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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：US11472533B2
公开(公告)日：2022-10-18
申请号：US16732106
申请日：2019-12-31
Applicant: Bell Textron Inc.
Inventor： Elizabeth Feeley , Karl Schroeder
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 hub may be configured to support a motor. The duct ring defines a trailing edge. The duct ring is coupled to each of the plurality of stators such that all or substantially all of each of the plurality of stators is located aft of the trailing edge of the duct ring.
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公开(公告)号：US20220177121A1
公开(公告)日：2022-06-09
申请号：US17116726
申请日：2020-12-09
Applicant: Bell Textron Inc.
Inventor： Alexander Dang Quang Truong , Karl Schroeder , Michael John Ryan
Abstract: An exemplary ducted fan includes a duct having a central longitudinal axis, a rotor hub and stator hub extending along the central longitudinal axis, rotor blades extending from the rotor hub, each of the rotor blades operable to rotate about its own pitch-change axis, the pitch-change axes lying in a rotor plane that is generally perpendicular to the central longitudinal axis, each of the rotor blades having a rotor trailing edge and a rotor chord length, stators extending from the stator hub to an interior surface of the duct, each of the stators having a stator leading edge and a stator thickness, and a first separation between the rotor plane and the stator leading edge of not less than approximately 1.5 times the stator thickness.
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公开(公告)号：US20210197964A1
公开(公告)日：2021-07-01
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：US20210197957A1
公开(公告)日：2021-07-01
申请号：US16732106
申请日：2019-12-31
Applicant: Bell Textron Inc.
Inventor： Elizabeth Feeley , Karl Schroeder
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 hub may be configured to support a motor. The duct ring defines a trailing edge. The duct ring is coupled to each of the plurality of stators such that all or substantially all of each of the plurality of stators is located aft of the trailing edge of the duct ring.
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Patent Agency Ranking
公开(公告)号：US20210199022A1
公开(公告)日：2021-07-01
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：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：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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