Time domain aero-thermo-elastic instability of two-dimensional non-linear curved panels with the effect of in-plane load considered

Abstract

This study presents aero-thermo-elastic Instability of two-dimensional Non-linear Curved Panels. Aero-thermo-elasticity plays an important role in the design and optimization of supersonic aircrafts. Furthermore, the transient and nonlinear effects of the thermal and aerodynamic environment encompassing a curved surface cannot be ignored. Accordingly, a homogenous curved plate with a high length-to-width ratio and simply-supported boundary conditions is assumed. The effect of large deflection is included in the equations through von Kármán non-linear strain-displacement relations. The thermal load is assumed to be a steady-state temperature non-uniform distribution. Structural properties such as modulus of elasticity and thermal expansion coefficient are assumed to be temperature-dependent. The novelty is incorporating first-and third-order piston theory for the non-linear curved panel flutter analysis under the effects of inplane and thermal loads. Hamilton's principle is used and partial differential equations are derived. The semi-analytical weighted residual method for the nonlinear curved panel is utilized. The fourth-and fifth-order Runge-Kutta iterative method are deployed to obtain the non-linear aero-thermo-mechanical deflections. Non-linear frequency analysis of cambered panel with the combined effects of aerodynamics, thermal and in-plane loads is investigated for the first time. The increase in panel curvature leads to a complicated behavior in the non-linear structural frequency variations. With increasing in-plane compressive load, complicated oscillating behavior is observed. More critical instability boundary for cambered panel is detected through the use of third-order piston theory. In addition, with an increase in panel curvature from 0 to 3, the panel displacement increases and for higher camber ratio, it decreases. Keywords Panel flutter • In-plane load • Thermal effects • First-order piston theory • Third-order piston theory • 2D panel • Time domain

Research on Panel Flutter Considering the Effect of Convective Active Cooling

“…The effect of structural damping is weak when the aerodynamic damping is large, while the opposite results are obtained when the aerodynamic damping is small. Hamid and Mohammad [11] presented the nonlinear vibrational frequency analysis of a curved panel under the effects of in-plane compressive and tensile loads, carried out for the first time in the time domain. The first-and third-order piston theories were incorporated for the nonlinear curved panel flutter analysis under the effects of in-plane and thermal loads.…”