公开(公告)号：US20180050796A1

公开(公告)日：2018-02-22

申请号：US15241529

申请日：2016-08-19

Applicant: Bell Helicopter Textron Inc.

Inventor： John Robert Wittmaak

IPC: B64C27/12 ,  B64D41/00 ,  B60L7/02 ,  B60L7/10

CPC classification number: B64C27/12 ,  B60L7/02 ,  B60L7/10 ,  B60L2200/10 ,  B64D41/00 ,  Y02T90/16

Abstract: In some embodiments, a rotorcraft includes a fuselage having a rotor hub assembly protruding therefrom that is rotatable relative thereto. A generator having an armature is mechanically coupled to the rotor hub assembly such that the armature is rotatable in response to rotation of the rotor hub assembly. A braking unit is in selective electrical communication with the generator. The braking unit is adapted to apply an electrical resistance to rotation of the armature, thereby reducing a rotational speed of the rotor hub assembly.

公开(公告)号：US20180043984A1

公开(公告)日：2018-02-15

申请号：US15233927

申请日：2016-08-10

Applicant: Bell Helicopter Textron Inc.

Inventor： Daniel Bryan Robertson ,  Kirk Landon Groninga ,  Frank Bradley Stamps

IPC: B64C3/10 ,  B64C9/00 ,  B64C39/02

CPC classification number: B64C3/10 ,  B64C9/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/108 ,  B64C2201/126

Abstract: An inflight connection system for aircraft having at least one wing with a wingtip includes, for each aircraft, a primary connector selectively extendable from the wingtip, an alignment connector selectively extendable from the wingtip and a male and female connector assembly disposed proximate the wingtip. The primary connectors extend a greater distance from the wingtips than the alignment connectors such that the primary connectors form a first connection between the aircraft when the aircraft are flying in a connection pattern. Thereafter, retraction of the primary connectors reduces wingtip separation of the aircraft such that the alignment connectors form a second connection between the aircraft establishing coarse alignment therebetween. Thereafter, retraction of the primary and alignment connectors further reduces wingtip separation of the aircraft such that the male and female connector assemblies form a third connection between the aircraft establishing fine alignment therebetween.

公开(公告)号：US09889929B2

公开(公告)日：2018-02-13

申请号：US14038154

申请日：2013-09-26

Applicant: Bell Helicopter Textron Inc.

Inventor： Charles Eric Covington ,  Carlos A. Fenny

IPC: B64C27/32 ,  B64C27/64 ,  H01F7/06 ,  H01F7/122 ,  B64C27/605 ,  H02K7/00

CPC classification number: B64C27/64 ,  B64C27/605 ,  H01F7/066 ,  H01F7/122 ,  H02K7/003

Abstract: According to one embodiment, a linear control motor includes a first permanent magnet, a coil, a first magnetic material, a shaft, and a first non-magnetic material. The first non-magnetic material is disposed between at least one of the movable components and at least one of the static components and operable to prevent physical contact between at least one of the movable components and at least one of the static components.

公开(公告)号：US20180029699A1

公开(公告)日：2018-02-01

申请号：US15221090

申请日：2016-07-27

Applicant: Bell Helicopter Textron Inc.

Inventor： Jeffrey Paul Nissen ,  John Richard McCullough

IPC: B64C27/473 ,  B64C29/00

CPC classification number: B64C27/473 ,  B64C29/0033 ,  B64C2027/4733 ,  B64D15/12

Abstract: In some embodiments, a rotorcraft includes an engine, a rotor hub assembly mechanically coupled to the engine and a plurality of rotor blade assemblies rotatably mounted to the rotor hub assembly. Each of the rotor blade assemblies includes a rotor blade having a leading edge and an erosion shield system extending spanwise along the leading edge of the rotor blade. The erosion shield system includes a plurality of erosion shield segments positioned adjacent to one another forming joints therebetween wherein, the joints deform responsive to strain experienced by the rotor blade, thereby isolating the erosion shield segments from at least a portion of the strain experienced by the rotor blade.

公开(公告)号：US20180022214A1

公开(公告)日：2018-01-25

申请号：US15674131

申请日：2017-08-10

Applicant: Textron Inc.

Inventor： Shane Christopher Reid ,  John Lawrence Stocks ,  Matthew Lawrence O'Donnell

IPC: B60K28/10 ,  F02D41/02 ,  F02D41/26

CPC classification number: B60K28/10 ,  B60K28/02 ,  B60W10/06 ,  B60W30/18 ,  F02D31/006 ,  F02D41/021 ,  F02D41/26 ,  F02D2200/60

Abstract: A method for controlling the operation of a vehicle prime mover based on the engagement status of one or more safety restraints of the vehicle. In various implementations the method comprises monitoring, via a RPM controller of the vehicle, an operational status of vehicle, monitoring, via the RPM controller, the engagement status at least one passenger safety restraint of the vehicle, and limiting, via the RPM controller, a rotational speed, e.g., revolutions per minute (RPM) of one or more prime mover of the vehicle when the vehicle is in a On operational status and the at least one safety restraint is in a disengaged status.

公开(公告)号：US09870004B2

公开(公告)日：2018-01-16

申请号：US14284045

申请日：2014-05-21

Applicant: Bell Helicopter Textron Inc.

Inventor： Brady G. Atkins ,  James E. Harris ,  Carl D. Griffith

IPC: G01C23/00 ,  G05D1/08 ,  G05D1/00

CPC classification number: G05D1/0833 ,  B64C13/341 ,  B64C27/58 ,  G05D1/0077 ,  B64C2027/7283 ,  B64C27/001

Abstract: A method of increasing the control authority of redundant stability and control augmentation system (SCAS) actuators by utilizing feedback between systems such that one system may compensate for the position of a failed actuator of the other system. Each system uses an appropriate combination of reliable and unreliable inputs such that unreliable inputs cannot inappropriately utilize the increased authority. Each system may reconfigure itself when the other system actuator fails at certain positions so that the pilot or other upstream input maintains sufficient control authority of the aircraft.

公开(公告)号：US09868542B2

公开(公告)日：2018-01-16

申请号：US15407471

申请日：2017-01-17

Applicant: Bell Helicopter Textron Inc.

Inventor： Jeffrey Matthew Williams ,  James Elbert King ,  James Everett Kooiman ,  Andrew G. Baines ,  Christopher R. Jackson ,  George Ryan Decker ,  Daniel J. Sweigard

IPC: B64D27/26 ,  F16H57/021 ,  F16H57/025 ,  B64C29/00 ,  B64C27/26 ,  B64C3/32 ,  B64D35/00 ,  F16H57/02

CPC classification number: B64D27/26 ,  B64C3/32 ,  B64C27/22 ,  B64C27/26 ,  B64C29/0033 ,  B64D35/00 ,  B64D2027/264 ,  B64D2027/266 ,  B64F5/40 ,  F16H57/021 ,  F16H57/025 ,  F16H2057/02043 ,  Y10T29/49318 ,  Y10T74/1966

Abstract: A propulsion system for a tiltrotor aircraft includes an engine supported by the airframe and a fixed gearbox operably coupled to the engine. Inboard and outboard pedestals are supported by the airframe and positioned above the wing. A pylon assembly is rotatably coupled between the inboard and outboard pedestals. The pylon assembly includes a spindle gearbox having an input gear, a mast operably coupled to the input gear and a proprotor assembly operable to rotate with the mast. The spindle gearbox is rotatable about a conversion axis to selectively operate the tiltrotor aircraft between helicopter and airplane modes. A common shaft, rotatable about the conversion axis, is configured to transfer torque from an output gear of the fixed gearbox to the input gear of the spindle gearbox. Each of the inboard and outboard pedestals includes a pillow block housing such as a full or a split pillow block housing.

公开(公告)号：US20180013270A1

公开(公告)日：2018-01-11

申请号：US15641936

申请日：2017-07-05

Applicant: Greenlee Textron Inc.

Inventor： John Michael Jubeck ,  Daniel John Marben ,  John Siegfried Tobias

IPC: H02G1/08 ,  G01L5/04 ,  G05B15/02 ,  G08B21/18

CPC classification number: G01L5/108 ,  G01L1/125 ,  G01L5/047 ,  G05B15/02 ,  G08B21/182 ,  H02G1/08

Abstract: A system and method include a gauge device and one or more of a communication device or a pulling assembly. The gauge device may be configured to send a message to display on one or more of the communication device or pulling assembly. Additionally or alternatively, the gauge device may be configured to send the message to be processed by pulling assembly to determine and perform a pull action. Additionally or alternatively, the gauge device may be configured to send the message to be executed by the pulling assembly to perform a pull action.

公开(公告)号：US09863523B2

公开(公告)日：2018-01-09

申请号：US15075583

申请日：2016-03-21

Applicant: Textron Inc.

Inventor： John Stocks ,  Scott Allen Wohlgamuth ,  Landon Ball ,  Timothy Kolody ,  Christopher Furman

IPC: F16H57/04 ,  B62J13/00 ,  F16D1/00 ,  F16H57/02 ,  F16H57/035 ,  F16H57/027 ,  F16H9/14

CPC classification number: F16H57/0416 ,  F16H9/14 ,  F16H57/035 ,  F16H57/0489 ,  F16H2057/02065

Abstract: A continuously variable transmission housing is provided that includes an inner cover and an outer cover connectable to the inner cover to define an interior chamber. The interior chamber is structured and operable to enclose a continuously variable transmission primary pulley, secondary pulley and pulley belt. The housing includes a duct panel mounted to the inner cover such that when the primary pulley is disposed within the interior chamber, the duct panel is disposed between an outer face of the primary pulley and the inner cover. Moreover, an air duct is defined between the inner cover and the duct panel, wherein the air duct is fluidly connected to ambient air from an ambient environment external to the housing. The duct panel includes a center opening that structured and operable to allow the ambient air to be drawn through the air duct and into the housing interior chamber.

公开(公告)号：US20180002015A1

公开(公告)日：2018-01-04

申请号：US15200230

申请日：2016-07-01

Applicant: Bell Helicopter Textron Inc.

Inventor： John Richard McCullough ,  Paul K. Oldroyd

IPC: B64C29/02 ,  B64D17/02 ,  B64C39/02 ,  B64D1/08 ,  G05D1/10 ,  G05D1/00

CPC classification number: B64C29/02 ,  B64C11/28 ,  B64C29/0033 ,  B64C39/024 ,  B64D1/08 ,  B64D17/02 ,  B64D17/80 ,  B64F1/31

Abstract: In some embodiments, a transportation method includes coupling a flying frame to a passenger pod assembly; lifting the passenger pod assembly into the air in a vertical takeoff and landing mode with the passenger pod assembly in a generally horizontal attitude; transitioning from the vertical takeoff and landing mode to a forward flight mode by rotating the flying frame relative to the passenger pod assembly, which remains in the generally horizontal attitude; transporting the passenger pod assembly toward a second location in the forward flight mode; transitioning the flying frame from the forward flight mode to the vertical takeoff and landing mode by rotating the flying frame relative to the passenger pod assembly, which remains in the generally horizontal attitude; landing the flying frame at the second location in the vertical takeoff and landing mode; and releasing the passenger pod assembly.