Stability Analysis of Coupled Rotor/Fuselage System of the Bearingless Rotor Helicopter on the Ship

摘要

The dynamic analysis model of the bearingless rotor helicopter, which includes the large deformation of the blade and the multiple-load-path of the blade root, is proposed. The blade model is analyzed by the finite element method, and each element contains 15 degrees of the freedom. Consequently, stability analysis of the coupled rotor/fuselage system of the bearingless rotor helicopter have been made, the result shows that the difference between analysis and experiment date of ground resonance is negligible, then the validity of this model has been proved. The ship resonance is analyzed with a 5 degrees of freedom of the ship model. The result shows that the nature frequency of fuselage and rotor has a little difference between on deck and on ground, when the linear stiffness of landing gear is considered. In addition, the damping of the regressing lag mode has a little rise.