论文部分内容阅读
采用数值模拟方法研究了大后掠三角翼前缘涡破裂诱导的垂尾抖振问题,分析了大迎角条件下的垂尾抖振特性。采用Navier-Stokes方程求解非定常气动力、耦合结构动力学方程,建立了气动弹性方程,在时域内采用松耦合方式推进以得到垂尾结构响应。研究结果表明:涡破裂流的脉动频带覆盖了垂尾扭转模态的固有频率,诱发了垂尾抖振现象;与传统的颤振频域响应特性不同,垂尾抖振响应的各阶位移与加速度响应主频均位于各阶结构模态固有频率附近。此外,弯曲与扭转响应存在耦合效应,且耦合作用的频率与提取的垂尾表面气动载荷脉动频率一致。垂尾的位移响应由一阶弯曲模态主导,振幅不大;加速度响应主要由扭转模态产生,量级较大,使结构持续遭受严重的附加惯性载荷作用。
The numerical simulation is used to study the chattering of vertical tail induced by the vortex rupture of the large swept delta wing, and the characteristics of the tail chattering at high angles of attack are analyzed. The Navier-Stokes equations are used to solve the unsteady aerodynamic forces and coupled structural dynamics equations. The aeroelastic equations are established, and the response of the vertical tail structures is obtained by the loose coupling method in the time domain. The results show that the pulsation frequency band of vortex rupture flow covers the natural frequency of torsional torsion mode and induces the phenomenon of vertical tail chattering. Different from the traditional chatter frequency response characteristics, The acceleration response frequency is located in the vicinity of the natural frequency of each mode structure. In addition, there is a coupling effect between bending and torsional response, and the coupling frequency is consistent with the frequency of aerodynamic loading pulsation on the extracted vertical surface. The displacement response of the tail is dominated by the first-order bending mode, and the amplitude is not large. The acceleration response is mainly produced by the torsional mode, and the magnitude is larger, so that the structure continues to suffer severe additional inertial load.