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公开(公告)号：US12103674B2
公开(公告)日：2024-10-01
申请号：US18122502
申请日：2023-03-16
发明人： Pranay Sinha , Damon Vander Lind
IPC分类号： B64C13/00 , B60L50/64 , B60L53/00 , B64C13/48 , B64C27/82 , B64C29/00 , B64C39/12 , B64D27/02 , B64D27/24 , B64D27/40 , B64D31/06 , G05D1/00
CPC分类号： B64C29/0033 , B60L50/64 , B60L53/00 , B64C13/48 , B64C27/82 , B64C39/12 , B64D27/02 , B64D27/24 , B64D27/40 , B64D31/06 , G05D1/101 , B60L2200/10 , B64C2027/8209 , B64D27/026 , B64D27/402
摘要： A vehicle includes a tilt rotor that is aft of a fixed wing and that is attached to the fixed wing via a pylon. A flight computer configured to instruct the tilt rotor to produce a maximum downward angle including by updating an actuator authority database associated with the flight computer to reflect the maximum downward angle, and generating a rotor control signal for the tilt rotor using the updated actuator authority database that reflects the maximum downward angle, wherein the maximum downward angle is adjustable.
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公开(公告)号：US12103672B2
公开(公告)日：2024-10-01
申请号：US17445323
申请日：2021-08-18
发明人： Rupert Pfaller , Tobias Ries
CPC分类号： B64C27/82 , B64C27/06 , B64C39/029 , B64C2027/8263
摘要： A rotary wing aircraft that extends along an associated roll axis between a nose region and an aft region and that comprises a fuselage with a front section and a rear section, the rotary wing aircraft comprising: a main rotor that is rotatably mounted at the front section, and a stabilizer arrangement that is arranged at the rear section in the aft region, wherein the rear section extends between the front section and the stabilizer arrangement and comprises an asymmetrical cross-sectional profile in direction of the associated roll axis.
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公开(公告)号：US12071226B2
公开(公告)日：2024-08-27
申请号：US17436140
申请日：2020-03-04
申请人： PAL-V IP B.V.
发明人： Edwin Anton Ross , Hans Joore , Michael Alwin William Stekelenburg , Lourens Jacobus Dingemanse
CPC分类号： B64C27/06 , B64C27/82 , B64C2027/8227 , B64C2027/8254 , B64C2027/8272 , B64C2027/829
摘要： A flying passenger rotor lifted vehicle that is capable of taking off and landing vertically, that is relatively light-weight, has responsive control, and increased safety against failure of propulsion/thrust systems. The flying vehicle can include a body having a tail section, a central thrust unit arranged along the longitudinal axis of the vehicle, at a distance from the rotation axis of the main rotor, a mounting support on either side of the body, and a side thrust unit mounted to each mounting support. The central thrust unit includes a fan which provides air flow with a flow component perpendicular to a virtual vertical midplane of the vehicle. Each of the side thrust units includes a fan which provides air flow with a flow component parallel to the virtual vertical midplane. At least one of the thrust units has controllable air deflection to deflect the corresponding output air flow in a controllable manner.
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公开(公告)号：US20240270380A1
公开(公告)日：2024-08-15
申请号：US18646214
申请日：2024-04-25
申请人： LEONARDO S.P.A.
摘要： An anti-torque rotor includes a mast rotatable about a first axis; a plurality of blades; an element slidable along the first axis, rotating integrally with the mast and operatively connected to the blades. The rotor also has a slidable control rod; a first bearing with a rotatable first ring, a second ring radially internal to the first ring and a plurality of first rolling bodies; a third ring slidable along the first axis and angularly fixed with respect to the first axis; and a locking element arranged in a first configuration, in which it prevents the relative rotation of the second and third rings and is movable from the first configuration to at least one emergency configuration, in which it renders the second ring free to rotate with respect to the third ring, when the first bearing is in a failure condition.
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公开(公告)号：US20240239512A1
公开(公告)日：2024-07-18
申请号：US18222558
申请日：2023-07-17
发明人： Michael HECKL , Julius VOGL
CPC分类号： B64D47/06 , B64C27/463 , B64C27/82 , F21K2/00 , B64C2027/8281
摘要： A rotorcraft with a fuselage and a tail boom, comprising: a horizontal stabilizer mounted to the tail boom; rotor blades with rotor blade tips which form a virtual blade tip circle upon rotation around a rotor head; luminescent components provided on the rotor blade tips; and a blade tip illumination device comprising at least one light source integrated into the horizontal stabilizer and configured to emit a light beam toward the virtual blade tip circle for excitation of the luminescent components; wherein the luminescent components emit light in response to excitation via the emitted light beam, and wherein the emitted light forms during rotation of the rotor blade tips around the rotor head on the virtual blade tip circle a luminous ring.
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公开(公告)号：US11999472B2
公开(公告)日：2024-06-04
申请号：US17518370
申请日：2021-11-03
CPC分类号： B64C27/48 , B64C27/10 , B64C27/35 , B64C27/26 , B64C2027/8236 , B64C2027/8272 , B64C2027/8281
摘要： A rotor blade retention assembly includes a central hub, a rotor blade including an upper outer surface, a lower outer surface, a blade hole, and a proximal end coupled to the central hub, a strap member extending along a portion of the rotor blade such that a distal end receiving portion extends into the blade hole, and a retainer assembly disposed within the blade hole and coupled to the strap member. The retainer assembly includes an upper bushing and a lower bushing slidably disposed within the blade hole. The upper bushing includes a counterbored portion. The retainer assembly also includes an outboard blade pin disposed within the distal end receiving portion and includes a blade pin inner cavity.
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公开(公告)号：US20240174354A1
公开(公告)日：2024-05-30
申请号：US18222547
申请日：2023-07-17
发明人： Rupert PFALLER , Tobias RIES
IPC分类号： B64C27/82
CPC分类号： B64C27/82 , B64C2027/8254 , B64C2027/8272 , B64C2027/8281
摘要： A rotorcraft with at least one main rotor and a fuselage, comprising: a tail boom connected to the fuselage, the tail boom extending in a longitudinal direction from the fuselage toward a duct-type portion; a shroud provided at the duct-type portion and forming a transverse duct comprising an air inlet region and an air outlet region; the transverse duct having a longitudinal extension; at least one ducted tail rotor rotatably arranged in the transverse duct; and an integral stabilizer arrangement mounted to the shroud, the integral stabilizer arrangement being embodied in box configuration and arranged laterally on a side of the shroud on which the air inlet region of the transverse duct is arranged.
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公开(公告)号：US20240140602A1
公开(公告)日：2024-05-02
申请号：US18367847
申请日：2023-09-13
发明人： Rupert PFALLER , Tobias RIES , Uwe KIESEWETTER
IPC分类号： B64C27/82
CPC分类号： B64C27/82 , B64C2027/8254
摘要： A rotorcraft with at least one main rotor and a fuselage, comprising: a tail boom connected to the fuselage, the tail boom extending in a longitudinal direction from the fuselage toward a duct-type portion; a shroud provided at the duct-type portion and forming a transverse duct comprising a circumferential direction and a longitudinal extension oriented at least essentially perpendicular to the circumferential direction and the longitudinal direction of the tail boom; and at least one ducted tail rotor rotatably arranged in the transverse duct; wherein the shroud comprises a first section connected to the tail boom and a second section spaced apart from the tail boom and diametrically opposed to the first section, the first section comprising an airfoil-like aerodynamic profile.
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公开(公告)号：US11866163B1
公开(公告)日：2024-01-09
申请号：US17701472
申请日：2022-03-22
CPC分类号： B64C27/82 , B64C27/26 , B64C2027/8227 , B64C2027/8236 , B64C2027/8272
摘要： A parking tail rotor for a rotary wing aircraft stops rotating at a high forward aircraft speed when aircraft control surfaces have adequate control authority to balance main rotor torque without the rotating tail rotor. When stopped, the blades of the parking tail rotor move due to the force of the relative wind to a parked position in which the span of the blades extend in the aft direction, reducing air resistance to the forward motion of the aircraft.
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公开(公告)号：US11853054B2
公开(公告)日：2023-12-26
申请号：US17603193
申请日：2021-10-12
IPC分类号： B64C27/02 , G05D1/08 , B64C11/50 , B64C27/10 , B64C27/12 , B64C27/22 , B64C27/26 , B64D31/00 , B64C27/00 , B64C27/14 , B64D27/24 , H02K1/27 , B64C11/48 , B64C27/82
CPC分类号： G05D1/0858 , B64C11/50 , B64C27/006 , B64C27/02 , B64C27/021 , B64C27/025 , B64C27/027 , B64C27/028 , B64C27/10 , B64C27/12 , B64C27/14 , B64C27/22 , B64C27/26 , B64D31/00 , B64C11/48 , B64C2027/8236 , B64D27/24 , H02K1/27
摘要： A multi-rotor aircraft includes a fuselage, a propulsion engine coupled to the fuselage that generates thrust to propel the aircraft along a first vector during forward flight, and rotors coupled to the fuselage, each rotor comprising blades, each rotor coupled to a motor, and each motor configured to supply power to and draw power from the coupled rotor. The aircraft includes a flight control system configured to control the motors coupled to the rotors in a power managed regime in which a net electrical power, consisting of a sum of the power being supplied to or drawn from each rotor by its motor, is maintained within a range determined by a feedback control system of the flight control system. The flight control system can also be leveraged to adjust rotor control inputs to modify at least one of thrust, roll, pitch, or yaw of the multi-rotor aircraft.
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