In view of the actual demand in upgrading performance improvements for unmanned aerial vehicle blade, the 200 kg unmanned aerial vehicle rotor is used as the prototype model, and with the COMOSOL software, the characteristics of helicopter blades are simulated. The mathematical model of the blade lift is based on the blade element approach, to overcome aerodynamic loading headaches in the conventional rotor dynamics simulation analysis. The blade attack angle and lift, and the tip displacement against the total distance and the cycle variable pitch are obtained through the coupling relationship between the space rotation movement of the helicopter rotor blade and the elastic deformation, and the results are compared with those of the conventional numerical analysis. The accuracy of the simulation results is verified. According to the simulation results, specific suggestions for improvement of the blade angle, the blade leading edge stiffness etc. are made, that provides a reference for improving the design of the blade.

multi-body dynamics  /  rotor blade characteristics  /  helicopter