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公开(公告)号:US10941683B2
公开(公告)日:2021-03-09
申请号:US15705803
申请日:2017-09-15
发明人: Scott David Poster
摘要: A removable oil filter system includes an oil filter mount, an oil filter element removably connected to the oil filter mount, an impending-bypass indicator connected to the oil filter mount and in fluid communication with an oil in the oil filter system, and a full-bypass indicator in fluid communication with the oil filter mount. The impending-bypass indicator is capable of reporting an impending-bypass condition of the oil filter system. The full-bypass indicator is capable of reporting a full-bypass condition of the oil filter system.
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公开(公告)号:US10938172B2
公开(公告)日:2021-03-02
申请号:US16394057
申请日:2019-04-25
申请人: CR FLIGHT L.L.C.
IPC分类号: H01R39/08 , B64D27/24 , H02K1/04 , H02K7/10 , H02K13/00 , H02K16/02 , H02K23/60 , B64C11/48 , B64C27/10 , B64C27/12
摘要: A high current and RPM-capable slip ring assembly for use in a selected application for transferring electricity between an exterior environment and an interior environment that includes multiple electrical conduction assemblies with each having a fixed exterior electrical connection disk and rotating interior electrical connection disk mounted around a non-electrically conducting spindle that has a central aperture and a central axle running through the center of the spindle with one end of the central axle connected to the selected application and the other end of the central axle connect to a supporting structure mount and an oiled porous/sintered disk sandwiched around the spindle between the interior and exterior electrical connection disks of each conduction assembly to allow easy rotation between each exterior electrical connection disk and each rotating interior electrical connection disk.
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公开(公告)号:US10914381B2
公开(公告)日:2021-02-09
申请号:US16055524
申请日:2018-08-06
申请人: Ratier-Figeac SAS
发明人: Bertrand Prouzet
IPC分类号: F16J15/00 , B64C27/12 , B60T1/06 , B60T11/236 , B64C27/00 , F16D65/18 , F16D65/847 , F16J15/06 , F16J15/3268 , F16J15/56 , F16D121/02 , F16D125/08 , F16D121/06 , F16D55/00
摘要: New methods and devices are described that are aimed at preventing the outbreak of fire in a hydraulic rotor brake. These methods and devices can be used in the rotor brake of a helicopter and comprise a first and second seal, with a drain groove positioned in between these two seals to drain leaked fluid away from the hot parts of the brake. In the brakes described, the second seal is positioned closer to the heat sink of the brake than the first seal. The drain groove is also connected via a channel or channels to a drain outlet or outlets.
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公开(公告)号:US10830333B2
公开(公告)日:2020-11-10
申请号:US15967935
申请日:2018-05-01
发明人: Scott David Poster
摘要: A gearbox filler assembly includes a cylindrical insert attached to an interior of a port disposed within a housing of the gearbox. The cylindrical insert has a first end disposed within the port, a second end extending outward from the port and is configured to receive a detachable filler cap, a retaining lip around at least a portion of a first interior circumference proximate to the first end, and a retaining slot around at least a second interior circumference between the retaining lip and the second end. A retaining ring is detachably coupled within the retaining slot. A cylindrical baffle is detachably retained between the retaining ring and the retaining lip.
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公开(公告)号:US20200339260A1
公开(公告)日:2020-10-29
申请号:US16920017
申请日:2020-07-02
申请人: Bell Textron Inc.
IPC分类号: B64C39/06 , B64C11/28 , B64C27/50 , B64C29/00 , B64C3/10 , B64C27/08 , B64C27/12 , B64D27/24 , B64D31/00 , B64C29/02 , B64C1/06 , B64C39/02
摘要: An aircraft includes a closed wing, a fuselage at least partially disposed within a perimeter of the closed wing, and one or more spokes coupling the closed wing to the fuselage. A source of electric power is disposed within or attached to the closed wing, fuselage or one or more spokes. A plurality of electric motors are disposed within or attached to the one or more spokes in a distributed configuration. Each electric motor is connected to the source of electric power. A propeller is operably connected to each of the electric motors and proximate to a leading edge of the one or more spokes. One or more processors are communicably coupled to the plurality of electric motors. A longitudinal axis of the fuselage is substantially vertical in vertical takeoff and landing and stationary flight, and substantially in a direction of a forward flight in a forward flight mode.
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公开(公告)号:US10800514B2
公开(公告)日:2020-10-13
申请号:US16043758
申请日:2018-07-24
发明人: Carmine Lisio
摘要: Herein provided are methods and systems for controlling operation a first propeller of an aircraft, the first propeller associated with a first engine, the aircraft further comprising a second propeller associated with a second engine. A first requested engine power for the first engine is obtained. A second requested engine power for the second engine is obtained. The first propeller is synchronized with the second propeller by setting a first propeller command for the first propeller based on the first and second requested engine power, and the first propeller command is sent for the first propeller.
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公开(公告)号:US20200307778A1
公开(公告)日:2020-10-01
申请号:US16793060
申请日:2020-02-18
申请人: Nidec Corporation
摘要: A motor mounted on a drone includes a rotor including a propeller mounting portion with a propeller detachably attached, the rotor being rotatable about a central axis, a stator radially facing the rotor with a gap therebetween, and an auto-balancer capable of automatically correcting dynamic balance of the rotor.
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公开(公告)号:US10788088B2
公开(公告)日:2020-09-29
申请号:US16274520
申请日:2019-02-13
申请人: Bell Textron Inc.
IPC分类号: F16D41/07 , B64C27/12 , F16D1/10 , B64D35/08 , F16D121/04
摘要: A selectable clutch assembly for a multimode powertrain of a rotorcraft. The selectable clutch assembly includes a freewheeling unit having input and output sides. The freewheeling unit has a driving mode wherein torque applied to the input side is transferred to the output side and an over running mode wherein torque applied to the output side is not transferred to the input side. A bypass assembly is coupled to and rotatable with the output side of the freewheeling unit and is actuatable between engaged and disengaged positions with the input side of the freewheeling unit. In the disengaged position, the freewheeling unit is operable in the driving and the over running modes such that the selectable clutch assembly is configured for unidirectional torque transfer. In the engaged position, the over running mode of the freewheeling unit is disabled such that the selectable clutch assembly is configured for bidirectional torque transfer.
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公开(公告)号:US10766611B2
公开(公告)日:2020-09-08
申请号:US15815988
申请日:2017-11-17
申请人: KOPTER GROUP AG
发明人: Roman Köstli , Martin Stucki
摘要: A helicopter rotor transmission in which the average lubricant monitoring and replenishment intervals are to be significantly increased. The helicopter rotor transmission has a central cavity, in which runs a bearing mast that is fixed in a locationally and rotationally manner, which is held passing through the gear housing at least partially in the direction of the central axis. An internally toothed gear ring of a rotatable rotor mast can be rotated about the central axis, with fixed rotation of the planetary gears about their planetary gear axes, such that the rotor mast can be set in rotation by means of a gear ring driver attached to the gear ring.
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公开(公告)号:US10752342B2
公开(公告)日:2020-08-25
申请号:US15835575
申请日:2017-12-08
申请人: AIRBUS HELICOPTERS
发明人: Setareh Taheri , Nicolas Certain
摘要: A regulator device for regulating a speed of rotation, of a shaft of a gas generator of at least one turboshaft engine of a rotorcraft. The rotorcraft has at least one main rotor for regulating at least lift and/or propulsion for said rotorcraft in the air; a control member for controlling a collective pitch of the blades of said at least one main rotor, said control member serving to generate a control setpoint for said collective pitch; at least one turboshaft engine suitable for driving rotation of said at least one main rotor, said at least one engine producing, at least temporarily, a drive torque that is transmitted to said at least one main rotor; and measurement means for taking at each instant a measurement of said drive torque transmitted by said at least one engine to said at least one main rotor.
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