Tail-rotor vibration dampener system
AssigneeThe Boeing Company
InventorEric B. Gilbert
Life of this patent
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Abstract
A tail-rotor vibration dampener system for an aircraft is provided. The system includes a fuselage and an open rotor assembly including a powerplant and a set of rotor blades. The system further includes at least one actuator unit connecting the open rotor assembly to the fuselage. The actuator unit includes a hydraulic actuator controlling a position of the open rotor assembly in relation to the fuselage and a dampening device operable to cancel a vibration emanating from the open rotor assembly. The system further includes a computerized vibration dampening controller, including programming to determine a frequency of the vibration emanating from the open rotor assembly and control the dampening device to cancel the vibration emanating from the open rotor assembly based upon the frequency.
Claims10
A tail-rotor vibration dampener system for an aircraft, the system comprising:
- a fuselage;
- an open rotor assembly including:
- a powerplant operable to provide an output torque;
- and
- a set of rotor blades receiving the output torque and concentrically rotating about a longitudinal axis of the open rotor assembly;
- at least one actuator unit connecting the open rotor assembly to the fuselage, the actuator unit including:
- a hydraulic actuator controlling a position of the open rotor assembly in relation to the fuselage;
- and
- a dampening device operable to cancel a vibration emanating from the open rotor assembly;
- and
- a computerized vibration dampening controller, including programming to:
- determine a frequency of the vibration emanating from the open rotor assembly;
- and
- control the dampening device to cancel the vibration emanating from the open rotor assembly based upon the frequency, wherein the dampening device includes an electrically activated hydraulic solenoid operable to create canceling vibrations within hydraulic fluid of the hydraulic actuator and the canceling vibrations are controlled to the frequency of the vibration emanating from the open rotor assembly and to an opposite phase of the vibration emanating from the open rotor assembly.
A tail-rotor vibration dampener system for an aircraft, the system comprising:
- a fuselage;
- an open rotor assembly including:
- a powerplant operable to provide an output torque;
- and
- a set of rotor blades receiving the output torque and concentrically rotating about a longitudinal axis of the open rotor assembly;
- a sensor operable to monitor a vibration emanating from the open rotor assembly;
- at least one actuator unit connecting the open rotor assembly to the fuselage, the actuator unit including:
- a hydraulic actuator controlling a position of the open rotor assembly in relation to the fuselage;
- and
- an electrically activated hydraulic solenoid creating a canceling vibration within hydraulic fluid of the hydraulic actuator and operable to cancel the vibration emanating from the open rotor assembly;
- and
- a computerized vibration dampening controller, including programming to:
- determine a frequency of the vibration emanating from the open rotor assembly;
- and
- control the electrically activated hydraulic solenoid to cancel the vibration emanating from the open rotor assembly based upon the frequency, wherein the canceling vibrations are controlled to the frequency of the vibration emanating from the open rotor assembly and to an opposite phase of the vibration emanating from the open rotor assembly.
Dependencies are inferred from the claim text.