公开(公告)号：US11952111B2

公开(公告)日：2024-04-09

申请号：US16862276

申请日：2020-04-29

申请人： Bell Textron Inc.

发明人： Frank Bradley Stamps ,  Thomas C. Parham, Jr.

IPC分类号： B64C27/605 ,  B64C27/57 ,  B64C27/64 ,  B64C27/68 ,  B64C29/00

CPC分类号： B64C29/0033 ,  B64C27/57 ,  B64C27/605 ,  B64C27/64 ,  B64C27/68

摘要： A system is provided for controlling the pitch of blades of a rotor, the system comprising an actuator for each blade, each actuator being configured for selective control of the pitch of an associated blade about a pitch axis. Sensors are configured for determining aerodynamic forces acting on the rotor, and a flight control system is configured to receive signals from the sensors and for operating the actuators in response to the signals to achieve a desired pitch-flap coupling value.

公开(公告)号：US11691723B2

公开(公告)日：2023-07-04

申请号：US17307845

申请日：2021-05-04

申请人： Bell Textron Inc.

发明人： Thomas C. Parham, Jr. ,  Frank Bradley Stamps ,  Jouyoung Jason Choi ,  Albert Gerard Brand ,  Michael Scott Seifert ,  Richard E. Rauber ,  John E. Brunken, Jr.

IPC分类号： B64C29/00 ,  B64C11/32 ,  B64C11/00 ,  B64C11/02

CPC分类号： B64C29/0033 ,  B64C11/008 ,  B64C11/02 ,  B64C11/32

摘要： A gimbaled rotor assembly for an aircraft. The gimbaled rotor assembly including a static mast; a spherical bearing comprising an inner component and an outer component pivotable relative to each other about a bearing focus, the inner component fixedly coupled to the static mast; a rotor hub rotatably coupled to the outer component, allowing for relative rotation of the rotor hub about a rotor axis and for pivoting together with the outer component about the bearing focus; and a primary hub spring coupling the outer component to the static mast and configured for opposing pivoting of the rotor hub about the bearing focus from a neutral position.

公开(公告)号：US20210163128A1

公开(公告)日：2021-06-03

申请号：US16862276

申请日：2020-04-29

申请人： Bell Textron Inc.

发明人： Frank Bradley Stamps ,  Thomas C. Parham, Jr.

IPC分类号： B64C29/00 ,  B64C27/605 ,  B64C27/57 ,  B64C27/64 ,  B64C27/68 ,  F01D5/10

摘要： A system is provided for controlling the pitch of blades of a rotor, the system comprising an actuator for each blade, each actuator being configured for selective control of the pitch of an associated blade about a pitch axis. Sensors are configured for determining aerodynamic forces acting on the rotor, and a flight control system is configured to receive signals from the sensors and for operating the actuators in response to the signals to achieve a desired pitch-flap coupling value.