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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。
Under the combination of unsteady aerodynamic forces, thermal loads and noise loads, hypersonic aircraft sills will exhibit complex nonlinear aeroelastic vibration response, especially near the critical flutter dynamic pressure As well as the sound load, the wall shows a complex jump movement. Based on the theory of von Karman large deformation plate, the equations of wall motion under thermo-acoustic load and aerodynamic force were established. The buckling deformation and thermal buckling stability of the heated wall in supersonic airflow were analyzed. By using the concept of potential well, Mechanism of plate jumping motion. By defining “zero crossing frequency”, the quantitative classification of jump movement is given, and the critical sound pressure level corresponding to the jump movement of the siding under different temperature rise and dynamic pressure conditions is calculated. The results show that with the increase of dynamic pressure, the depth of potential well in heated wall plate first increases and then decreases, and the trap depth of heated wall plate increases with the increase of temperature before flutter critical dynamic pressure.