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公开(公告)号：US11305867B2
公开(公告)日：2022-04-19
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：US11480072B2
公开(公告)日：2022-10-25
申请号：US16732094
申请日：2019-12-31
Applicant: Bell Textron Inc.
Inventor： Elizabeth Feeley , Karl Schroeder , Joseph Richard Carpenter, Jr.
Abstract: A duct for a ducted-rotor aircraft includes a hub, a duct ring, and a plurality of stators that extend outward from the hub. The duct ring defines a trailing edge. The duct includes one or more fittings, such as a system of fittings. Each fitting has a body that defines a first attachment interface that is configured to couple to structure of the duct ring and a second attachment interface that is configured to couple to one of the plurality of stators. The first and second attachment interfaces are spaced from each other such that when the fittings are coupled to the duct ring and the plurality of stators, all or substantially all of each of the plurality of stators are located aft of the trailing edge of the duct ring.
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公开(公告)号：US11643186B2
公开(公告)日：2023-05-09
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
CPC classification number: B64C11/001 , B64C11/02 , B64C11/46 , B64D27/26 , B64C29/0033 , B64D2027/264
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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Patent Agency Ranking
公开(公告)号：US11548630B2
公开(公告)日：2023-01-10
申请号：US16732065
申请日：2019-12-31
Applicant: Bell Textron Inc.
Inventor： William Anthony Amante , Karl Schroeder , Joseph Richard Carpenter, Jr. , Timothy Brian Carr
Abstract: A ducted-rotor aircraft includes a fuselage, first and second ducts, and a spindle that is coupled to the fuselage. Each duct includes a rotor having a plurality of blades. The first and second ducts are coupled to opposed ends of the spindle. The spindle is rotatably coupled to the fuselage with first and second bearings. The first bearing is configured to react to radial loads and the second bearing is configured to react to both radial and axial loads. The spindle includes a shaft, first and second fittings secured to opposed ends of the shaft, and first and second attachment interfaces that are attachable to the first and second ducts. The attachment interfaces may be integral with the fittings. Alternatively, the fittings may be configured to be secured to the attachment interfaces with fasteners.
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公开(公告)号：US11453491B2
公开(公告)日：2022-09-27
申请号：US17173860
申请日：2021-02-11
Applicant: Bell Textron Inc.
Inventor： Elizabeth Feeley , Karl H. Schroeder , George Matthew Thompson , Michael Mark Attaway , Joseph Richard Carpenter, Jr.
Abstract: One embodiment is a rotor system comprising a duct ring; a hub disposed centrally to the duct ring; first and second stators each connected between the duct ring and the hub; first and second control vanes rotatably connected to the first and second stators, respectively; a structural hoop having a first end connected to the first control vane and a second end connected to the second control vane, the structural hoop for translating rotation of the first control vane about a vane axis to the second control vane; and a mechanism for restricting at least one of forward-aft movement and side-to-side movement of the structural hoop relative to the duct ring.
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公开(公告)号：US11685502B2
公开(公告)日：2023-06-27
申请号：US16916732
申请日：2020-06-30
Applicant: Bell Textron Inc.
Inventor： Joseph Richard Carpenter, Jr. , Timothy Brian Carr , Nicholas Hou , William Anthony Amante
CPC classification number: B64C1/061 , B64C1/40 , B64C2001/0081
Abstract: A replaceable web structure for an aircraft frame is described and includes a plurality of structural members fabricated from a first type of material, the replaceable web structure comprising a plurality of web members fabricated from thin sheets of a second type of material, wherein each of the web members is fastened to a web frame of one of the structural members to replace a web portion of the one of the structural members; wherein the second type of material is stronger than the first type of material such that one of the sheets of the second type of material is lighter weight than a sheet of equal strength of the first type of material.
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公开(公告)号：US11560222B2
公开(公告)日：2023-01-24
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：US11242139B2
公开(公告)日：2022-02-08
申请号：US16732076
申请日：2019-12-31
Applicant: Bell Textron Inc.
Inventor： Karl Schroeder , Joseph Richard Carpenter, Jr. , Brett Zimmerman
Abstract: A ducted-rotor aircraft includes a fuselage, one or more ducts, and a spindle that rotatably couples the one or more ducts to the fuselage. Each duct includes a hub that is configured to support a rotor, a plurality of stators that are coupled to the hub, a duct ring that is coupled to the plurality of stators, and a fitting that is coupled to a first stator of the plurality of stators. The fitting has a tubular collar that defines a first aperture that extends through the fitting. The collar is configured to receive a portion of the spindle. The first stator includes a rib that is spaced inward from the fitting and that defines a second aperture that is aligned with the first aperture and that is configured to receive an end of the spindle.
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