Abstract
As a basic component of engineering fields such as aeronautics, astronautics and shipbuilding, panel structure has been widely used in engineering and scientific research. It is of great theoretical and practical significance to study the vibration of panels. The panel flutter problem has caused widely concerned by researchers at home and abroad during to the emergence of high-speed aircrafts. With regard to the eigenvalue problem of rectangular panels, it is generally believed that it is difficult to obtain a closed form eigen solution in the case of an adjacent boundaries clamped-supported or a free boundary that cannot be decoupled. Aiming at the problem, this paper studies the two-dimensional symmetric orthogonal laminated plate structure in the hypersonic flow in the thermal environment, and combines the first-order piston aerodynamic theory to study a high-precision separation variable method. Through this method, analytical solution to the closed form of the thermal flutter problem of rectangular panels can be obtained under any homogeneous boundary conditions.
Highlights
Panel flutter is one kind of typical self-excited vibration in aero-elastics that can cause fatigue damage to the structure
Analytical solution to the closed form of the thermal flutter problem of rectangular panels can be obtained under any homogeneous boundary conditions
This paper studies a high-precision separation variable method based on two-dimensional symmetric orthogonal laminates, and obtains the exact solution of the two-dimensional panel thermal flutter problem under various homogeneous boundaries (SS, GG, CC, FF, GS, SG, SC, SF, GC, CG, GF and CF)
Summary
Panel flutter is one kind of typical self-excited vibration in aero-elastics that can cause fatigue damage to the structure. This phenomenon was first observed in 1940’s [1], and was clearly observed in experiments in 1950’s [2], Mei [3] gave a summary of which before 1999. Due to the increase of the Mach number, the aerodynamic thermal effect is not negligible. This paper studies a high-precision separation variable method based on two-dimensional symmetric orthogonal laminates, and obtains the exact solution of the two-dimensional panel thermal flutter problem under various homogeneous boundaries (SS, GG, CC, FF, GS, SG, SC, SF, GC, CG, GF and CF). The research work on the eigenvalue problem of two-dimensional panel flutter is summarized
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