中文摘要：

采用气动结构松耦合技术研究了飞翼布局无人机的方向舵嗡鸣响应及副翼、升降舵及襟翼的振动时域响应。首先建立较为详细的飞翼布局无人机的结构模型和气动模型,基于雷诺平均的N-S方程建立流体控制方程和结构动力学方程的耦合求解技术;气动计算中的网格变形技术采用非结构动网格,其中动网格更新技术采用弹簧近似光滑和局部网格重构组合方法;基于LU-SGS子迭代的时间推进技术和HLLEW的空间离散方法进行气动数据的计算,湍流模型采用SST湍流模型,采用三维插值技术进行气动与结构耦合界面结构变形位移与气动力载荷之间数据的传递;在方向舵转轴端部设置方向舵偏转运动的约束方程;基于提出的气动结构松耦合方法计算飞翼无人机方向舵偏转引起的方向舵嗡鸣和全机的方向舵、副翼、升降舵及襟翼振动的时域响应;并研究了旋转角频率参数变化对飞翼无人机全机振动响应特性的影响。研究表明旋转角频率对方向舵的偏转响应和副翼、升降舵及襟翼的振动响应频率影响较大。

英文摘要：

Transonic rudder buzz responses and aileron, elevator, flap vibration time responses, are presen- ted by adopting the CFD/CSD loosely coupled method for a tailless flying wing UAV. The RANS N-S e- quations and finite element methods are established based on the detailed aerodynamic and structural mod- el, in which the aerodynamic meshes use the unstructured dynamic meshes based on the combination of the spring-based smoothing and local re-meshing methods. The LU-SGS iteration and HLLEW space discrete methods based on the SST turbulence model are used to calculate the aerodynamic force. The interfaces be- tween the structural and aerodynamic model are built with an exact match surface where load transferring is performed based on 3D interpolation. The constraints of the rudder motions are fixed at the end of the flying wing UAV structural model, and the structural geometric nonlinearities are also considered in the high aspect ratio flying wing UAV. Based on the presented buzz aerodynamic structural coupled method, the flying wing UAV transonic buzz responses and aileron, elevator, flap vibration time responses induced by the rudder motion are studied; the effects of rotating angular frequency on the vibration time responses are also given.