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公开(公告)号：US10279901B2
公开(公告)日：2019-05-07
申请号：US15272062
申请日：2016-09-21
Applicant: Bell Helicopter Textron Inc.
Inventor： Steven Ray Ivans , Brent Chadwick Ross
IPC: B64C29/00 , B64C39/02 , B64D27/02 , B64D33/02 , B64D33/04 , B64D35/04 , B64D35/08 , F16H35/00 , B64C3/18 , F16H1/20
Abstract: A propulsion system includes an engine disposed within a fuselage, a first gearbox coupled to the engine, a wing member having an upper wing skin and torque box formed by a first rib, a second rib, a first spar and second spar, a drive shaft coupled to the first gearbox and disposed within the wing member, a second gear box coupled to the drive shaft and disposed outboard from the second rib or inboard from the first rib, and a rotatable proprotor coupled to the second gear box. The rotatable proprotor includes a plurality of rotor blades, a rotor mast having a mast axis of rotation, and a proprotor gearbox coupled to the rotor mast. The proprotor gearbox is rotatable about a conversion axis, which intersects with the mast axis of rotation at a point within a central region of the torque box and above the upper wing skin.
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公开(公告)号：US10259560B2
公开(公告)日：2019-04-16
申请号：US15270053
申请日：2016-09-20
Applicant: Bell Helicopter Textron Inc.
Inventor： Steven Ray Ivans , Brent Chadwick Ross
Abstract: A modular payload system for an aircraft includes a modular bay recessed within the aircraft. The modular bay includes a modular bay interface. The modular payload system includes a plurality of payload modules each having a respective function and a payload interface adapted to connect to at least a portion of the modular bay interface. The plurality of payload modules are interchangeably insertable into the modular bay to enable the modular bay to support the functions of the plurality of payload modules.
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13.发明申请公开(公告)号：US20190009900A1
公开(公告)日：2019-01-10
申请号：US15642525
申请日：2017-07-06
Applicant: Bell Helicopter Textron Inc.
Inventor： Jeremy Chavez , Brent Chadwick Ross
Abstract: The present invention includes a rotorcraft drive system comprising: an engine positioned at an end of a wing between a mid-wing spar and an aft-wing spar; a spindle positioned forward from the engine, the spindle capable of rotation between a hover and forward flight position, wherein the spindle rotates about a rotation bearing on an inboard split rib and an outboard tip rib or in a cantilevered spindle configuration supported by the inboard tip rib; and a tilt axis driveshaft connected to the engine, wherein the tilt axis drive shaft connects to a plurality of gears and shafts that transmit power from the engine to a proprotor gear box when the spindle is in: a forward position, a hover position, and during a transition between the forward position and the hover position without loss of power to the proprotor gear box.
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14.发明申请公开(公告)号：US20180362180A1
公开(公告)日：2018-12-20
申请号：US15625452
申请日：2017-06-16
Applicant: Bell Helicopter Textron Inc.
Inventor： Brent Chadwick Ross , Daniel B. Robertson
Abstract: The present invention includes a rotorcraft drive system, method, and aircraft comprising a fixed engine; a rotating spindle that rotates a proprotor gearbox and rotor pylon between a hover and forward flight position, wherein the rotating spindle rotates about a rotation bearings on two inboard ribs of a wing member; and an interconnect drive shaft connected to the fixed engine, wherein the interconnect drive shaft passes through an aft cove of the wing member and connects to the engine via a forward-aft drive shaft, wherein the forward-aft drive shaft is connected to the proprotor gearbox to provide power to a proprotor.
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公开(公告)号：US20180079487A1
公开(公告)日：2018-03-22
申请号：US15271721
申请日：2016-09-21
Applicant: Bell Helicopter Textron, Inc.
Inventor： Steven Ray Ivans , Brent Chadwick Ross
Abstract: An aircraft has a wing, a pylon carried by the wing, at least one of a rotor system component and a drive system component disposed within the pylon, and a wing extension carried by the at least one of a rotor system component and drive system component, wherein the wing extension is foldable relative to the pylon to selectively reduce an overall space occupied by the aircraft.
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Patent Agency Ranking
公开(公告)号：US11238200B2
公开(公告)日：2022-02-01
申请号：US16293425
申请日：2019-03-05
Applicant: Bell Helicopter Textron Inc.
Inventor： Michael McNair , Brent Chadwick Ross , Christopher Stroncek , Kip Gregory Campbell , Joseph Scott Drennan , Brett Zimmerman , Carey Cannon
Abstract: A method of operating a targeting system simulation tool (TSST) includes providing a TSST configured to receive an obstacle/effect parameterization, a simulation parameterization, a sensor parameterization, an aircraft parameterization, and an autonomy parameterization. The method further includes receiving by the TSST, at least one of each of an obstacle/effect parameterization and a simulation parameterization. The method further includes receiving by the TSST, either (1) a sensor parameterization or (2) an aircraft parameterization. The method further includes operating the TSST to apply the provided ones of the obstacle/effect parameterization, simulation parameterization, sensor parameterization, and aircraft parameterization to generate a value, value range, or value limit for the unprovided aircraft parameterization or unprovided sensor parameterization.
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公开(公告)号：US10343762B2
公开(公告)日：2019-07-09
申请号：US15272141
申请日：2016-09-21
Applicant: Bell Helicopter Textron, Inc.
Inventor： Brent Chadwick Ross , Steven Ray Ivans
Abstract: An aircraft has a fuselage, an engine disposed within the fuselage, a rotatable wing disposed above the fuselage and selectively rotatable about a wing rotation axis, and a plurality of interconnect driveshafts disposed within the rotatable wing, and at least one drive system component that is connected between the engine and the interconnect driveshaft is disposed along the wing rotation axis.
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公开(公告)号：US20180079503A1
公开(公告)日：2018-03-22
申请号：US15272062
申请日：2016-09-21
Applicant: Bell Helicopter Textron Inc.
Inventor： Steven Ray Ivans , Brent Chadwick Ross
CPC classification number: B64C29/0033 , B64C3/18 , B64C39/024 , B64C2201/104 , B64C2201/108 , B64C2201/165 , B64D27/02 , B64D33/02 , B64D33/04 , B64D35/04 , B64D35/08 , F16H1/203 , F16H35/008
Abstract: A propulsion system includes an engine disposed within a fuselage, a first gearbox coupled to the engine, a wing member having an upper wing skin and torque box formed by a first rib, a second rib, a first spar and second spar, a drive shaft coupled to the first gearbox and disposed within the wing member, a second gear box coupled to the drive shaft and disposed outboard from the second rib or inboard from the first rib, and a rotatable proprotor coupled to the second gear box. The rotatable proprotor includes a plurality of rotor blades, a rotor mast having a mast axis of rotation, and a proprotor gearbox coupled to the rotor mast. The proprotor gearbox is rotatable about a conversion axis, which intersects with the mast axis of rotation at a point within a central region of the torque box and above the upper wing skin.
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公开(公告)号：US20180079484A1
公开(公告)日：2018-03-22
申请号：US15272141
申请日：2016-09-21
Applicant: Bell Helicopter Textron, Inc.
Inventor： Brent Chadwick Ross , Steven Ray Ivans
CPC classification number: B64C3/56 , B64C3/385 , B64C5/02 , B64C5/10 , B64C7/02 , B64C11/28 , B64C27/14 , B64C29/0033 , B64C39/024 , B64C2201/02 , B64C2201/108
Abstract: An aircraft has a fuselage, an engine disposed within the fuselage, a rotatable wing disposed above the fuselage and selectively rotatable about a wing rotation axis, and a plurality of interconnect driveshafts disposed within the rotatable wing, and at least one drive system component that is connected between the engine and the interconnect driveshaft is disposed along the wing rotation axis.
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公开(公告)号：US20180079482A1
公开(公告)日：2018-03-22
申请号：US15270053
申请日：2016-09-20
Applicant: Bell Helicopter Textron Inc.
Inventor： Steven Ray Ivans , Brent Chadwick Ross
CPC classification number: B64C1/22 , B64C1/00 , B64C2201/126 , B64C2211/00 , B64D1/02 , B64D1/04 , B64D1/06 , B64D7/00 , B64D37/04
Abstract: A modular payload system for an aircraft includes a modular bay recessed within the aircraft. The modular bay includes a modular bay interface. The modular payload system includes a plurality of payload modules each having a respective function and a payload interface adapted to connect to at least a portion of the modular bay interface. The plurality of payload modules are interchangeably insertable into the modular bay to enable the modular bay to support the functions of the plurality of payload modules.
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