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公开(公告)号：US20240017823A1
公开(公告)日：2024-01-18
申请号：US17867231
申请日：2022-07-18
摘要： In an embodiment, an aircraft includes a drive system, a main engine coupled to the drive system to provide first power, and a supplemental engine coupled to the drive system to provide second power additive to the first power. The aircraft also includes a control system to control the main engine and the supplemental engine to optimize usage of the supplemental engine. The control system is operable to maintain the supplemental engine in a reduced power state at least until a determination is made that supplemental power is needed to satisfy a total power demand of the drive system. The control system is also operable to determine that supplemental power is needed to satisfy the total power demand of the drive system. The control system is further operable to increase a power level of the supplemental engine in response to the determination that supplemental power is needed.
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公开(公告)号：US20230327292A1
公开(公告)日：2023-10-12
申请号：US18206610
申请日：2023-06-06
发明人： Michael Raymond Hull , Steven Loveland , Yue Fan
IPC分类号： H01M50/512 , B64D27/24 , B60L50/64 , B64C29/00 , B60L58/10 , H01M10/42 , H01M50/249 , H01M50/209
CPC分类号： H01M50/512 , B64D27/24 , B60L50/64 , B64C29/00 , B60L58/10 , H01M10/425 , H01M50/249 , H01M10/4207 , H01M50/209 , H01M2010/4271 , B64D2221/00 , B60L2200/10 , H01M2220/20
摘要： A modular battery system includes an array of battery modules arranged in at least one stack. Each battery module includes a plurality of battery cells, a first side having positive and negative receptacles and a second side, that is opposite of the first side, having positive and negative plugs. The receptacles and plugs are configured such that adjacent battery modules in a side-by-side relationship are electrically coupled together via plug and receptacle connections and such that the battery modules are electrically coupled together in parallel. An interconnection electrically couples each stack of battery modules together via plug and receptacle connections with one of the battery modules in each stack such that the stacks of battery modules are electrically coupled together in parallel. Each of the battery modules includes a thermal conditioning system configured to thermally isolate the battery module from the other battery modules.
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公开(公告)号：US12130617B2
公开(公告)日：2024-10-29
申请号：US18397371
申请日：2023-12-27
CPC分类号： G05D1/0011 , G05D1/0094 , G05D1/102 , G05D1/223 , G05D1/652 , G05D1/689 , G06T7/292 , G06V20/13 , G06V20/17 , G08G5/0047
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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公开(公告)号：US12130199B2
公开(公告)日：2024-10-29
申请号：US17369470
申请日：2021-07-07
申请人： Bell Textron Inc.
IPC分类号： G01M13/04 , B64C13/50 , B64C27/605
CPC分类号： G01M13/04 , B64C27/605 , B64C13/503
摘要： Embodiments are directed to systems and methods for estimating wear in aircraft rotor systems. Data associated with loads and motions of a swashplate actuator is collected. The swashplate actuator drives a swashplate and at least one control link is coupled to the swashplate. The loads and motions of the at least one control link is estimated based upon the loads and motions of the swashplate actuator. Using a wear model, the current wear of control link components is estimated due to the loads and motions of the at least one control link. Wear estimates for the components are aggregated across multiple flights and used to determine when maintenance actions should occur.
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公开(公告)号：US20240336356A1
公开(公告)日：2024-10-10
申请号：US18539741
申请日：2023-12-14
摘要： A rotorcraft has a drive system including a main rotor coupled to a main rotor gearbox to rotate the main rotor at a rotor speed, a main engine coupled to the drive system to provide a first power, a supplemental engine coupled, when a first clutch is engaged, to the drive system to provide a second power additive to the first power, and a control system operable to control the main engine and the supplemental engine to provide a total power demand, where the main engine is controlled based on variations in rotor speed and a power compensation command to produce the first power, and the supplemental engine is controlled to produce the second power in response to a supplemental power demand.
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公开(公告)号：USD1044652S1
公开(公告)日：2024-10-01
申请号：US29871646
申请日：2023-02-24
摘要： FIG. 1 is a perspective view of an aircraft vanity display screen showing our new design in an aircraft lavatory;
FIG. 2 is another perspective view showing the aircraft vanity display screen of FIG. 1;
FIG. 3 is a side view showing the aircraft vanity display screen of FIG. 1;
FIG. 4 is another side view showing the aircraft vanity display screen of FIG. 1; and,
FIG. 5 is front view showing the aircraft vanity display screen of FIG. 1.
In FIGS. 1-5, broken lines indicate environmental structure that forms no part of the claimed design.-
公开(公告)号：US12103696B2
公开(公告)日：2024-10-01
申请号：US17721200
申请日：2022-04-14
发明人： Bradley Passe , Kip Campbell
CPC分类号： B64D35/00 , B64C29/0033 , B64D27/10 , B64D27/16
摘要： An aircraft includes a fuselage, a pylon, a wing positioned between the fuselage and the pylon, and a plurality of drive shafts located inside the wing and adapted to drive a rotor associated with the pylon.
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公开(公告)号：US12103692B2
公开(公告)日：2024-10-01
申请号：US18068693
申请日：2022-12-20
发明人： Zachary Richard Matson , Clark Ray Miller , Shawn Durwin Doggett , Jennifer Lynn Graham-Rateliff , Craig James Brownell
IPC分类号： B64D27/40
CPC分类号： B64D27/40
摘要： An engine support truss assembly for aircraft includes a mounting plate having a front side and a back side opposite the front side, a truss structure mechanically coupled to the front side of the mounting plate, and a backup structure mechanically coupled to the back side of the mounting plate. The truss structure includes a plurality of structural members each including precipitation-hardened stainless steel. The backup structure is configured to provide mechanical support to the truss structure.
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公开(公告)号：US12084175B2
公开(公告)日：2024-09-10
申请号：US17720089
申请日：2022-04-13
CPC分类号： B64C29/0033 , B64C3/32 , B64C3/56 , B64C27/50
摘要： An aircraft includes a fuselage and a wing assembly that is rotatable between a substantially perpendicular orientation relative to the fuselage in flight modes and a substantially parallel orientation relative to the fuselage in a wing stowage mode. The wing assembly includes a wing that is pivotable between forward flight and VTOL orientations by a pivot angle. A distributed thrust array is coupled to the wing that includes outboard and inboard propulsion assemblies, each propulsion assembly having an axis of rotation that has a fixed angle relative to a chord axis of the wing. In a VTOL flight mode, the axis of rotation of each propulsion assembly is substantially vertical and the wing is in the VTOL orientation. In a forward flight mode, the wing is in the forward flight orientation and the axis of rotation of each propulsion assembly is tilted forward from the vertical by the pivot angle.
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公开(公告)号：US20240286741A1
公开(公告)日：2024-08-29
申请号：US18115220
申请日：2023-02-28
CPC分类号： B64C29/0033 , B64C11/02 , B64C11/28
摘要： A universal-joint cross assembly includes a cross. Four compression rings are mounted at terminal positions of the cross. Each of the four compression rings is positioned at a 90° interval relative to adjacent ones of the four compression rings. The universal-joint cross assembly includes four inner balls. Each of the four inner balls is fixed to one of the four compression rings and forms a portion of a spherical bearing.
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