Abstract: The driving structure of a bionic flapping-wing aircraft is designed,and a space rocker-type driving mechanism and a wing torsion mechanism are proposed to realize the 0-shaped spatial trajectory in the process of wing flapping.For the spatial "0" movement of the wing,a pneumatic analysis model of the bionic aircraft is established.The dynamic mesh and the unsteady value calculation method are used to analyze the lift-resistance characteristics at different phases during the flapping process.The aerodynamic efficiency under different parameters is obtained by comparing the air dynamic efficiency and the flow field,which provides a reference for the design of the bionic flapping-wing aircraft and the selection of the flutter mode. The rationality of the structure design is verified by the aerodynamic measurement experiment,bench attitude calibration and outfield flight test.