The coupled rotor/fuselage system was developed using multibody dynamics approach. The undercarriage of helicopter comprised the oleo and tyre as a nonlinear system. The ship had the roll and pitch motion in the form of harmonic oscillation. Under different rotor speeds and excited frequencies
the response and dynamic stability of the rotor/fuselage system had been investigated. The result shows that the fuselage and the rotor oscillations may generate limit cycle oscillations under the excitement of ship. When the rotor oscillation is equal to the excited frequency of ship
the response of regressing lag will bring about limit cycle oscillations
and the center of gravity of rotor will shift from the hub
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Related Author
ZHANG Wei
WANG Fei
ZHAO Qijun
王亮权
史勇杰
徐国华
计宏伟
赵洪
Related Institution
National Laboratory of Science and Technology on Rotorcraft Aeromechanics, Nanjing University of Aeronautics and Astronautics
China Helicopter Research and Development Institute, Aviation Industry Corporation of China, Limited
南京航空航天大学 直升机旋翼动力学国家级重点实验室
National Key Laboratory of Science and Technology on Rotorcraft Aeromechanics, College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics
School of Naval Architecture and Ocean Engineering, Jiangsu University of Science and Technology