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公开(公告)号：US10196139B2
公开(公告)日：2019-02-05
申请号：US15986219
申请日：2018-05-22
Applicant: Bell Helicopter Textron Inc.
Inventor： Emily Schofield , Chad Lewis Jarrett , Daniel P. Sottiaux , Frank Bradley Stamps
Abstract: An apparatus comprising a drivelink comprising a housing including a socket, wherein the socket comprises a cross-sectional area, and a bearing cartridge disposed within the socket, wherein a cross-sectional area of the cartridge is less than the cross-sectional area of the socket. An apparatus comprising a drivelink comprising a housing having a socket, and a bearing cartridge positioned within the socket and comprising a first portion and a second portion, wherein the first portion is configured to undergo compression when a load is applied to the drivelink, and wherein the second portion is configured to not be in tension when the load is applied to the drivelink.
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公开(公告)号：US20190031336A1
公开(公告)日：2019-01-31
申请号：US16154207
申请日：2018-10-08
Applicant: Bell Helicopter Textron Inc.
Inventor： John Richard McCullough , Paul K. Oldroyd
IPC: B64C29/00 , B64C27/26 , B64C27/28 , B64C27/30 , B64C29/02 , B64C39/02 , B64C39/08 , B64D27/06 , B64D27/24 , B64D27/26
Abstract: Systems and methods for automated configuration of mission specific aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. A method includes receiving mission parameters including flight parameters and payload parameters; configuring an airframe based upon the mission parameters including selecting a flight control system, first and second wings and first and second pylons operable for coupling between the first and second wings, the first and second wings each having first and second inboard nacelle stations and first and second outboard nacelle stations; determining thrust requirements based upon the mission parameters; configuring a two-dimensional distributed thrust array based upon the thrust requirements including selecting inboard propulsion assemblies operable for coupling to the inboard nacelle stations of the first and second wings and selecting outboard propulsion assemblies operable for coupling to the outboard nacelle stations of the first and second wings.
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公开(公告)号：US20190031334A1
公开(公告)日：2019-01-31
申请号：US16154173
申请日：2018-10-08
Applicant: Bell Helicopter Textron Inc.
Inventor： John Richard McCullough , Paul K. Oldroyd
Abstract: A mission configurable aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft includes an airframe having first and second wings with first and second pylons extending therebetween. A two-dimensional distributed thrust array is attached to the airframe. The thrust array including a plurality of inboard propulsion assemblies coupled to first and second inboard nacelle stations of the first and second wings. The thrust array also includes a plurality of outboard propulsion assemblies coupled to first and second outboard nacelle stations of the first and second wings. A flight control system is operable to independently control each of the propulsion assemblies. A payload is coupled to the airframe. The inboard propulsion assemblies have a thrust type that is different from the thrust type of the outboard propulsion assemblies.
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公开(公告)号：US20190031333A1
公开(公告)日：2019-01-31
申请号：US15662257
申请日：2017-07-27
Applicant: Bell Helicopter Textron Inc.
Inventor： Kirk Landon Groninga , Daniel Bryan Robertson
CPC classification number: B64C29/0033 , B64C39/008 , B64C39/08 , B64D27/24 , B64D2027/026
Abstract: An aircraft having a vertical takeoff and landing flight mode and a forward flight mode. The aircraft includes a fuselage and a dual tiltwing assembly having a vertical lift orientation and a forward thrust orientation relative to the fuselage. The dual tiltwing assembly includes a forward wing and an aft wing coupled together and to the fuselage by a quadrilateral linkage. A distributed propulsion system is coupled to the dual tiltwing assembly and includes a plurality of forward propulsion assemblies coupled to the forward wing and a plurality of aft propulsion assemblies coupled to the aft wing. A flight control system is operably associated with the distributed propulsion system and the dual tiltwing assembly. The flight control system is operable to independently control each of the propulsion assemblies and is operable to transition the dual tiltwing assembly between the vertical lift orientation and the forward thrust orientation.
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公开(公告)号：US10190672B2
公开(公告)日：2019-01-29
申请号：US15089671
申请日：2016-04-04
Applicant: Bell Helicopter Textron Inc.
Inventor： Ryan T. Ehinger
Abstract: According to one embodiment, a rotorcraft includes a body, a rotor blade, a drive system that can be operated to rotate the rotor blade, and an emergency valve control unit. The drive system contains a first gearbox assembly, a second gearbox assembly, a first lubrication system that can deliver lubricant to the first gearbox assembly, and a second lubrication system that can deliver lubricant to the second gearbox assembly. The drive system also contains an emergency valve that can be opened to deliver lubricant from the first lubrication system to the second gearbox assembly. The emergency valve control unit can instruct the emergency valve to open.
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Patent Agency Ranking
公开(公告)号：US20190017543A1
公开(公告)日：2019-01-17
申请号：US15698796
申请日：2017-09-08
Applicant: Bell Helicopter Textron Inc.
Inventor： Glenn Alan Shimek , Amarjit Olenchery Kizhakkepat , Ken Shundo , Michael Dean Dearman , Kyle Thomas Cravener , Michael Christopher Burnett
Abstract: A bearing assembly for coupling a proprotor blade to a yoke in a proprotor system. The bearing assembly is positionable within an inboard pocket of a blade arm of the yoke. The proprotor system is operable for use on a tiltrotor aircraft having helicopter and airplane flight modes. The bearing assembly includes a centrifugal force bearing and a shear bearing having an inboard beam coupled therebetween. The centrifugal force bearing has a mating surface, a lateral movement constraint feature and at least one radially extending anti-rotation feature. The inboard beam has a mating surface in a contact relationship with the mating surface of the centrifugal force bearing, a lateral movement constraint feature operably associated with the lateral movement constraint feature of the centrifugal force bearing and at least one radially extending anti-rotation feature that corresponds with the at least one radially extending anti-rotation feature of the centrifugal force bearing.
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公开(公告)号：US20190016457A1
公开(公告)日：2019-01-17
申请号：US15990624
申请日：2018-05-26
Applicant: Bell Helicopter Textron Inc.
Inventor： Robert Patrick Wardlaw , John Richard McCullough , Amarjit Olenchery Kizhakkepat , Tyler Wayne Baldwin
CPC classification number: B64C29/0033 , B64C11/06 , B64C27/35 , F16C17/10 , F16C33/06 , F16C2326/43
Abstract: A proprotor system for a tiltrotor aircraft having helicopter and airplane flight modes includes a yoke having a plurality of blade arms each having an inboard pocket with an outboard surface. Each of a plurality of bearing assemblies is disposed at least partially within one of the inboard pockets with each bearing assembly including a shear bearing and a centrifugal force bearing having an integral shoe with an outboard surface. Each of a plurality of inboard beams is disposed at least partially between one of the centrifugal force bearings and one of the shear bearings. Each of a plurality of proprotor blades is coupled to one of the inboard beams. The integral shoes are coupled to the yoke such that there is a spaced apart relationship between the outboard surfaces of the integral shoes and the outboard surfaces of the pockets to prevent centrifugal force load transfer therebetween.
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公开(公告)号：US20190016456A1
公开(公告)日：2019-01-17
申请号：US15990623
申请日：2018-05-26
Applicant: Bell Helicopter Textron Inc.
Inventor： Michael Dean Dearman , Amarjit Olenchery Kizhakkepat , Tyler Wayne Baldwin , Michael Christopher Burnett
Abstract: A proprotor system for a tiltrotor aircraft having a helicopter flight mode and an airplane flight mode includes a yoke having a plurality of blade arms each having an inboard pocket with a load transfer surface. Each of a plurality of bearing assemblies is disposed at least partially within one of the inboard pockets. Each of a plurality of inboard beams is disposed at least partially between a centrifugal force bearing and a shear bearing of each bearing assembly and has a proprotor blade coupled thereto. Each of a plurality of independent shoes is coupled between one of the centrifugal force bearings and the yoke. Each shoe has a load transfer surface that has a contact relationship with the load transfer surface of the respective inboard pocket forming a centrifugal force load path therebetween.
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公开(公告)号：US20190016454A1
公开(公告)日：2019-01-17
申请号：US15648650
申请日：2017-07-13
Applicant: Bell Helicopter Textron Inc.
Inventor： Kyle Thomas Cravener , Amarjit Kizhakkepat , Ken Shundo , Jared Mark Paulson , Tyler Wayne Baldwin
CPC classification number: B64C29/0033 , B64C27/35 , B64C27/54 , F16C23/045 , F16C27/02 , F16C27/063 , F16C33/203 , F16C33/22 , F16C2326/43
Abstract: A proprotor system for a tiltrotor aircraft having a helicopter flight mode and an airplane flight mode. The proprotor system includes a yoke having a plurality of blade arms with inboard pockets. A centrifugal force and shear bearing assembly is disposed in each of the inboard pockets of the yoke. Each of a plurality of proprotor blades is coupled to the yoke by one of the bearing assemblies such that each proprotor blade has a pitch change degree of freedom about a pitch change axis and a tilting degree of freedom about a focal point. Each bearing assembly includes a centrifugal force bearing coupled to the yoke, a shear bearing coupled to the yoke and an inboard beam coupled between the centrifugal force bearing and the shear bearing. Each inboard beam is coupled to a respective proprotor blade.
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公开(公告)号：US10173348B2
公开(公告)日：2019-01-08
申请号：US15264410
申请日：2016-09-13
Applicant: Bell Helicopter Textron Inc.
Inventor： Sylvain Tessier , Richard Gingras , Jacques Dionne , Felix Bednar
IPC: B29C33/48 , B29C70/32 , B29C33/38 , B29K105/08 , B29K63/00 , B29K307/04 , B29L31/30
Abstract: A method of manufacturing a self-supporting, monolithic fuselage body, including engaging peripheral mandrel sections around at least one central mandrel section, placing uncured composite material on the mold surface, curing the composite material on the mold surface, and sliding the central mandrel section(s) out of engagement with the peripheral mandrel sections and disengaging the peripheral mandrel sections from the cured composite material without collapsing the mandrel sections. The peripheral mandrel sections each include a shape-retaining core of a thermally insulating material and an outer layer on an outer surface of the shape-retaining core. The outer layer has a coefficient of thermal expansion within the range of variation of that of the coefficient of thermal expansion of the composite material. A mandrel for layup and cure of a predetermined composite material in the manufacture of a monolithic fuselage is also discussed.
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