公开(公告)号：US11702202B1

公开(公告)日：2023-07-18

申请号：US16402562

申请日：2019-05-03

申请人： Government of the United States, as represented by the Secretary of the Air Force

发明人： Michael L. Anderson ,  Zachary Froembling ,  Kaz I. Teope

IPC分类号： B64C39/02 ,  B64C27/33 ,  F16M13/02 ,  B64C1/30 ,  F16H25/22 ,  F15B15/14 ,  B64U10/13 ,  B64U30/20

CPC分类号： B64C39/024 ,  B64C1/30 ,  B64C27/33 ,  F16M13/022 ,  B64U10/13 ,  B64U30/20 ,  F15B15/14 ,  F16H25/2204 ,  F16M2200/06 ,  F16M2200/021

摘要： A system, method and apparatus for unfolding and folding a multi-arm device that includes a support member and an actuator. A first arm is coupled to the actuator and extends from a folded position to an unfolded position upon actuation of the actuator. A second arm is coupled to the actuator and moves from a folded position to an unfolded position upon actuation of a linkage that causes the second arm to rotate. A third arm moves from a folded position to an unfolded position, via an elbow joint, upon release of a tether attached to the third arm.

公开(公告)号：US11541995B2

公开(公告)日：2023-01-03

申请号：US16928605

申请日：2020-07-14

申请人： LOCKHEED MARTIN CORPORATION

发明人： Eric S. Parsons

IPC分类号： B64C27/48 ,  B64C27/33 ,  B64C27/82

摘要： A structural member for use in a rotor system which rotates about a rotational axis includes a pin which extends substantially perpendicular to the rotational axis, a filler component positioned adjacent the pin, and a plurality of layers of composite material having fibers oriented lengthwise along a central axis which is perpendicular to the rotational axis. The plurality of fibers in the layers of composite material is wrapped about the pin and the filler component such that the fibers extend along the central axis and the plurality of layers form an opening filled by the filler component and which decreases as a function of distance from the pin along the central axis.

公开(公告)号：US11186363B2

公开(公告)日：2021-11-30

申请号：US15295258

申请日：2016-10-17

申请人： Sikorsky Aircraft Corporation

发明人： Timothy Fred Lauder ,  Jonathan Hartman ,  Peter James Waltner

IPC分类号： B64C27/14 ,  B64D27/24 ,  B64C27/33 ,  H02K7/08

摘要： A rotary wing aircraft includes an airframe, a stationary mast fixedly engaged to the airframe and extending along a first axis, and an electric motor. The electric motor includes a stator assembly engaged to the mast and a rotor assembly disposed radially outward from the stator assembly and configured to rotate with respect to the stator assembly. A plurality of rotor blades project radially outward from the rotor assembly.

公开(公告)号：US10967965B2

公开(公告)日：2021-04-06

申请号：US16106288

申请日：2018-08-21

申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH

发明人： Moritz Buesing ,  Rupert Pfaller ,  Martin Ortner

IPC分类号： B64C27/33 ,  B64C27/635 ,  B64C27/48

摘要： An elastic flapping hinge for connecting a rotor blade to a rotor hub of a rotary wing aircraft, comprising an elastic flapping hinge member arrangement that includes a hub attachment area for attachment to the rotor hub, a connection area for attachment to the rotor blade, and an elastic flapping hinge area that is arranged between the hub attachment area and the connection area and adapted to allow flapping movements, the elastic flapping hinge member arrangement comprising at least two elastic flapping hinge members having a first bending stiffness for flapping movements and a second bending stiffness for lead-lag movements, the first bending stiffness being smaller than the second bending stiffness, wherein the at least two elastic flapping hinge members diverge from each other in the elastic flapping hinge area by a predetermined divergence angle.

公开(公告)号：US10717521B2

公开(公告)日：2020-07-21

申请号：US15509741

申请日：2015-09-28

申请人： Sikorsky Aircraft Corporation

发明人： Steven D. Weiner ,  Mikel Brigley ,  David H. Hunter

IPC分类号： B64C27/10 ,  F16F15/02 ,  B64C27/00 ,  B64C27/14 ,  B64C1/00 ,  B64C7/00 ,  B64C13/18 ,  B64C13/50 ,  B64C19/00 ,  B64C27/12 ,  B64C27/16 ,  B64C27/32 ,  B64C27/33 ,  B64C27/473 ,  B64C27/48 ,  B64C27/51 ,  B64C27/52 ,  B64C27/54 ,  B64C27/78 ,  B64C27/80 ,  B64C27/82 ,  B64D39/00 ,  B64D39/06 ,  B64D45/02 ,  F16H37/02 ,  G05D1/00 ,  G05D1/02 ,  B64C13/04 ,  G05D1/08 ,  B64C27/57 ,  B64D35/06 ,  B64C27/467 ,  B64C27/08 ,  F02C9/28 ,  F16D13/52 ,  F16D13/72 ,  F16D13/74

摘要： An aircraft includes an airframe; an extending tail; a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly; and a translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe; wherein a ratio of (i) the hub separation between the hub of the upper rotor assembly and the hub of the lower rotor assembly to (ii) a radius of the upper rotor assembly is between about 0.1 and about 0.135.

公开(公告)号：US10518868B2

公开(公告)日：2019-12-31

申请号：US15375385

申请日：2016-12-12

申请人： Textron Innovations Inc.

发明人： Thomas Clement Parham, Jr. ,  Jouyoung Jason Choi ,  Gary Miller ,  Frank Bradley Stamps ,  Richard Erler Rauber

IPC分类号： B64C11/04 ,  B64C11/06 ,  B64C27/00 ,  B64C27/33 ,  B64C27/35 ,  B64C27/51 ,  B64C27/54 ,  B64C29/00

摘要： A soft-in-plane proprotor system for a tiltrotor aircraft having a helicopter mode and an airplane mode. The proprotor system includes a hub, a plurality of proprotor blades and a plurality of loop yokes, each coupling one of the proprotor blades with the hub and each including first and second longitudinal sections extending between inboard and outboard arcuate sections and a bearing assembly disposed between the inboard and outboard arcuate sections of each loop yoke. Each bearing assembly includes a flapping bearing disposed generally within the inboard arcuate section of the respective loop yoke and coupled to the hub, a lead-lag damper coupled to the hub, a centrifugal force bearing disposed generally within the outboard arcuate section of the respective loop yoke and a blade anchor coupled between the lead-lag damper and the centrifugal force bearing. The blade anchor is also coupled to the respective proprotor blade.

公开(公告)号：US20190375496A1

公开(公告)日：2019-12-12

申请号：US16547003

申请日：2019-08-21

申请人： Bell Helicopter Textron Inc.

发明人： Gary Miller ,  Frank B. Stamps

IPC分类号： B64C27/33 ,  B64C27/605 ,  B64C29/00

摘要： In one embodiment, a rotor hub comprises a yoke for attaching a plurality of rotor blades, a constant velocity joint to drive torque from a mast to the yoke and to enable the yoke to pivot, and a rotor control system configured to adjust an orientation of the plurality of rotor blades. Moreover, the rotor control system comprises: a swashplate, an adapter ring, a plurality of actuators controlled based on a flight control input, a plurality of lower pitch links configured to transfer motion between the swashplate and the adapter ring, a plurality of phase adjustment levers configured to adjust a control phase associated with motion transferred between the swashplate and the adapter ring, and a plurality of upper pitch links configured to adjust a pitch of the plurality of rotor blades, wherein there are more upper pitch links than lower pitch links.

公开(公告)号：US10450059B2

公开(公告)日：2019-10-22

申请号：US15882573

申请日：2018-01-29

申请人： Bell Helicopter Textron Inc.

发明人： Kyle Thomas Cravener ,  Tyler Wayne Baldwin ,  Nicholas Allen Torske

IPC分类号： B64C27/33 ,  B64C27/35 ,  B64C27/48 ,  B64C27/32 ,  B64C27/50 ,  B64C29/00

摘要： A multi-piece inboard beam assembly for use in a rotor blade assembly of a rotorcraft. The inboard beam assembly includes an inboard beam connected to an inboard beam fitting with an anti-rotational connection. The inboard beam is connected to a yoke via bearings and the inboard beam fitting is connected to a grip in a double shear condition. In use, the grip, the inboard beam fitting with the double shear connection, the inboard beam, a centrifugal force bearing held by the inboard beam, and the yoke carry the centrifugal force created upon rotation of the rotor blade assembly.

公开(公告)号：US10434687B2

公开(公告)日：2019-10-08

申请号：US15519726

申请日：2015-12-10

申请人： Sikorsky Aircraft Corporation

发明人： Joshua A. Breon ,  Mario Dipreta

IPC分类号： B29C70/38 ,  B29C70/54 ,  B29C39/04 ,  B29C33/30 ,  B29C64/245 ,  B29C70/86 ,  B29C39/10 ,  B29C39/12 ,  B29C70/30 ,  B64C27/473 ,  B29C70/46 ,  B64F5/10 ,  B64C27/48 ,  B64C27/33

摘要： A composite piece tool used to create a composite piece. The tool includes a substrate having a substrate surface, walls disposed on the substrate and extending from the substrate surface in a thickness direction of the composite piece to define opposite locations of longitudinal composite piece ends and composite piece sides, a tooling surface disposed to occupy an entirety of a space delimited by the walls and on which the composite piece formed and a servo controller coupled to the tooling surface and configured to move the tooling surface upwardly and downwardly relative to the substrate surface and walls to form the composite piece.

公开(公告)号：US20180281937A1

公开(公告)日：2018-10-04

申请号：US15765119

申请日：2016-08-12

申请人： Sikorsky Aircraft Corporation

发明人： Frederick J. Miner ,  David A. Darrow ,  Stephen V. Poulin ,  Richard Thomas Hood ,  Frank P. D'Anna

IPC分类号： B64C27/32 ,  B64C27/33 ,  B64C27/48

CPC分类号： B64C27/327 ,  B64C11/06 ,  B64C27/33 ,  B64C27/48

摘要： A box frame hub arm structure is provided and includes a body having an outboard surface, which is disposable to abut with an inboard surface of an outboard arm of an aircraft rotor head, and lead/lag sides. The body is formed to define a first cavity, an aperture communicative with the first cavity through the outboard surface and second and third cavities. The second and third cavities extend outwardly in opposite lead/lag directions from the first cavity to the lead/lag sides.