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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：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：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：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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公开(公告)号：US20240278935A1
公开(公告)日：2024-08-22
申请号：US18172837
申请日：2023-02-22
发明人： Gregory Alan Spruce
CPC分类号： B64F5/10 , F16C35/06 , F16C43/04 , B64C29/0033
摘要： A fixture for installing a bearing race around a mast at a particular location is described. The fixture includes a plurality of vertical rails; a mast retention assembly positioned in between the plurality of rails and connected to inner surfaces of the rails, the mast retention assembly including a mast retention opening for receiving the mast therethrough, the mast retention assembly maintaining the mast in a vertical orientation when the mast is disposed through the mast retention opening; and a shuttle translatably connected to inner surfaces of the rails, the shuttle configured to retain the bearing race in a bearing race retention opening of the shuttle and to translate the bearing race from an upper end of the mast as the mast is disposed through the mast retention opening, wherein the mast passes through an inner opening of the bearing race, and to the particular position on the mast.
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公开(公告)号：US20240258556A1
公开(公告)日：2024-08-01
申请号：US18594587
申请日：2024-03-04
发明人： Phalgun Madhusudan
IPC分类号： H01M10/04 , H01M50/166
CPC分类号： H01M10/0431 , H01M50/166
摘要： A battery cell assembly, including a rolled cell formed from a first electrode and a second electrode rolled together about a longitudinal axis. The rolled cell includes a primary section in which the first electrode and the second electrode overlap in a radial direction from the longitudinal axis, and a first extension end extending from a first longitudinal end of the primary section and formed from a first edge section of the first electrode. The first edge section includes a first folded portion folded to contact an adjacent portion of the first edge section. The battery cell assembly further includes a first end cap coupled to the rolled cell and contacting the first folded portion.
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公开(公告)号：US20240246698A1
公开(公告)日：2024-07-25
申请号：US18159461
申请日：2023-01-25
发明人： Clifton Lee Harrell
摘要： In an embodiment, an aircraft includes an actuator and a flight control computer interfaced with the actuator. The flight control computer is configured to: increase an initiating force output by an initiating channel of the actuator; stop the increasing of the initiating force in response to observing restraining forces on restraining channels of the actuator; hold the initiating force at a quiescent initiating value while the restraining channels hold the restraining forces at quiescent restraining values; increase the initiating force to a target initiating value while the restraining channels increase the restraining forces to target restraining values; calculate a force fight test result by summing a difference between the target initiating value and the quiescent initiating value with differences between the target restraining values and the quiescent restraining values; and indicate the actuator failed verification in response to the force fight test result being greater than a first predetermined threshold.
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公开(公告)号：US20240246665A1
公开(公告)日：2024-07-25
申请号：US18624806
申请日：2024-04-02
CPC分类号： B64C27/28 , B64C29/0033
摘要： A rotor system for an aircraft includes a rotor assembly comprising a plurality of rotor blades connected to a rotor mast, wherein the rotor assembly is tiltable relative to a wing of the aircraft between a first position corresponding to an airplane mode of the aircraft and a second position corresponding to a helicopter mode of the aircraft; and a drive system for providing rotational energy to the rotor assembly via the rotor mast. The drive system includes at least one electric motor for generating rotational energy to a motor shaft; and a gearbox connected to receive rotational energy from the at least one electric motor via the motor shaft and to provide rotational energy to the rotor mast via a rotor shaft, wherein the at least one electric motor is fixed relative to the wing of the aircraft.
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公开(公告)号：US20240190554A1
公开(公告)日：2024-06-13
申请号：US18079352
申请日：2022-12-12
CPC分类号： B64C11/30 , B64C27/20 , B64C27/52 , B64C29/0033 , B64D35/04 , F16H2057/02043
摘要： A linear actuator for axially translating a control tube to change the pitch of rotor blades at a top portion of the control tube, the linear actuator including an outer sleeve fixed in a stationary position with the control tube extending through the outer sleeve, a screw nut connected by a threaded interface to the control tube, and an actuator motor coupled to the screw nut to rotate the screw nut and thereby translate the control tube.
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