Finite Element Analysis For A Test Bench Of Rotor Wing System

In the development and production of helicopter, rotor wing system is in a vital position. The application of new technique, new material, and new process concentrate on at first the rotor wing system. High risk factor on technology and economy is included in the development of rotor wing system. Rely on the rotor wing system, helicopter can get up and down vertically, hang on and free to fly in the direction.Aero dynamical characteristic of rotor wing is vital in the performance and flight of helicopter. Rotor wing is also main source of vibration and noise. Malfunction of rotor wing cause a major part of helicopter accidents. For above reasons, it is needed for guaranteeing quality of rotor wing. This experimental bench for dynamical equilibrium test of rotor wing system is a kind of method extensively used both at home and abroad recently. It is mainly used to experimental investigation of pneumatic, dynamics, flight dynamics of rotor wing. By test, it can guarantee dynamical equilibrium, quality of the wing group, and flight of helicopter.This dissertation is mainly about force and deforming, natural frequency of test bench. The force and deforming is caused by external force and temperature environment. The dissertation analyzed the possible breakage on the theory basis. By the finite element method, it got data about force and deforming, natural frequency of test bench. It has meanings both in theory and realistic for development of test bench.