Transonic rudder buzz responses and aileron, elevator, flap vibration time responses, are presented by adopting the CFD/CSD loosely coupled method for a tailless flying wing UAV. The RANS NS equations and finite element methods are established based on the detailed aerodynamic and structural model, 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 between 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.