公开(公告)号：US10752349B2

公开(公告)日：2020-08-25

申请号：US16173064

申请日：2018-10-29

Applicant: Bell Helicopter Textron Inc.

Inventor： Andrew Paul Haldeman ,  Zachary Edwin Dailey ,  Aaron Alexander Acee ,  Dalton T. Hampton

IPC: B64C27/605 ,  B64C27/06 ,  B64C27/00 ,  B64C13/04 ,  B64C13/40 ,  B64C27/72

Abstract: An exemplary rotorcraft includes a power train with an engine coupled to a gearbox, a main rotor blade having a mast coupled to the power train, a control input linkage in communication between a pilot input device and the main rotor blade configured to communicate a control input force from the pilot input device to the main rotor blade, and a counterweight system in connection with the control input linkage and the power train to apply a centrifugal force to the control input linkage.

公开(公告)号：US11117654B2

公开(公告)日：2021-09-14

申请号：US16277504

申请日：2019-02-15

Applicant: Bell Helicopter Textron Inc.

Inventor： Aaron Alexander Acee ,  Andrew Paul Haldeman ,  Colin John Thomas

IPC: B64C27/82 ,  B64C27/78 ,  B64C27/08

Abstract: A method of controlling a tail rotor system includes pivoting a swashplate of the tail rotor system about an axis passing through a diameter of the swashplate. Pivoting the swashplate causes a first linkage of a first pair of linkages coupled between the swashplate and a collective crosshead to move in a first direction and a second linkage of the first pair of linkages coupled between the swashplate and the collective crosshead to move in a second direction that is opposite the first direction. The movement of the first and second linkages causes a plane of rotation of a pair of rotors of the tail rotor system to cant relative to a centerline of a mast of the tail rotor system. A tail rotor system is also disclosed.

公开(公告)号：US10814971B2

公开(公告)日：2020-10-27

申请号：US15949660

申请日：2018-04-10

Applicant: Bell Helicopter Textron Inc.

Inventor： Dalton T. Hampton ,  Andrew Paul Haldeman ,  Aaron Alexander Acee ,  Matthew John Hill

IPC: B64C27/82 ,  B64C27/06

Abstract: Systems and methods include providing an aircraft with a tail rotor system having a tail rotor housing that forms a cambered airfoil between an upper cambered surface and a lower cambered surface of the tail rotor housing. The cambered airfoil design of the tail rotor housing is capable of providing sufficient lifting force of an aircraft to offload the tail rotor during forward flight, thereby eliminating the need for a traditional vertical stabilizer or fin. The tail rotor blades of the tail rotor system are disposed within an aperture in the tail rotor housing, which minimizes or preferably eliminates exposure of the tail rotor blades to edgewise airflow typically encountered during forward flight, thereby allowing rigid rotor hubs, both in-plane and out-of-plane, to be used in the tail rotor system while also reducing noise output of the tail rotor system.

公开(公告)号：US20200247535A1

公开(公告)日：2020-08-06

申请号：US16266086

申请日：2019-02-03

Applicant: Bell Helicopter Textron Inc.

Inventor： Aaron Alexander Acee ,  Andrew Paul Haldeman

IPC: B64C27/12 ,  F04D29/58 ,  B64C27/20 ,  B64D33/08

Abstract: Systems and methods include providing an aircraft with a ducted rotor assembly. The ducted rotor assembly includes a housing having a duct, a rotor drive mechanism coupled to a rotor system, and a plurality of stators that both structurally support the rotor drive mechanism within the duct of the housing and carry a fluid through internal fluid passages in the plurality of stators to provide cooling to the rotor drive mechanism. Some of the stators carry fluid to the rotor drive mechanism, where the fluid absorbs heat from the rotor drive mechanism, and some of the stators carry fluid away from the rotor drive mechanism. The rotor system generates an airflow over the stators carrying fluid away from the rotor drive mechanism to effect transfer between the fluid and the airflow.

公开(公告)号：US20190329878A1

公开(公告)日：2019-10-31

申请号：US15967220

申请日：2018-04-30

Applicant: Bell Helicopter Textron Inc.

Inventor： Andrew Paul Haldeman ,  Zachary Edwin Dailey ,  Charles Owen Black ,  Dalton T. Hampton ,  Aaron Alexander Acee

IPC: B64C27/52 ,  B64C27/12

Abstract: A transmission tilt control device includes a transmission rotatably coupled to an airframe of a helicopter, a rotor mast coupled to the transmission, and an actuator coupled between the transmission and the airframe. The actuator being configured to rotate the transmission fore and aft about a tilt axis that is perpendicular to an axis of rotation of the rotor mast.

公开(公告)号：US20190291848A1

公开(公告)日：2019-09-26

申请号：US15933106

申请日：2018-03-22

Applicant: Bell Helicopter Textron Inc.

Inventor： Sebastien Duval ,  Guillaume Noiseux-Boucher ,  Aaron Alexander Acee

IPC: B64C5/06 ,  B64C27/82

Abstract: Systems and methods include providing an aircraft with a vertical stabilizer system having a vertical stabilizer operatively coupled to a tail boom, tail rotor gearbox, or other component of the aircraft at a forward attachment and an aft attachment. The vertical stabilizer is selectively rotatable to adjust an angle of attack of the vertical stabilizer with respect to a forward flight direction of the aircraft. The vertical stabilizer is rotatable between a forward flight position having a substantially small degree angle of attack and a hover or lateral movement position having a substantially ninety degree angle of attack.