公开(公告)号：US20220306073A1

公开(公告)日：2022-09-29

申请号：US17840101

申请日：2022-06-14

Applicant: Textron Inc.

Inventor： Russell William King

IPC: B60W20/13 ,  F02N11/06 ,  B60W10/26 ,  B60L58/14 ,  B60W20/12 ,  G01C21/26

Abstract: A method for remotely controlling the operation of a gas powered golf car, wherein the method comprises, via a global positioning system enhanced fleet management system (GPSEFMS) of the golf car communicatively connected with an internal combustion engine control unit (ECU) and a global position sensor of the golf car: monitoring a location of the golf car as the golf car is moving utilizing geospatial position data communicated from a global position sensor of the golf car to the GPSEFMS; determining when the golf car is one of near or within a geofenced area; and sending control commands to the ECU instructing the ECU to modify operation of the internal combustion engine, and hence operation of the golf car, in accordance with a predetermined operation profile specific to the geofenced area.

公开(公告)号：US20220289400A1

公开(公告)日：2022-09-15

申请号：US17197212

申请日：2021-03-10

Applicant: Bell Textron Inc.

Inventor： Sung K. Kim ,  Russell C. Peters ,  Manish J. Mistry

IPC: B64D31/14 ,  B64D27/24 ,  G05D1/10 ,  G05D1/08

Abstract: A method of adjusting a directional movement ability in an aircraft having two or more rotors includes receiving a desired thrust demand for each rotor of the two or more rotors, comparing the desired thrust demands to determine a maximum thrust demand, determining whether the maximum thrust demand exceeds a maximum thrust limit of the two or more rotors, and adjusting each desired thrust demand based on whether the maximum thrust demand exceeds the maximum thrust limit to provide an adjusted thrust demand for each rotor of the two or more rotors. Each rotor can be operated based on a respective adjusted thrust demand.

公开(公告)号：US20220289368A1

公开(公告)日：2022-09-15

申请号：US17198007

申请日：2021-03-10

Applicant: Bell Textron Inc.

Inventor： Andrew Paul HALDEMAN ,  Michael SEIFERT ,  Timothy McClellan MOSIG ,  Aaron ACEE ,  Diana R. TINLIN ,  Andrew Thomas CARTER ,  Glenn Thornton LANCASTER

IPC: B64C27/59 ,  F01D5/02 ,  F01D7/00 ,  F01D5/30

Abstract: A blade pitch adjustment mechanism includes a pitch cylinder having a first face and pitch slots extending longitudinally from the first face, a blade sleeve having a second face and a blade slot extending longitudinally from the second face, the blade sleeve is configured to be rotationally positioned in the pitch cylinder with the second face located with the first face, wherein the blade slot and the pitch slots are cooperative to form keyway, corresponding to a discrete blade pitch, when the blade slot is aligned with a pitch slot.

公开(公告)号：US11440285B2

公开(公告)日：2022-09-13

申请号：US16866288

申请日：2020-05-04

Applicant: Bell Textron Inc.

Inventor： Suvankar Mishra

IPC: G01N5/02 ,  B32B3/30 ,  B29B11/00 ,  B29B11/16

Abstract: An example of a method of manufacturing a component from a composite prepreg includes collecting a specimen from the composite prepreg and quantifying an amount of surface resin of the specimen by submerging the specimen in a container containing a fluid to determine a fluid pickup percentage. Responsive to a determination that the fluid pickup percentage exceeds a predefined threshold value, forming a component from the composite prepreg.

公开(公告)号：US11440277B2

公开(公告)日：2022-09-13

申请号：US16846373

申请日：2020-04-12

Applicant: Bell Textron Inc.

Inventor： Suvankar Mishra

IPC: B29C73/10 ,  B29C73/24 ,  B64F5/40 ,  B29K105/06 ,  B29L31/30

Abstract: A method of repairing an aircraft component having a structural core surrounded by an exterior skin of composite material includes removing damaged material from the component to create a cavity therein that exposes an undamaged portion of the structural core, applying a septum comprising composite material to the undamaged portion of the structural core within the cavity such that an orientation of fibers in the septum matches an orientation of fibers in the exterior skin, placing a repair core onto the septum in the cavity such that cells of the repair core are in alignment with cells of the undamaged portion of the structural core, inserting a shim into the cavity along a perimeter of the repair core, applying a patch that covers the cavity to the exterior skin, and co-curing the septum, shim, and patch to bond the repair core in place within the cavity.

公开(公告)号：US20220281613A1

公开(公告)日：2022-09-08

申请号：US17192478

申请日：2021-03-04

Applicant: BELL TEXTRON INC.

Inventor： THUVARAGAN SENTHILNATHAN ,  CHEN KUANG

IPC: B64D33/08 ,  B64D13/06 ,  B64D27/24

Abstract: Various implementations directed to an aircraft thermal management system are provided. In one implementation, an aircraft may include a fuselage having one or more fuselage sections. The aircraft may also include one or more electric motors configured to drive one or more propulsion systems of the aircraft, where the one or more electric motors are configured to generate thermal energy. The aircraft may further include an aircraft thermal management system configured to transfer the thermal energy generated by the one or more electric motors to the one or more fuselage sections.

公开(公告)号：US20220274692A1

公开(公告)日：2022-09-01

申请号：US17188785

申请日：2021-03-01

Applicant: Bell Textron Inc.

Inventor： Andrew Paul HALDEMAN ,  Paul Wayne WOOLBRIGHT ,  Timothy McClellan MOSIG ,  George Matthew THOMPSON

IPC: B64C27/35 ,  B64C27/82 ,  B64C27/48

Abstract: A spherical bearing centrifugal force retention link includes an inboard spherical bearing to attach to a rotor hub and an outboard spherical bearing to attach to a rotor blade. In use, the inboard spherical bearing and the outboard spherical bearing react centrifugal force radially and a torsional moment of the centrifugal force link is substantially constant throughout the rotor blade pitch range.

公开(公告)号：US11427350B2

公开(公告)日：2022-08-30

申请号：US16264623

申请日：2019-01-31

Applicant: Bell Helicopter Textron Inc.

Inventor： Justin A. Rivera

IPC: B64F5/10 ,  B64C27/473 ,  B33Y10/00 ,  B23K26/34 ,  B29C64/10 ,  B22F10/20 ,  B33Y80/00 ,  B23K15/00 ,  B28B1/00 ,  B23K26/354

Abstract: A method of forming a rotor blade, including forming at least one of a partial upper skin, a partial lower skin, and a partial support network using an additive manufacturing process; and forming a first receptacle in at least a one of the partial upper skin, the partial lower skin, and the partial support network using the additive manufacturing process. The first receptacle is configured to receive of at least one of an electronic component and a mechanical component. In some embodiments, there is a method of manufacturing a rotor blade that includes forming a first locating receptacle in at least one of the upper skin, the lower skin, and the support network using the additive manufacturing process; and positioning at least one of the upper skin, the lower skin, and the support network in a desired position on a fixture based, in part, on the first locating receptacle.

公开(公告)号：US20220267005A1

公开(公告)日：2022-08-25

申请号：US17184270

申请日：2021-02-24

Applicant: Bell Textron Inc.

Inventor： Craig CILLESSEN ,  Marco BAYERLEIN ,  Ansgar Hannes BAISCH ,  Ralf KASSNER

IPC: B64D9/00

Abstract: A fast-rope system for use with a rotary aircraft includes a tubular housing attached to an interior portion of a cabin and adjacent to an upper portion of an exit door opening of the rotary aircraft and a fast-rope frame structure rotatably coupled to the tubular housing. The fast-rope frame structure includes a cylindrical pipe contained partially within the tubular housing and operable to rotate within the tubular housing and a cantilever beam structure fixedly connected to the cylindrical pipe and configured to have a fast rope attached thereto and move in response to rotation of the cylindrical pipe within the tubular housing.

公开(公告)号：US11414185B2

公开(公告)日：2022-08-16

申请号：US16804357

申请日：2020-02-28

Applicant: Bell Textron Inc.

Inventor： Kyle Thomas Cravener

IPC: B64D27/12 ,  B64C11/28 ,  B64C29/00 ,  B64C11/06

Abstract: Embodiments are directed to a propulsion assembly for an aircraft. The propulsion assembly comprises a mast, a hub assembly coupled to the mast and having a gimballing degree of freedom relative to the mast, the hub assembly having an inner hub wall spaced part from the mast, a gimbal lock positioned about the mast, the gimbal lock configured to fit between the inner hub wall and the mast in an engaged position, and an over-center locking mechanism coupled to the gimbal lock. The gimbal lock is movable between a disengaged position and the engaged position relative to the hub assembly. The gimbal lock enables the gimballing degree of freedom in the disengaged position and disables the gimballing degree of freedom in the engaged position. The over-center locking mechanism is configured to move the gimbal lock between the engaged position and the disengaged position.