公开(公告)号：US11365012B2

公开(公告)日：2022-06-21

申请号：US16214735

申请日：2018-12-10

Applicant: Bell Helicopter Textron Inc.

Inventor： Joseph Dean Rainville

IPC: B64D31/00 ,  H01M8/04082 ,  H01M8/04746 ,  H01M8/04313 ,  B64D33/08 ,  B64C39/02 ,  B60L58/33 ,  B60L58/00 ,  B64D27/24 ,  H01M8/04029

Abstract: An aircraft that includes a fuselage, an electric motor driven propulsion system, and a fuel cell system configured to provide electricity to the electric motor. The fuel cell system includes a fuel cell, a hydrogen tank, an oxygen tank, an air channel, and a cathode switch. The cathode switch being configured to convert between an air mode, wherein the fuel cell operates utilizing air from the air channel, and an oxygen mode, wherein the fuel cell operates utilizing oxygen from the oxygen tank.

公开(公告)号：US20220185469A1

公开(公告)日：2022-06-16

申请号：US17119703

申请日：2020-12-11

Applicant: Bell Textron Inc.

Inventor： William ATKINS ,  George Ryan DECKER ,  Steven Allen ROBEDEAU, JR.

IPC: B64C29/00

Abstract: A pylon conversion actuator, for use in tiltrotor aircraft, that converts the tiltrotor between hover flight mode and forward flight mode. Pylon conversion actuator selectively retracts and extends between a retracted position to an extended position. Pylon conversion actuator includes an extendable arm, a motor, and an actuator platform.

公开(公告)号：US20220177109A1

公开(公告)日：2022-06-09

申请号：US17116778

申请日：2020-12-09

Applicant: Bell Textron Inc.

Inventor： Levi HEFNER ,  Maurice Griffin ,  Jennifer Diana Andrews

IPC: B64C1/06 ,  B64C29/02 ,  B64C39/08 ,  B64D47/08 ,  B64C1/36 ,  B64D9/00

Abstract: In an embodiment, an aircraft includes first and second wings. The aircraft also includes a plurality of propulsion assemblies, the plurality of propulsion assemblies including a propulsion assembly connected to each end of each of the first and second wings. The aircraft also includes first and second vertical supports disposed between the first and second wings. The aircraft also includes a storage pod disposed between the first and second vertical supports. The storage pod includes a nose portion that extends forward of the plurality of propulsion assemblies. The nose portion includes at least one radar and at least one camera. Other embodiments of this aspect include corresponding computer systems, apparatus, and computer programs recorded on one or more computer storage devices, each configured to perform the actions of the methods.

公开(公告)号：US20220169397A1

公开(公告)日：2022-06-02

申请号：US17107048

申请日：2020-11-30

Applicant: Bell Textron Inc.

Inventor： Mark Allen SIEMSEN ,  Albertus Muljadi TJANDRA

IPC: B64D31/06 ,  G08G5/00 ,  G06N7/00

Abstract: In an embodiment, a method includes receiving flight data related to an aircraft that includes an engine installed therein. The flight data includes values of an engine parameter. The method also includes determining values of a measured installation delta for the engine based, at least in part, on the flight data. The method also includes determining values of a measured power parameter for the engine based, at least in part, on the flight data. The method also includes generating a mathematical model of a plurality of installation deltas for the engine as a function of the engine parameter, where the plurality of installation deltas include the measured installation delta and an unmeasured installation delta. The method also includes validating the mathematical model based, at least in part, on the values of the measured installation delta. The method also includes generating a performance profile of the engine.

公开(公告)号：US20220169389A1

公开(公告)日：2022-06-02

申请号：US17112446

申请日：2020-12-04

Applicant: Bell Textron Inc.

Inventor： Christopher Edward Foskey

IPC: B64D11/06 ,  B64C1/14 ,  E05F15/622

Abstract: An embodiment is a system including an external passenger seating unit comprising at least one seat; and a translation mechanism for translating the external passenger seating unit between a first position in which the external passenger seating unit is stowed in a payload bay of an aircraft and a second position in which the external passenger seating unit is deployed external to the aircraft for accommodating at least one passenger.

公开(公告)号：US11339836B2

公开(公告)日：2022-05-24

申请号：US16926451

申请日：2020-07-10

Applicant: Bell Textron Inc.

Inventor： Gilberto Morales ,  Carlos Alexander Fenny ,  Cody Anderson

IPC: F16D41/07 ,  B64D35/00 ,  F16D41/08 ,  F16D43/25 ,  F16D41/06

Abstract: A clutch has an inner race, an outer race spaced from the inner race and forming a radial cavity between the races, and a plurality of sprags disposed in the radial cavity. The sprags have a different coefficient of thermal expansion (CTE) from the inner race, the outer race, or both races, and a sprag cage retains the sprags at a uniform spacing within the radial cavity. When the clutch is at a first temperature, a gap exists between the sprags and the inner race, between the sprags and the outer race, or between the sprags and both races, and the clutch is disengaged. When the clutch is at a second temperature the sprags are in contact with both the races, and the clutch is engaged.

公开(公告)号：US11338917B2

公开(公告)日：2022-05-24

申请号：US17036942

申请日：2020-09-29

Applicant: Bell Textron Inc.

Inventor： William Anthony Amante ,  Timothy Brian Carr

IPC: B64C29/00 ,  F04D27/00 ,  F04D29/18

Abstract: In an embodiment, a ducted fan assembly includes a housing that further includes a rotor. The ducted fan assembly also includes a rim that defines an opening surrounding at least a portion of the housing. The ducted fan assembly also includes a movable leading edge that is attached to the rim and extends around at least a portion of a perimeter of the ducted fan assembly, where the movable leading edge is adjustable between at least a first position and a second position.

公开(公告)号：US20220145810A1

公开(公告)日：2022-05-12

申请号：US17094340

申请日：2020-11-10

Applicant: Bell Textron Inc.

Inventor： Alan Hisashi STEINERT

IPC: F02C9/42 ,  B64D27/10 ,  B64D31/04 ,  B64D41/00 ,  B64C27/06 ,  B64D27/24 ,  B64C27/12 ,  B64C27/82 ,  B64D37/00 ,  F02C6/20

Abstract: An exemplary aircraft includes a turbine engine having a gas generator spool and a power spool, the power spool operational to drive a rotor, a first generator coupled to the gas generator spool, and a controller operable to increase a load on the gas generator spool when the gas generator spool is on a speed limit thereby increasing a speed limit margin in order to increase power available from the turbine engine.

公开(公告)号：US20220136586A1

公开(公告)日：2022-05-05

申请号：US17086876

申请日：2020-11-02

Applicant: Bell Textron Inc.

Inventor： Gregory Alan Spruce ,  Alan Wayne Falls ,  Douglas Robert Mueller

IPC: F16H1/28 ,  F16H57/08 ,  F16H57/00 ,  F16H57/023

Abstract: In one embodiment of the present disclosure, there is provided a planetary gear system. The planetary gear system includes a split double helical ring gear having a first ring gear with first helical ring teeth and a second ring gear with second helical ring teeth, a split double helical sun gear having a first sun gear with first helical sun teeth and a second sun gear with second helical sun teeth, a sun gear coupler coupling the first sun gear and the second sun gear; and a single-piece double helical planet pinion having a first helical planet teeth portion and a second helical planet teeth portion, where the first helical planet teeth mesh with the first helical sun teeth and the first helical ring teeth, and the second helical planet teeth mesh with the second helical sun teeth and the second helical ring teeth.

公开(公告)号：US20220127012A1

公开(公告)日：2022-04-28

申请号：US17079978

申请日：2020-10-26

Applicant: Bell Textron Inc.

Inventor： Gregory Alan Spruce ,  Alan Wayne Falls ,  Douglas Robert Mueller

IPC: B64D35/00 ,  B64C27/12 ,  F16H57/04

Abstract: In one embodiment of the present disclosure, there is provided an aircraft gearbox including a gear and a gear shrouding for providing lubrication to the gear. The gear shrouding is disposed around the gear, has an inner surface facing the gear and an opposing outer surface facing away from the gear, and includes a channel formed along at least a portion of the gear shrouding between the inner surface and the outer surface of the gear shrouding, an input orifice extending to the channel, wherein the input orifice is at a first position on the channel, and an output orifice extending to the channel, wherein the output orifice is at a second position on the channel different from the first position. In another embodiment, the gear shrouding further includes a second output orifice at a third position on the channel different from the first and second positions.