公开(公告)号：US20190009898A1

公开(公告)日：2019-01-10

申请号：US15645110

申请日：2017-07-10

Applicant: Bell Helicopter Textron Inc.

Inventor： Jeffrey M. Bosworth ,  Kyle T. Cravener

IPC: B64C27/605 ,  B64C27/72

CPC classification number: B64C27/605 ,  B64C27/72 ,  B64C2027/7294

Abstract: A pitch horn assembly for an aircraft including a blade attachment member having a first end, a second end configured to be coupled to a rotor blade; and a blade attachment axis extending between the first end and the second end of the blade attachment member; a moveable arm configured to be coupled to the blade attachment member at a pitch horn axis, the moveable arm having a first end configured to be coupled to a pitch link; a second end; and a moveable arm axis extending between the first end and the second end of the moveable arm; an extendable member configured to be coupled to the blade attachment member and the moveable arm of the pitch horn, wherein the extendable member moves the moveable arm about the pitch horn axis. An embodiment provides a method of adjusting a pitch-flap coupling in an aircraft.

公开(公告)号：US10343772B2

公开(公告)日：2019-07-09

申请号：US15645110

申请日：2017-07-10

Applicant: Bell Helicopter Textron Inc.

Inventor： Jeffrey M. Bosworth ,  Kyle T. Cravener

IPC: B64C27/605 ,  B64C27/72

Abstract: A pitch horn assembly for an aircraft including a blade attachment member having a first end, a second end configured to be coupled to a rotor blade; and a blade attachment axis extending between the first end and the second end of the blade attachment member; a moveable arm configured to be coupled to the blade attachment member at a pitch horn axis, the moveable arm having a first end configured to be coupled to a pitch link; a second end; and a moveable arm axis extending between the first end and the second end of the moveable arm; an extendable member configured to be coupled to the blade attachment member and the moveable arm of the pitch horn, wherein the extendable member moves the moveable arm about the pitch horn axis. An embodiment provides a method of adjusting a pitch-flap coupling in an aircraft.

公开(公告)号：US20200347903A1

公开(公告)日：2020-11-05

申请号：US16399458

申请日：2019-04-30

Applicant: Bell Helicopter Textron Inc.

Inventor： Peter Quinn Romano ,  Michael S. Seifert ,  Jeffrey M. Bosworth

IPC: F16F7/10 ,  B64C17/00

Abstract: An aircraft comprises an aircraft component, a sensor, and a multiple frequency vibration absorber (absorber). The sensor is operable to detect a frequency of a vibration of the aircraft component. The absorber is coupled to the aircraft component and configured to absorb the vibration. The absorber comprises a beam element, a fluidic flexible matrix composite (FFMC) tube, a valve, and a controller. The beam element is attached to the aircraft component. The fluidic flexible matrix composite (FFMC) tube is coupled to the beam element and is operable to absorb the vibration based on a stiffness of the FFMC tube. The valve is fluidically coupled to the FFMC tube and is to control the stiffness of the FFMC tube based on regulating a flow of a liquid through the FFMC tube. The controller can actively control absorption of the vibration via the FFMC tube based on opening and/or closing the valve.

公开(公告)号：US20180339770A1

公开(公告)日：2018-11-29

申请号：US15607001

申请日：2017-05-26

Applicant: Bell Helicopter Textron Inc.

Inventor： John E. Brunken ,  Jeffrey M. Bosworth

IPC: B64C27/57 ,  B64C11/06 ,  B64C11/30 ,  B64C29/00

Abstract: In one aspect, a rotor assembly includes a hub and a plurality of rotor blades; at least one blade root actuator configured to adjust at least one of the plurality of rotor blades independently of the other rotor blades to accommodate forces on the aircraft; and at least one controller couplable to the at least one blade root actuator and configured to send signals to the at least one blade root actuator to enable adjustment of the at least one of the plurality of rotor blades. In another embodiment, at least one blade flap is associated with a rotor blade can be actuated to adjust the shape of the rotor blade. In some embodiments, there are methods and systems incorporating at least one of the root blade actuator and the blade flap for stabilizing a tiltrotor aircraft by counteracting destabilizing forces on at least one rotor blade.