摘要
The effects of shape memory alloy( SMA) wires on the natural frequency,flutter boundary and amplitude of limit cycle oscillation( LCO) of a laminated composite panel are investigated. The classical plate theory as well as von-Karman strain-displacement relation are used to formulate the nonlinear dynamic model of the smart laminated panel. The aerodynamic loadings are simulated by the third order piston theory. The thermomechanical behavior of SMA wires is estimated according to one-dimensional Brinson SMA model. The effects of SMA wires temperature,pre-strain,volume fraction and orientation on flutter boundary and amplitude of LCO of the panel are analyzed in detail.
The effects of shape memory alloy( SMA) wires on the natural frequency,flutter boundary and amplitude of limit cycle oscillation( LCO) of a laminated composite panel are investigated. The classical plate theory as well as von-Karman strain-displacement relation are used to formulate the nonlinear dynamic model of the smart laminated panel. The aerodynamic loadings are simulated by the third order piston theory. The thermomechanical behavior of SMA wires is estimated according to one-dimensional Brinson SMA model. The effects of SMA wires temperature,pre-strain,volume fraction and orientation on flutter boundary and amplitude of LCO of the panel are analyzed in detail.
基金
Sponsored by the National Natural Science Foundation of China(Grant Nos.91216106 and 11472089)
