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公开(公告)号：US10793275B2
公开(公告)日：2020-10-06
申请号：US16004159
申请日：2018-06-08
Applicant: Bell Helicopter Textron Inc.
Inventor： Jeremy Robert Chavez , Brent Chadwick Ross
Abstract: Embodiments are directed to an aircraft, such as a tiltrotor, having an internal payload storage area. A rotatable deployment system is mounted within the payload storage area. The rotatable deployment system comprises a frame that is configured to rotate between a stowed position and a deployment position. Two extendible arms are attached to the frame, wherein each extendible arm is configured to move in opposite directions between a retracted position and a plurality of extended positions. Each extendible arm has a fixed end and a moving end. A payload mounting point on each moving end. The payload mounting point allows a payload to pan and tilt in azimuth and elevation.
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公开(公告)号：US10654580B2
公开(公告)日：2020-05-19
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：US20180043986A1
公开(公告)日：2018-02-15
申请号：US15232465
申请日：2016-08-09
Applicant: Bell Helicopter Textron Inc.
Inventor： David L. Miller , Brent Chadwick Ross
CPC classification number: B64C7/02 , B64C27/14 , B64C29/0033 , B64D33/02 , B64D2033/0253 , B64D2033/0293
Abstract: The present invention includes an air flow bypass for a tiltrotor engine comprising: a ram air inlet comprising bypass door(s) capable of at least partially or fully blocking a ram air flow through the ram air inlet; a barrier filter inlet positioned in a side, a bottom, and/or a top of a tiltrotor engine nacelle; a filter plenum; a selector duct comprising one or more openings; and one or more selector duct doors or covers over the one or more openings; wherein the barrier filter inlet, the filter plenum, the one or more openings in the selector duct, the selector duct, and an engine are in fluid communication and the bypass door(s) in the ram inlet are closed and the barrier filter inlet provides filtered air flow to the engine when the aircraft is in hover operations.
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公开(公告)号：US10882598B2
公开(公告)日：2021-01-05
申请号：US15951539
申请日：2018-04-12
Applicant: Bell Helicopter Textron Inc.
Inventor： Jeremy Robert Chavez , Brent Chadwick Ross
Abstract: Embodiments are directed to systems and methods for a sliding door in a pressurized aircraft. In one embodiment, an aircraft comprises a fuselage having a door opening, and a door configured to slide into the door opening from within the fuselage, the door held in a closed position in the door opening by excess air pressure within the fuselage during operation of the aircraft.
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公开(公告)号：US10689106B2
公开(公告)日：2020-06-23
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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Patent Agency Ranking
公开(公告)号：US20200026811A1
公开(公告)日：2020-01-23
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：US10414483B2
公开(公告)日：2019-09-17
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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公开(公告)号：US10023296B2
公开(公告)日：2018-07-17
申请号：US15232465
申请日：2016-08-09
Applicant: Bell Helicopter Textron Inc.
Inventor： David L. Miller , Brent Chadwick Ross
Abstract: The present invention includes an air flow bypass for a tiltrotor engine comprising: a ram air inlet comprising bypass door(s) capable of at least partially or fully blocking a ram air flow through the ram air inlet; a barrier filter inlet positioned in a side, a bottom, and/or a top of a tiltrotor engine nacelle; a filter plenum; a selector duct comprising one or more openings; and one or more selector duct doors or covers over the one or more openings; wherein the barrier filter inlet, the filter plenum, the one or more openings in the selector duct, the selector duct, and an engine are in fluid communication and the bypass door(s) in the ram inlet are closed and the barrier filter inlet provides filtered air flow to the engine when the aircraft is in hover operations.
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公开(公告)号：US20190375506A1
公开(公告)日：2019-12-12
申请号：US16004159
申请日：2018-06-08
Applicant: Bell Helicopter Textron Inc.
Inventor： Jeremy Robert Chavez , Brent Chadwick Ross
IPC: B64D7/06
Abstract: Embodiments are directed to an aircraft, such as a tiltrotor, having an internal payload storage area. A rotatable deployment system is mounted within the payload storage area. The rotatable deployment system comprises a frame that is configured to rotate between a stowed position and a deployment position. Two extendible arms are attached to the frame, wherein each extendible arm is configured to move in opposite directions between a retracted position and a plurality of extended positions. Each extendible arm has a fixed end and a moving end. A payload mounting point on each moving end. The payload mounting point allows a payload to pan and tilt in azimuth and elevation.
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公开(公告)号：US20190315448A1
公开(公告)日：2019-10-17
申请号：US15951539
申请日：2018-04-12
Applicant: Bell Helicopter Textron Inc.
Inventor： Jeremy Robert Chavez , Brent Chadwick Ross
Abstract: Embodiments are directed to systems and methods for a sliding door in a pressurized aircraft. In one embodiment, an aircraft comprises a fuselage having a door opening, and a door configured to slide into the door opening from within the fuselage, the door held in a closed position in the door opening by excess air pressure within the fuselage during operation of the aircraft.
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