Abstract: The general differential equations of motion of an unbalance flexible rotor system with multi-rigid-disk, multi-lumped-mass and multi-bearing are developed by using Lagrange’s equation during any maneuvering flight which include three translational and three rotational components of the motion of the aircraft. The influences of different maneuvering flights on the dynamic characteristics of a rotor system are numerically studied in a double-disk cantilever flexible rotor system. It is shown that the maneuvering flight makes the center of motion orbit of the rotor system greatly shift and the rotor’s vibration significantly increases, which may result in the particle impact between the rotor and the stator. The influence of the maneuvering flight on the dynamic characteristics of a rotor system must be considered in the design of aeroengine’s rotor system.

Key words: rotor dynamics, maneuvering flight, flexible rotor, base motion