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公开(公告)号：US11186185B2
公开(公告)日：2021-11-30
申请号：US15609779
申请日：2017-05-31
摘要： The present invention includes a system and method for slowing the rotation of a rotor using, for example, rotor brake system for a rotorcraft comprising: one or more generators connected to a main rotor gearbox; an electric distributed anti-torque system mounted on a tail boom of the rotorcraft comprising two or more electric motors connected to the one or more generators, wherein the two or more electric motors are connected to one or more blades; and wherein a rotation of the rotor is slowed by placing a drive load on the main rotor gearbox with the one or more generators to bleed the mechanical power from rotor into electrical power via the two or more electric motors, wherein the electric distributed anti-torque system generates thrust in opposing directions.
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公开(公告)号：US10773798B2
公开(公告)日：2020-09-15
申请号：US15720626
申请日：2017-09-29
摘要： An aircraft rotor assembly has a yoke and a plurality of rotor blade assemblies coupled thereto. Each of the rotor blade assemblies include a rotor blade, a bearing, and a blade grip coupling the rotor blade to the bearing. Each of the rotor blades is rotatable about a lead-lag axis, flap axis, and a pitch change axis, wherein all the axes intersect within the bearing. Adjacent pairs of rotor blade assemblies are coupled together via a damper assembly that is coupled to the pitch change axis of each of the rotor blade assemblies.
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公开(公告)号：US10766612B2
公开(公告)日：2020-09-08
申请号：US15658190
申请日：2017-07-24
摘要： A rotor hub assembly that includes a yoke configured to attach blades thereto, a universal joint configured to attach to, and transmit forces between, a mast and the yoke, and an elastomeric member configured to attenuate vibrations transmitted from the universal joint to the mast.
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公开(公告)号：US20190351999A1
公开(公告)日：2019-11-21
申请号：US15982420
申请日：2018-05-17
摘要： A propulsion assembly for a rotorcraft includes a blade assembly, a drive shaft coupled to the blade assembly and an electric motor coupled to the drive shaft and operable to provide rotational energy to the drive shaft to rotate the blade assembly. The propulsion assembly includes a landing assistance turbine coupled to the drive shaft and operable to selectively provide rotational energy to the drive shaft during an underpowered descent to rotate the blade assembly and provide upward thrust, thereby reducing a descent rate of the rotorcraft prior to landing.
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公开(公告)号：US10414492B2
公开(公告)日：2019-09-17
申请号：US15251128
申请日：2016-08-30
摘要： A tail sitter aircraft includes a fuselage having a forward portion and an aft portion. The forward portion of the fuselage includes first and second rotor stations. A first rotor assembly is positioned proximate the first rotor station. A second rotor assembly is positioned proximate the second rotor station. A tailboom assembly extends from the aft portion of the fuselage. The tailboom assembly includes a plurality of landing members. In a vertical takeoff and landing mode of the aircraft, the first and second rotor assemblies rotate about the fuselage to provide vertical thrust. In a forward flight mode of the aircraft, the first rotor assembly rotates about the fuselage to provide forward thrust and the second rotor assembly is non-rotatable about the fuselage forming wings to provide lift.
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公开(公告)号：US10392098B2
公开(公告)日：2019-08-27
申请号：US16289438
申请日：2019-02-28
IPC分类号： B63H1/06 , B64C11/34 , B64C29/00 , B64C27/605 , B64C27/41 , B64C11/00 , F16D3/62 , B64C27/473
摘要： A high stiffness hub assembly for a rotor system operable to rotate with a mast of a rotorcraft. The hub assembly includes a yoke and a constant velocity joint assembly. The yoke has a plurality of blade arms each configured to hold a rotor blade. The constant velocity joint assembly provides a torque path from the mast to the yoke that includes a trunnion assembly, a plurality of drive links and a plurality of pillow blocks. The trunnion assembly is coupled to the mast and has a plurality of outwardly extending trunnions. Each drive link has a leading bearing coupled to one of the trunnions and a trailing bearing coupled to one of the pillow blocks. Each pillow block is independently mounted between an upper surface of the yoke and a hub plate.
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公开(公告)号：US20190112041A1
公开(公告)日：2019-04-18
申请号：US15787093
申请日：2017-10-18
发明人： Andrew Paul Haldeman , Dalton T. Hampton , Frank Bradley Stamps , John Lloyd , Gilberto Morales
摘要： A rotor assembly has a composite driveshaft extending between a transmission and a yoke for providing torque from the transmission to the yoke to cause rotation of the yoke and a plurality of rotor blade assemblies attached thereto. The rotor hub also has a composite static mast coupled to the yoke and a frame. The static mast being configured to carry the lift and thrust forces from the yoke to the frame.
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公开(公告)号：US10196139B2
公开(公告)日：2019-02-05
申请号：US15986219
申请日：2018-05-22
摘要： An apparatus comprising a drivelink comprising a housing including a socket, wherein the socket comprises a cross-sectional area, and a bearing cartridge disposed within the socket, wherein a cross-sectional area of the cartridge is less than the cross-sectional area of the socket. An apparatus comprising a drivelink comprising a housing having a socket, and a bearing cartridge positioned within the socket and comprising a first portion and a second portion, wherein the first portion is configured to undergo compression when a load is applied to the drivelink, and wherein the second portion is configured to not be in tension when the load is applied to the drivelink.
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公开(公告)号：US20180327086A1
公开(公告)日：2018-11-15
申请号：US15594588
申请日：2017-05-13
IPC分类号： B64C27/32 , B64C27/605 , B64C29/00 , B64C27/06 , F16C19/06
CPC分类号： B64C27/32 , B64C27/06 , B64C27/605 , B64C29/0033 , F16C19/06 , F16C2326/43
摘要： An aircraft rotor assembly has a yoke with at least two arms extending therefrom. The yoke is attached to a mast through a constant-velocity joint, thereby permitting axial tilt of the yoke relative to the mast. Each arm of the yoke includes an axisymmetric elastomeric bearing with a spherical central member and two opposite partially-spherical members attached to the central member. Each axisymmetric bearing cooperates with a cup and a bracket. Each cup is attached to one of the yoke arms and each bracket is attached to a blade cuff.
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公开(公告)号：US20180265186A1
公开(公告)日：2018-09-20
申请号：US15459781
申请日：2017-03-15
CPC分类号： B64C27/001 , B64C27/10 , B64C27/22 , B64C27/82 , B64C2027/002 , B64C2027/8236 , B64C2027/8281
摘要： A vibration isolation system for an advancing blade concept rotorcraft having a pylon assembly and an airframe. The vibration isolation system includes one or more pylon links each having first and second ends with the first end coupled to the pylon assembly and the second end coupled to the airframe. Each pylon link includes a vibration isolator, such as a Liquid Inertia Vibration Eliminator unit, that is interposed between the pylon assembly and the airframe. The vibration isolator system is operable to reduce or eliminate transmission of the pylon assembly vibration to the airframe.
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