Aerothermoelastic behaviors of curvilinear fiber composite panels based on the refined zig-zag theory

The aerothermoelastic characteristics of curved fiber composite laminated panels subjected to supersonic airflow are proposed. Based on the refined zig-zag theory, the refined zig-zag theory is adopted to describe the panel and the quasi-steady first-order piston theory is utilized for calculating the aerodynamic force. With considering uniformly distributed temperatures as thermal loads throughout the panel thickness, a finite element method is employed to solve the discretization equation of aerothermoelastic motion using the complex mode method. The validity of this aerothermoelastic model is substantiated through a meticulous comparison of computed results with existing solutions documented in the literature. The maximum error of the present critical flutter dynamic pressure of the curvilinear fiber composite laminates is 0.16% comparing with the literature. Furthermore, different plate theories are investigated to explore aerothermoelastic stability, including flat, critical buckling, and limit cycle oscillation for curvilinear fiber composite laminated panels. Detailed discussions are provided on how curvilinear fiber angle and temperature rise influence natural frequencies and flutter characteristics of composite laminates.