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Solar-powered UAV is a lightweight aircraft with high aspect ratio, and its wing has significant aeroelastic effect, especially flutter. This kind of aircraft has the characteristics of large size and low stiffness. It is costly and difficult to realize to study wing flutter through wind tunnel test. Therefore, simulation calculation is the main means to analyze the flutter problem of this kind of aircraft. Aiming at the high aspect ratio wing of a solar UAV with wingspan of 40 meters, the finite element model of the wing was firstly treated by engineering. On this basis, the structural dynamics analysis and flutter calculation were carried out, and the flutter velocity under different pod arrangements on the wing was mainly calculated. The simulation results show that the flutter speed of the solar UAV wing is 26m/s, which meets the design requirements. Further analysis shows that the flutter speed of the UAV can be improved by increasing the length of the engine connecting rod, increasing the counterweight on the engine and changing the spanwise position of the pod on the wing.