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公开(公告)号：US20210139139A1
公开(公告)日：2021-05-13
申请号：US16679018
申请日：2019-11-08
Applicant: Bell Textron Inc.
Inventor： Karl Schroeder , Timothy Brian Carr , David G. Carlson , Kevin Stump , William Anthony Amante , Joseph Richard Carpenter, JR.
Abstract: A duct for a ducted-rotor aircraft may include an internal structure and an aerodynamic exterior skin that is adhesively bonded to the internal structure. The skin may include a leading-edge portion disposed at an inlet of the duct and an inner portion disposed along an interior of the duct. The inner portion of the skin may be bonded to the internal structure with a first bondline of adhesive and the leading-edge portion of the skin may be bonded to the inner portion of the skin with a second bondline of adhesive. One or both of the first and second bondlines of adhesive may be of non-uniform thickness to take up tolerance stackups between the inner portion of the skin, the leading-edge portion of the skin, and the internal structure.
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公开(公告)号：US20210139131A1
公开(公告)日：2021-05-13
申请号：US16679117
申请日：2019-11-08
Applicant: Bell Textron Inc.
Inventor： Karl Schroeder , Christopher Marion Johnson , Joseph Richard Carpenter, JR. , David G. Carlson
Abstract: A hub assembly for a ducted-rotor aircraft includes a plurality of stator supports, a first integral fitting that attaches to first ends of the stator supports, and a second integral fitting that attaches to second ends of the stator supports. The first fitting includes a plurality of motor attachment portions configured to locate and support a motor of the ducted-rotor aircraft, a plurality of fairing mounts configured to support attachment of an aerodynamic fairing to the hub assembly, and a plurality of stator locators configured to locate respective ones of the plurality of stator supports for attachment to the hub assembly. The first fitting has a body portion with an annular wall that supports the motor attachment portions, the fairing mounts, and the stator locators. The first fitting may be fabricated as a monolith that includes the body portion, motor attachment portions, fairing mounts, and stator locators.
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公开(公告)号：US20210139130A1
公开(公告)日：2021-05-13
申请号：US16679121
申请日：2019-11-08
Applicant: Bell Textron Inc.
Inventor： Karl Schroeder , William Anthony Amante , Joseph Richard Carpenter, JR. , Christopher Marion Johnson
Abstract: A duct for a ducted-rotor aircraft may include internal structural components such as a spindle that is supported by a fuselage of the aircraft, first and second annular spars that are attached to an end of the spindle, a central hub that supports a motor of the aircraft, a plurality of stators that extend from the central hub to the second spar, and a plurality of ribs that are attached to the first spar and the second spar at respective opposed ends. The spindle may include an attachment interface to which the first and second spars are attached. The attachment interface may be disposed at the second end of the spindle. The attachment interface may define first and second arc-shaped planar surfaces to which the first and second spars, respectively, are attached.
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公开(公告)号：US10995846B2
公开(公告)日：2021-05-04
申请号：US15704355
申请日：2017-09-14
Applicant: Bell Helicopter Textron Inc.
Inventor： Scott David Poster
IPC: F16H57/029 , F16H57/04 , B64C27/14 , B64C27/12 , F16J15/447
Abstract: The present invention includes a system, method and kit for preventing or reducing water penetration of a gearbox, the system including: a fan or impeller coupled to the gearbox; and a hub coupled to the fan and shaped to provide a labyrinth seal that prevents or reduces water penetration into the gearbox.
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公开(公告)号：US10994855B2
公开(公告)日：2021-05-04
申请号：US16399537
申请日：2019-04-30
Applicant: Bell Helicopter Textron Inc.
Inventor： William Benjamin Johns , Jason William Minter
Abstract: In some examples, an aircraft comprises a motorized module. The motorized module comprises a motor and a first coil. The motor is to operate equipment onboard the aircraft and generates vibrations during operation. The first coil is operable to wirelessly transmit power to a separate module onboard the aircraft based on electromagnetic induction between the first coil and a second coil in a separate module, and wirelessly transfer data with the separate module via the second coil based on the electromagnetic induction, the data being associated with the motor. A gap separates the motorized module and the separate module. The gap isolates the separate module from the vibrations.
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Patent Agency Ranking
公开(公告)号：US10994852B2
公开(公告)日：2021-05-04
申请号：US15946439
申请日：2018-04-05
Applicant: Bell Helicopter Textron Inc.
Inventor： Steven R. Ivans , Terry L. Gibson
Abstract: An embodiment of the present invention provides a blocking door that is pivotally disposed on a fixed nacelle of a tiltrotor aircraft for pivoting between a stowed position when a proprotor pylon is in the substantially horizontal position and a protective blocking position in front of the proprotor pylon when the proprotor pylon is positioned in the non-horizontal position. In other aspects, there is provided a blocking door and a method of reducing infrared and/or radar signatures of rotorcraft with a rotatable proprotor.
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公开(公告)号：US20210122464A1
公开(公告)日：2021-04-29
申请号：US16661118
申请日：2019-10-23
Applicant: Bell Textron Inc.
Inventor： Colton James Gilliland , Russell Lee Mueller , Tyson T. Henry
Abstract: A drivetrain for an aircraft includes an engine, a driveshaft receiving rotational energy from the engine and a gearbox including a planetary gear system receiving rotational energy from the driveshaft. The planetary gear system includes a sun gear, planet gears, a ring gear and an integral carrier forming flexured carrier posts. Each flexured carrier post supports a respective one of the planet gears and has a fixed proximal end and a cantilevered distal end. The planetary gear system includes flexured roller races, each having a fixed end and a cantilevered end. The fixed end of each flexured roller race is coupled to the cantilevered distal end of a respective flexured carrier post. The planet gears engage with the flexured roller races to rotate about the flexured carrier posts. The cantilevered ends of the flexured roller races experience cantilevered motion to absorb loads from the planet gears.
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公开(公告)号：US10988245B2
公开(公告)日：2021-04-27
申请号：US15811002
申请日：2017-11-13
Applicant: Bell Helicopter Textron Inc.
Inventor： Chandrashekar Rudraswamy
Abstract: A tiltrotor assembly has a central hub with a plurality of rotor blades extending therefrom and is configured to rotate about a mast axis to generate lift in a hover position. The central hub is configured to rotate about a tilt axis between the hover position and a forward-flight position such that rotation about the mast axis generates forward thrust. The central hub is surrounded by a segmented duct that includes a thin rotatable inner ring and a wide fixed outer ring. The inner ring is configured to rotate with the central hub about the tilt axis leaving the wide outer ring in a generally horizontal position.
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公开(公告)号：US20210116015A1
公开(公告)日：2021-04-22
申请号：US16657166
申请日：2019-10-18
Applicant: Bell Textron Inc.
Inventor： Douglas Robert MUELLER
Abstract: An example of an emergency lubrication system for an aircraft includes a lubricant tank configured to supply a lubricant to a gearbox of the aircraft, a tube coupled between the lubricant tank and the gearbox and comprising a check ball disposed within the tube, a first lubricant line coupled to the tube and a first inlet of the gearbox, and a second lubricant line coupled to the tube and a second inlet of the gearbox.
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公开(公告)号：US20210101676A1
公开(公告)日：2021-04-08
申请号：US16593998
申请日：2019-10-05
Applicant: Bell Textron Inc.
Inventor： Karl Schroeder , William Anthony Amante , Joseph Richard Carpenter, JR. , David G. Carlson
Abstract: An annular spar for a ducted-rotor of an aircraft may be fabricated from composite material, such as carbon-fiber-reinforced plastic (CFRP). The spar may include an annular plate, a first circumferential flange that extends from an outer edge of the plate, and a second circumferential flange that extends from an inner edge of the plate. The first and second circumferential flanges may taper inwardly toward a center axis of the spar. The spar may be constructed of a plurality of layers of CFRP. One or more of the layers may be fabricated from a single ply of CFRP, and one or more other layers may be fabricated from a plurality of plies of CFRP. The spar may exhibit a coefficient of thermal expansion (CTE) that allows an associated tip gap to remain essentially constant throughout a range of operating temperatures.
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