamic pressure, boundary conditions and an initial
geometric imperfection on the panel response.
Keywords
shape memory alloy; Fundamental Frequency; Aero-Thermal Buckling; Geometric Imperfection
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