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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.
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公开(公告)号：US20170305567A1
公开(公告)日：2017-10-26
申请号：US15407481
申请日：2017-01-17
Applicant: Bell Helicopter Textron Inc.
Inventor： Jeffrey Matthew Williams , George Ryan Decker , James Everett Kooiman , Andrew G. Baines , Daniel J. Sweigard
CPC classification number: B64D27/26 , B64C3/32 , B64C27/22 , B64C27/26 , B64C29/0033 , B64D35/00 , B64D2027/266 , B64F5/40 , F16C17/022 , F16C17/26 , 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 an input gear of the spindle gearbox. Each of the inboard and outboard pedestals includes a spherical bearing providing a self-aligning coupling with the pylon assembly.
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公开(公告)号：US20170305566A1
公开(公告)日：2017-10-26
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 , B64C29/00 , F16H57/021 , B64C3/32 , B64D35/00 , B64C27/26 , F16H57/025 , 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.
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公开(公告)号：US20170259905A1
公开(公告)日：2017-09-14
申请号：US15601679
申请日：2017-05-22
Applicant: Bell Helicopter Textron Inc.
Inventor： James Everett Kooiman , George Ryan Decker , Keith Alan Stanney , Robert Mark Chris
Abstract: An airframe assembly for an aircraft includes a first airframe member having first and second skins with a large cell core and a solid insert joined therebetween. The solid insert has a side surface at least a portion of which is adjacent to the large cell core. The first airframe member has a first set of openings extending through the first skin, the solid insert and the second skin. The airframe assembly also includes a second airframe member having a second set of openings operable to be aligned with the first set of openings of the first airframe member. Each of a plurality of fasteners extends through one of the openings of the first set of openings and one of the openings of the second set of openings securably coupling the first airframe member to the second airframe member.
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公开(公告)号：US09663225B1
公开(公告)日：2017-05-30
申请号：US15417113
申请日：2017-01-26
Applicant: Bell Helicopter Textron Inc.
Inventor： James Everett Kooiman , George Ryan Decker , Andrew G. Baines , David R. Bockmiller , Erick Wayne Kohler
CPC classification number: B64C29/0033 , B64C27/22 , B64D35/00 , B64F5/40 , F16H1/006 , Y10T29/49318 , Y10T74/1966
Abstract: A drive system for a tiltrotor aircraft includes a first gearbox rotatably mounted to the airframe and rotatable about a longitudinal axis to operate the tiltrotor aircraft between helicopter and airplane modes. A second gearbox extends generally normal to the longitudinal axis of the first gearbox. A common shaft, rotatable about the longitudinal axis, transfers torque from an output gear of the second gearbox to an input gear of the first gearbox. A support assembly couples the second gearbox to the airframe and includes a fixed joint proximate the longitudinal axis, a first directional reacting joint remote from the longitudinal axis providing a first radial growth degree of freedom to the second gearbox and a second directional reacting joint remote from the longitudinal axis providing a second radial growth degree of freedom to the second gearbox that is not parallel with the first radial growth degree of freedom.
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Patent Agency Ranking
公开(公告)号：US20190389572A1
公开(公告)日：2019-12-26
申请号：US16015760
申请日：2018-06-22
Applicant: Bell Helicopter Textron Inc.
Inventor： Colton Gilliland , Jeffrey Williams , Michael E. Rinehart , James Kooiman , Mark Przybyla , Clegg Smith , Eric Stephen Olson , George Ryan Decker , David Russell Bockmiller
Abstract: A tiltrotor aircraft includes a propulsion system with a fixed engine and a rotatable proprotor. The engine is located on the top surface of the wing of the tiltrotor aircraft, and the rotatable proprotor assembly is also mounted on the top surface of the wing. The engine and proprotor assembly are connected via a series of one or more gearboxes that route the engine output from the engine to the proprotor.
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公开(公告)号：US20180305037A1
公开(公告)日：2018-10-25
申请号：US15496257
申请日：2017-04-25
Applicant: Bell Helicopter Textron Inc.
Inventor： James Everett Kooiman , Charles David Hogue , George Ryan Decker , Andrew G. Baines , Douglas Kirk Wolfe
Abstract: A fuel system for an aircraft includes a fuel cell having a plurality of sides including a first side and at least one deformable clip having a secured end and a free end. The secured end is coupled to the first side of the fuel cell and the free end overlapping the airframe of the aircraft such that the first side of the fuel cell is positioned adjacent to the airframe. The at least one deformable clip is deformable to allow the fuel cell to move independently of the airframe in response to an impact of the aircraft, thereby protecting the fuel cell from damage resulting from the impact.
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公开(公告)号：US09981750B2
公开(公告)日：2018-05-29
申请号：US15792686
申请日：2017-10-24
Applicant: Bell Helicopter Textron Inc.
Inventor： Jeffrey Matthew Williams , George Ryan Decker , James Everett Kooiman , Andrew G. Baines , Daniel J. Sweigard
CPC classification number: B64D27/26 , B64C3/32 , B64C27/22 , B64C27/26 , B64C29/0033 , B64D35/00 , B64D2027/266 , B64F5/40 , F16C17/022 , F16C17/26 , 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 an input gear of the spindle gearbox. Each of the inboard and outboard pedestals includes a spherical bearing providing a self-aligning coupling with the pylon assembly.
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公开(公告)号：US20180099758A1
公开(公告)日：2018-04-12
申请号：US15835617
申请日：2017-12-08
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 , B64C27/26 , B64C29/00 , F16H57/021 , F16H57/025 , 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 pedestal assembly for receiving a pylon assembly of a tiltrotor aircraft having a helicopter mode and an airplane mode, the tiltrotor aircraft having an airframe including a fuselage and a wing. The pedestal assembly includes an inboard pedestal supported by the airframe and positioned above the wing. The inboard pedestal includes an inboard bearing assembly disposed within an inboard pillow block housing. The pedestal assembly also includes an outboard pedestal supported by the airframe and positioned above the wing. The outboard pedestal includes an outboard bearing assembly disposed within an outboard pillow block housing. The inboard and outboard bearing assemblies are operable to receive the pylon assembly therein such that the pylon assembly is rotatably mounted between the inboard and outboard pedestals to selectively operate the tiltrotor aircraft between the helicopter mode and the airplane mode.
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公开(公告)号：US09783292B2
公开(公告)日：2017-10-10
申请号：US15497055
申请日：2017-04-25
Applicant: Bell Helicopter Textron Inc.
Inventor： James Everett Kooiman , George Ryan Decker , Andrew G. Baines , David R. Bockmiller , Erick Wayne Kohler
CPC classification number: B64C29/0033 , B64C27/22 , B64D35/00 , B64F5/40 , F16H1/006 , Y10T29/49318 , Y10T74/1966
Abstract: A support assembly for coupling a first gearbox to an airframe of an aircraft. The first gearbox has an output gear operable to transfer torque to an input gear of a second gearbox via a common shaft rotatable about a longitudinal axis. The support assembly includes a fixed joint proximate the longitudinal axis. A first directional reacting joint remote from the longitudinal axis provides a first radial growth degree of freedom to the first gearbox relative to the longitudinal axis. A second directional reacting joint remote from the longitudinal axis provides a second radial growth degree of freedom to the first gearbox relative to the longitudinal axis. The first radial growth degree of freedom is not parallel with the second radial growth degree of freedom such that the support assembly maintains the output gear of the first gearbox in substantial collinear alignment with the input gear of the second gearbox.
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