Abstract:

The mathematical model of a maneuvering rotor is derived. The dynamical characteristics of a rotor during acceleration and deceleration are studied. The influences of the gravity and balance parameters are also considered. The conclusions show that: (1)if the velocity and acceleration of the aircraft are changed, the amplitude response of the rotor is varied too; (2)the velocity and acceleration of the aircraft in the vertical direction affect the response of the rotor obviously; (3)when the aircraft runs in the way of a sine curve in the vertical plane the response curve is also periodic after one or two periods; (4)in most cases studied in this paper, the response curve, mainly the amplitude value, is influenced by the gravity and unbalance parameters; (5)the response is influenced largely by the amplitude and period of the sine curve when the aircraft maneuvers in the vertical plane. The curve trend may be much different when the initial rotating speed is lower before acceleration or higher before deceleration. The change of gravity affects the trends of the response obviously. The unbalance parameter has little influence. The conclusion can be used to diagnose the faults of the aircraft rotor on line.

Key words: maneuvering rotor, unbalance, aircraft, fault diagnosis, rotor dynamics