Aerodynamics and blade flutter intelligent simulation of propeller vehicle under different wing angle

Leilei Yu, Zongjie Cao, Shuai Yang

Abstract: In recent years, with the development of aerospace field, composite materials show its importance and particularity in many fields and have a wide range of application potential because of its light weight structure. The application of composite materials to UAV blades can reduce the structural weight and improve the impact resistance. The mechanical properties, damage performance and failure mechanism of laminate under high strain rate are the fundaments for high-speed impact mechanics analysis. In this paper, a kind of fiber composite blade is designed independently, and the optimal laying angle is determined. Fluent is selected as the CFD calculation software to carry out the fluid–solid coupling analysis of the composite fixed wing. By changing the wing angle (0°, 10°, 17°, 24°), the flutter performance of the fixed wing under the condition of 45 m/s velocity flow is studied. The results show that the laminated laminate designed in this paper has longer action time under impact load, better protection for structure and better effect of resisting impact, and the trend and inflection point of stress and deformation of fixed wing are similar. Flutter occurs, the stress on the lower side of the fixed wing is larger than that on the upper side, and the stress on the outside is larger than that on the inside, and with the increase of time, the stress gradually spreads to both sides along the direction of the fixed wing. There is no correlation between the stress and strain of the fixed blade, and there is a threshold for the wing angle. When the wing angle is 10°, the blade has the smallest strain and the strongest wind resistance.