Tail-rotor vibration dampener system
AssigneeThe Boeing Company
InventorEric B. Gilbert
Life of this patent
Estimating the term…
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.
Claims20
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
- rotor blades to receive the output torque and rotate 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 to control 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 on the frequency.
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
- rotor blades to receive the output torque and rotate 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 to control a position of the open rotor assembly in relation to the fuselage;
- and
- an electrically activated linear actuator to control an overall length of the actuator unit 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 linear actuator to cancel the vibration emanating from the open rotor assembly based on the frequency.
Dependencies are inferred from the claim text.