Analysis of aeroelastic vibro-acoustic response for heated panel of hypersonic vehicle

Hypersonic vehicle panel in combination with unsteady aerodynamic pressure, thermal loading and acoustic loading exhibits a complex nonlinear aeroelastic vibration response. The panel shows a complex snap-through response, especially in the vicinity of the critical flutter dynamic pressure. Based on von Karman large deformation plate theory, the equations of motion under the interaction of aerodynamic pressure and thermal-acoustic loading are established. In addition, the buckling deformation and thermal buckling instability of a heated panel in supersonic flow is analyzed. According to the potential well theory, the mechanism of snap-through phenomenon is explored. By defining zero-cross frequency, a quantitative classification method for snap-through motion is proposed. Furthermore, the critical sound pressure level under different dynamic pressure and temperature conditions is calculated. The results show that when the dynamic pressure is smaller than the critical flutter dynamic pressure, the depth of the potential well first increases and then decreases with dynamic pressure increasing. And the depth of potential well increases with the increase of temperature rise.