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公开(公告)号：US20210332879A1
公开(公告)日：2021-10-28
申请号：US16861069
申请日：2020-04-28
Applicant: Bell Textron Inc.
Inventor： Amanda Christine SAVAGE , Charles Hubert SPELLER
Abstract: A gearbox system for a rotorcraft includes a gearbox housing, an oil pump receiving bore formed into the gearbox housing and having formed therein a first opening having a first diameter and a second opening, and an oil pump positioned within the oil pump receiving bore. The second opening is bounded by a lip that extends radially into the second opening, the second opening having a second diameter that is smaller than the first diameter.
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公开(公告)号：US20210316849A1
公开(公告)日：2021-10-14
申请号：US16846371
申请日：2020-04-12
Applicant: Bell Textron Inc.
Inventor： George Matthew Thompson , Jonathan Andrew Knoll , Nicholas Carlson
Abstract: A rotor blade retention device for use in an aircraft having a plurality of blades includes an array of cavities, each cavity adapted to receive a portion of a tension-torsion strap therein. Each cavity is oriented such that, when the portion of the tension-torsion strap is received therein, a central plane of the tension-torsion strap is inclined relative to a blade plane of rotation defined by the plurality of blades. The retention device may have a body that defines an aperture adapted to receive a portion of a rotor mast of the aircraft, may comprise a rotor mast of the aircraft, or may comprise first and second plates that cooperate to form the array of cavities and that are adapted to receive a portion of the rotor mast of the aircraft.
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公开(公告)号：US20210316843A1
公开(公告)日：2021-10-14
申请号：US17308309
申请日：2021-05-05
Applicant: Bell Textron Inc.
Inventor： Derek William HEARD , Richard Theodore PERRYMAN , Nathan Craig CLARK , Joshua Andrew EMRICH , Yann LAVALLEE , Ralph Michael GANNARELLI
IPC: B64C17/00
Abstract: A movable ballast system for an aircraft includes first and second ballast docks secured to the aircraft. The first ballast dock includes a first housing and a first ballast tray secured within the first housing. The first ballast tray includes a plurality of channels. The second ballast dock is positioned aft of a CG of the aircraft and includes a second housing and a second ballast tray secured within the second housing. The second ballast tray includes a plurality of channels. The movable ballast system includes a plurality of movable ballasts, each movable ballast of the plurality of movable ballasts being configured to fit within at least one channel of each of the plurality of channels of the first and second ballast trays.
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公开(公告)号：US20210309371A1
公开(公告)日：2021-10-07
申请号：US16841050
申请日：2020-04-06
Applicant: Bell Textron Inc.
Inventor： James Everett Kooiman , Jeffrey Matthew Williams , Clegg Benjamin Brian Smith , Michael E. Rinehart , Franklin Foster Caldwell , Tjepke Heeringa
Abstract: A system is described and includes a rack for carrying payload disposed in a payload bay; and a payload extension assembly for affecting linear translation of the rack between a first position in which the rack is fully retracted within the payload bay and a second position in which the payload extension assembly is fully extended and the rack is supported outside the payload bay. The payload extension assembly comprises forward and aft tracks respectively attached to forward and aft walls of the payload bay; a first stage for providing linear translation of the rack relative to the forward and aft tracks; and a second stage for providing linear translation of the rack relative to the first stage. The system further comprises a payload actuator system for selectively causing the rack extension assembly to move the rack between the first and second positions.
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公开(公告)号：US20210276702A1
公开(公告)日：2021-09-09
申请号：US16808818
申请日：2020-03-04
Applicant: Bell Textron Inc.
Inventor： William Kyle Heironimus , Stephen Yibum Chung
Abstract: One embodiment is an electric drive system for an aircraft including a motor, a gear box associated with the motor, and a cooling fan for drawing air into the unit across an electronic component to cool the electronic component and for expelling air into an oil cooler for cooling oil contained therein. The electric drive system further includes an oil distribution system for distributing oil cooled by the oil cooler to at least one motor and at least one gearbox, the distributed oil being used to cool the motor and the gearbox, a reservoir for collecting the distributed oil after it has been used to cool the motor and the gearbox, and at least one structural element for retaining the motor, gearbox, the cooling fan, the oil distribution system, and the reservoir together as a unit.
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Patent Agency Ranking
公开(公告)号：US20210270312A1
公开(公告)日：2021-09-02
申请号：US16806205
申请日：2020-03-02
Applicant: Bell Textron Inc.
Abstract: An exemplary adjustable length link includes a first rod end having a body with a threaded socket, a second rod end having a threaded shaft and a sleeve having external threads cooperative with the threaded socket and a bore with internal threads cooperative with the threaded shaft.
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公开(公告)号：US20210269170A1
公开(公告)日：2021-09-02
申请号：US16804137
申请日：2020-02-28
Applicant: Bell Textron Inc.
Inventor： Kip Gregory CAMPBELL
Abstract: An exemplary method to determine an airspeed and an angle of attack of a propeller powered vehicle includes determining the power delivered to the propeller, the air density, a propeller power coefficient, an advance ratio for the propeller, and the airspeed using the advance ratio and determining the angle of attack using the airspeed.
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公开(公告)号：US20210269148A1
公开(公告)日：2021-09-02
申请号：US16804357
申请日：2020-02-28
Applicant: Bell Textron Inc.
Inventor： Kyle Thomas Cravener
Abstract: Embodiments are directed to a propulsion assembly for an aircraft. The propulsion assembly comprises a mast, a hub assembly coupled to the mast and having a gimballing degree of freedom relative to the mast, the hub assembly having an inner hub wall spaced part from the mast, a gimbal lock positioned about the mast, the gimbal lock configured to fit between the inner hub wall and the mast in an engaged position, and an over-center locking mechanism coupled to the gimbal lock. The gimbal lock is movable between a disengaged position and the engaged position relative to the hub assembly. The gimbal lock enables the gimballing degree of freedom in the disengaged position and disables the gimballing degree of freedom in the engaged position. The over-center locking mechanism is configured to move the gimbal lock between the engaged position and the disengaged position.
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公开(公告)号：US11104414B2
公开(公告)日：2021-08-31
申请号：US16590223
申请日：2019-10-01
Applicant: Bell Textron Inc.
Inventor： George Matthew Thompson , Jonathan Knoll , Paul Sherrill
Abstract: A rotor assembly has a rotor hub having a unitary structure. The rotor assembly further includes a unitary crosshead having a first upper tab and a first lower tab located vertically below the first upper tab. The first upper tab and the first lower tab define a slot therebetween to accept a first pin of the first rotor blade. A second upper tab and a second lower tab located vertically below the second upper tab define a slot therebetween to accept a second pin of the second rotor blade. A first recess is provided between the first lower tab and the second lower tab so that the crosshead comprises no material directly between at least a portion of the first lower tab and the second lower tab along at least one straight path.
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公开(公告)号：US20210253259A1
公开(公告)日：2021-08-19
申请号：US17225018
申请日：2021-04-07
Applicant: Bell Textron Inc.
Inventor： Troy C. Schank
Abstract: A hybrid power system for a vertical takeoff and landing (“VTOL”) aircraft including a first power source operable to provide a power output for at least a forward flight mode; and a second power source configured to provide a high specific power output for an altitude adjustment flight mode, the second power source including an auxiliary gas generator coupled to a turbine and a drive system. In other aspects, there is provided a VTOL aircraft and methods for providing power to a VTOL aircraft.
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