高超声速飞行器受热壁板的气动弹性声振分析

高超声速飞行器壁板在非定常气动力、热载荷和噪声载荷构成的多物理场联合作用下，将表现出复杂的非线性气动弹性声振响应，特别是在颤振临界动压附近，受热载荷以及声载荷作用，壁板表现出复杂的跳变运动。基于von Karman大变形板理论，建立了热-声载荷和气动力共同作用下的壁板运动方程，分析了超声速气流中受热壁板的屈曲变形及热屈曲稳定性，借助势阱概念初步分析了壁板跳变运动产生的机理。通过定义“穿零频次”给出了跳变运动定量的分类方法，并计算得到不同温升和动压情况下，壁板发生跳变运动所对应的临界声压级。结果表明：在颤振临界动压之前，随着动压的增加，受热壁板势阱的深度先增大后减小，且受热壁板的势阱深度随着温升的增加而增大。

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.