Abstract
This work investigates thermal aeroelastic tailoring of a laminated composite panel with a lamination parameter-based method. Equivalent membrane and bending coefficients of thermal expansions for symmetric laminated panel are derived and represented with lamination parameters using Classical Laminated Plate Theory. The relationship between thermal flutter behavior and lamination parameters is examined. The optimization process is split into two stages. In the first stage, lamination parameters and laminate thicknesses are as design variables to minimize the structure mass, subject to thermal flutter behavior and feasible region constraints of lamination parameters. In the second-stage, instead of using conventional genetic algorithm, the enhanced JAYA method is extended to search the laminate configuration to target the optimal lamination parameters. The effectiveness of the presented method is demonstrated through a thermal aeroelastic tailoring problem.
Highlights
IntroductionPanel thermal flutter is a self-excited oscillation phenomenon resulting from the interactions of the inertial force, elastic force, the aerodynamic pressure, and the induced temperature load due to supersonic airflow [1]
Three assumptions are usually adopted during thermal flutter analysis: (1) the temperature field is not affected by deformation of the structure; (2) the time scale of flutter dynamic response is much smaller than that of temperature change, so the temperature field can be regarded as a steady state during thermal flutter analysis; (3) when the temperature rise is not too high, the influence of temperature on material properties is ignored
The laminate thickness and Lamination parameters (LPs) are as design variables for weight reduction using
Summary
Panel thermal flutter is a self-excited oscillation phenomenon resulting from the interactions of the inertial force, elastic force, the aerodynamic pressure, and the induced temperature load due to supersonic airflow [1]. Mechanical stiffness softening can directly change the dynamic characteristics and usually reduce the thermal flutter boundary of the panel. Increasing attentions have been paid to thermal flutter investigation for laminated composite structures. Ganapathi and Touratier [2] presented an investigation of the effects of various temperature loading, laminate thickness, and boundary conditions on the thermal flutter behavior. Zhao and Cao [4] investigated the flutter characteristics of a laminated panel with aerodynamic, thermal, and acoustic loads. Chai et al [5] investigated the flutter and thermal buckling behavior of laminated shells with various boundary conditions. Thermal flutter characteristics of curvilinear fiber path variable stiffness composite has been paid attention recently [8–10]
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