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：US11885407B1

公开(公告)日：2024-01-30

申请号：US17812880

申请日：2022-07-15

申请人： Textron Innovations Inc.

发明人： Douglas Robert Mueller ,  Ivan Russell Laric

IPC分类号： F16H57/04 ,  B64D35/00 ,  B64C29/00 ,  F01M11/06 ,  F16K11/076 ,  F01M11/04

CPC分类号： F16H57/0435 ,  B64C29/0033 ,  B64D35/00 ,  F01M11/04 ,  F01M11/065 ,  F16K11/076 ,  F16H57/0436

摘要： A fluid pump system for an aircraft has a rotatable component having first and second fluid ports, each port in fluid communication with a selected interior portion of the component, the portions being spaced from each other. A valve controls allows a first flow rate through the first fluid port and allows a second flow rate through the second fluid port when the component is in a first angular orientation. The valve allows a third flow rate through the first fluid port and allows a fourth flow rate through the second fluid port when the component is in a second angular orientation.

公开(公告)号：US11815368B2

公开(公告)日：2023-11-14

申请号：US16846372

申请日：2020-04-12

申请人： Bell Textron Inc.

发明人： Grant Michael Beall ,  William Anthony Amante ,  Jessica Arlie Revere

IPC分类号： G01D5/22 ,  F16H57/12 ,  F16H19/00 ,  B64C29/00 ,  B64C11/00 ,  B64D45/00

CPC分类号： G01D5/2291 ,  B64C11/001 ,  B64C29/0033 ,  B64D45/0005 ,  F16H19/001 ,  F16H57/12 ,  F16H2057/127

摘要： A resolver assembly for a ducted-rotor aircraft is configured to detect and measure rotation of a spindle of the aircraft. The resolver assembly includes first and second gear-driven resolvers. The first and second resolvers are coupled about a shared pivot axis and are independently pivotable about the pivot axis to maintain engagement of the first and second resolvers with the spindle of the aircraft. The resolver assembly is configured such that the first and second resolvers are biased toward the spindle. The input shafts of the first and second resolvers are spaced from the pivot axis through respective first and second distances that extend outward from the pivot axis along respective first and second radial directions. The first distance is equal to the second distance and the first radial direction is not coincident with the second radial direction.

公开(公告)号：USD999001S1

公开(公告)日：2023-09-19

申请号：US29807766

申请日：2021-09-14

申请人： Thomas James McMullen

设计人： Thomas James McMullen

摘要： FIG. 1 is a front oblique view of a display system.
FIG. 2 is a front elevation view of the display system.
FIG. 3 is a rear elevation view of the display system.
FIG. 4 is a right elevation view of the display system.
FIG. 5 is a left elevation view of the display system.
FIG. 6 is a top view of the display system.
FIG. 7 is a bottom view of the display system.
FIG. 8 is a partial bottom view of the display system; and,
FIG. 9 is a partial oblique bottom view of the display system.
Broken lines in FIGS. 1-9 are shown to illustrate environment, namely, apertures, a lower hemisphere, a golf ball, and a base, that form no part of the claimed design.

公开(公告)号：US11708147B2

公开(公告)日：2023-07-25

申请号：US17557981

申请日：2021-12-21

申请人： Textron Innovations Inc.

发明人： Pascal Flynn-Robitaille

IPC分类号： B64C9/08 ,  B64C13/38 ,  B64C29/02

CPC分类号： B64C9/08 ,  B64C13/38 ,  B64C29/02

摘要： An aircraft includes a wing and a rotor pod mounted to the wing. The rotor pod includes a body having a forward end and an aft end. A propeller is mounted to the body of the rotor pod at the forward end. A control surface is mounted to the body of the rotor pod between the forward and aft ends and extends outwardly from the body. The control surface is displaceable relative to the body between a first control configuration and a second control configuration to control an attitude of the aircraft. The control surface in the first control configuration is closer to the propeller than the control surface in the second control configuration.

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：US11673280B1

公开(公告)日：2023-06-13

申请号：US17410979

申请日：2021-08-24

申请人： Jeffrey S. Randall ,  Michael B. Alford

发明人： Jeffrey S. Randall ,  Michael B. Alford

IPC分类号： B26B1/04

CPC分类号： B26B1/04

摘要： A folding knife has a handle and a blade with a working end and a tang, the blade being coupled to the handle and pivotable relative to the handle about a fold axis between an open position and a closed position. A toggle is coupled to the handle and pivotable relative to the handle about a toggle axis, the toggle axis being located a radial distance from the fold axis. A free end of the toggle has an open lock face located a radial distance from the toggle axis. A primary lock face on the tang is located on the opposite side of the fold axis from the working end. When the blade is in the open position, the open lock face engages the primary lock face to prevent rotation of the blade toward the closed position.

公开(公告)号：USD987546S1

公开(公告)日：2023-05-30

申请号：US29675588

申请日：2019-01-03

申请人： Bell Helicopter Textron Inc.

设计人： Steven Loveland ,  Allen Brittain ,  Paul Charles Griffiths

摘要： FIG. 1 is a bottom perspective view of the aircraft landing gear.
FIG. 2 is a front elevational view of the landing gear of FIG. 1.
FIG. 3 is a rear elevational view of the landing gear of FIG. 1.
FIG. 4 is a left side elevational view of the landing gear of FIG. 1.
FIG. 5 is a right side elevational view of the landing gear of FIG. 1.
FIG. 6 is a top plan view of the landing gear of FIG. 1.
FIG. 7 is a bottom plan view of the landing gear of FIG. 1; and,
FIG. 8 is a top perspective view of the aircraft landing gear shown in an environment of use.
The broken lines shown in FIGS. 1-7 illustrate portions of the aircraft landing gear that form no part of the claimed design; the additional broken lines shown in FIG. 8 are for purposes of illustrating environmental subject matter only and forms no part thereof. The right side not shown is understood to be a mirror image of the left side shown in FIGS. 1-8.

公开(公告)号：US11623736B2

公开(公告)日：2023-04-11

申请号：US17336264

申请日：2021-06-01

申请人： Textron Innovations Inc.

发明人： Erik Oltheten ,  Darren Gregory Lang ,  Charles Eric Covington

IPC分类号： B64C13/04

摘要： An aircraft includes an electronically controlled engine (ECE) and a first and a second throttle control assembly. The first throttle control assembly includes a first throttle fly button configured to command a FLY mode and a first throttle idle button configured to command an IDLE mode. The second throttle control assembly includes a second throttle fly button configured to command the FLY mode and a second throttle idle button configured to command the IDLE mode.

公开(公告)号：US11587456B2

公开(公告)日：2023-02-21

申请号：US17354999

申请日：2021-06-22

申请人： Textron Innovations Inc.

发明人： Jeffrey Paul Nissen ,  Daniel Brent McCall ,  Joshua Peter Riccobono

IPC分类号： G09B9/30 ,  G09B9/08 ,  G02B27/01 ,  G06T19/00 ,  G09B9/12 ,  G09B9/24

摘要： Systems and methods include providing a virtual reality (“VR”) flight emulator system that simulates control, operation, and response of a vehicle. The flight emulator includes a control interface and a head-mounted display worn by a user. Motion, orientation, and/or forces experienced by the simulated vehicle are imparted to a user through a motion-control seat. Multiple flight emulators can be connected to a communication network, and a master flight emulator may teleport into a slave flight emulator in order to observe, overtake, override, and/or assume control of the slave flight emulator. Inputs made via the control interface of the master flight emulator or during playback of a pre-recorded training exercise or flight mission are translated into the control interface, head-mounted display, and motion-control seat of the slave flight emulator to provide real-time feedback to the user of the slave flight emulator.