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公开(公告)号：US11873111B2
公开(公告)日：2024-01-16
申请号：US17143387
申请日：2021-01-07
CPC分类号： B64D37/32 , B60L50/72 , B64C27/00 , B64D37/02 , B60L2200/10
摘要： Embodiments are directed to a fuel cell protection system comprising an aircraft fuselage having an inner surface and an outer surface, an attachment point mounted on the outer surface, an aircraft fuel cell spaced apart from the inner surface, and a plate positioned between the inner surface and the aircraft fuel system, the plate spaced apart from the inner surface to create a void space. The attachment point may be a cargo hook. The void space is configured to receive all or a portion of the cargo hook after a crash. The plate creating the void space may be a rigid material or may be a ballistic fabric material.
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42.发明授权公开(公告)号：US11866169B2
公开(公告)日：2024-01-09
申请号：US16988375
申请日：2020-08-07
申请人： Bell Textron Inc.
IPC分类号： B64C7/02 , B64C39/02 , H01M8/0267 , H01M8/04014 , B64U50/19
CPC分类号： B64C7/02 , B64C39/024 , H01M8/0267 , H01M8/04014 , B64U50/19 , H01M2250/20
摘要： An unmanned aerial vehicle (UAV) has an air-cooled fuel cell, an air channel comprising a forward facing opening for receiving ram air and connected to the air-cooled fuel cell, and a passive ram air filtration system (PRAFS) configured to filter particulate matter from ram air received into the air channel via the opening.
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公开(公告)号：US11835012B2
公开(公告)日：2023-12-05
申请号：US17749708
申请日：2022-05-20
发明人： Stephen M. Eddy
CPC分类号： F02D9/02 , B64C11/30 , B64D31/04 , F02D11/04 , F02D29/02 , F02D2009/021 , F02D2009/0277
摘要： An automatic aircraft powerplant control system includes a throttle servo for adjusting a throttle valve via a throttle control linkage. A throttle control lever provides a user input to the throttle servo, and a throttle controller controls the throttle servo for controlling a throttle valve. A propeller servo may be provided for adjusting a propeller governor setting of an engine. A propeller control lever provides a user input to the propeller servo, and a propeller controller controls the propeller servo. A full-authority digital engine control (FADEC) controller is used to automatically control mixing of fuel and air via a fuel-air mixture device. The FADEC controller may be used to automatically provide propeller control.
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公开(公告)号：US11814163B2
公开(公告)日：2023-11-14
申请号：US17148307
申请日：2021-01-13
申请人： Bell Textron Inc.
IPC分类号： B64C29/00 , B64D27/24 , B64D29/02 , B64D35/02 , B64D35/04 , H02K7/108 , F16D41/00 , H02K7/116
CPC分类号： B64C29/0033 , B64D27/24 , B64D29/02 , B64D35/02 , B64D35/04 , H02K7/108 , H02K7/116 , F16D41/00
摘要： A rotor system for an aircraft includes an open rotor assembly comprising a plurality of rotor blades connected to a rotor mast via a yoke, wherein the rotor assembly is tiltable between a first position corresponding to an airplane mode and a second position corresponding to a helicopter mode; and a drive system for providing rotational energy to the open rotor assembly via the rotor mast, the drive system comprising at least one electric motor for providing rotational energy to a drive shaft and a gearbox connected to the drive shaft for receiving rotational energy from the at least one electric motor via the drive shaft and providing rotational energy to the rotor mast via a rotor shaft; wherein the drive system is rotatable relative to the wing about a tilt axis and the rotor shaft is coaxial with the drive shaft.
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公开(公告)号：US11814162B2
公开(公告)日：2023-11-14
申请号：US16905558
申请日：2020-06-18
申请人： Bell Textron Inc.
摘要： One embodiment includes a rotary aircraft, including: a main drive rotor; an aircraft body mechanically coupled to the main drive rotor; and first and second flight assist wings passively rotatably coupled to the aircraft body.
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公开(公告)号：US11807357B2
公开(公告)日：2023-11-07
申请号：US17527900
申请日：2021-11-16
申请人： Bell Textron Inc.
CPC分类号： B64C29/0033 , B64C39/12 , B64D27/26
摘要： One embodiment is an aircraft operable in a hover mode and a cruise mode and including a fuselage; wings connected on opposite sides of the fuselage; a canard connected to the fuselage forward of the wings; forward propulsion systems connected to a trailing edge of the canard on opposite sides of the fuselage; aft propulsion systems connected to trailing edges of the wings; and wing-mounted propulsion systems connected to leading edges of the wings. The aft propulsion systems are tiltable between a first position when the aircraft is in the hover mode and a second position when the aircraft is in the cruise mode. Each of the propulsion systems includes a rotor assembly comprising a plurality of rotor blades. The propulsion systems are substantially equidistant from a center of gravity (CG) of the aircraft.
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公开(公告)号：US11801939B2
公开(公告)日：2023-10-31
申请号：US17667675
申请日：2022-02-09
申请人： Bell Textron Inc.
摘要： A vehicle includes a first rotor system having a rotor blade having an axis of rotation, a rotatable inboard drive component, and a rotatable outboard drive component. The first rotor system further includes a flexible closed loop component associated with each of the inboard drive component and the outboard drive component. Movement of the closed loop component can selectively cause at least one of rotation of the rotor blade about the axis of rotation and movement of the axis of rotation.
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公开(公告)号：US20230339607A1
公开(公告)日：2023-10-26
申请号：US17729646
申请日：2022-04-26
CPC分类号： B64C29/0033 , B64D27/24 , B64C11/305 , B64C11/301
摘要： A method of verifying operation of an aircraft in a pre-defined flight mode includes operating the aircraft in a first flight mode, commanding the aircraft to transition to a second flight mode, evaluating a plurality of motor performance parameters, and based on values of the plurality of motor performance parameters, determining whether the aircraft has successfully transitioned to the second flight mode.
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公开(公告)号：US11787554B2
公开(公告)日：2023-10-17
申请号：US17340837
申请日：2021-06-07
CPC分类号： B64D37/04 , B64C1/06 , B64C3/34 , B64C29/0033 , B64D37/30
摘要： An aircraft includes a fuselage airframe and a wing airframe that is subject to flight loads. The fuselage airframe includes fore/aft floor beams having a plurality of floor intercostals laterally extending therebetween and fore/aft roof beams with a plurality of roof intercostals laterally extending therebetween. Each of a plurality of cabin frames extends generally vertically between respective floor and roof beams. The wing airframe includes forward and aft wing spars with a plurality of wing ribs extending therebetween. At least one fuel tank, that is configured to contain a pressurized fuel such as pressurized hydrogen fuel, integrally forms at least a portion of one of the beams, the intercostals, the frames, the spars and/or the ribs such that the fuel tank is subject to the flight loads.
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公开(公告)号：US20230305553A1
公开(公告)日：2023-09-28
申请号：US18311662
申请日：2023-05-03
CPC分类号： G05D1/0011 , G05D1/0094 , G08G5/0047 , G05D1/102 , G06V20/13 , G06T7/292 , G06V20/17
摘要： One embodiment is a navigation system for an aircraft including a positioning system to generate information related to a position of the aircraft, a group of cameras mounted to a body of the aircraft, each camera of the group of cameras to simultaneously capture images of a portion of an environment that surrounds the aircraft, and a processing component coupled to the positioning system and the group of cameras, the processing component to determine a current position of the aircraft based on the information related to the position of the aircraft and the images.
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