公开(公告)号：US20180135735A1

公开(公告)日：2018-05-17

申请号：US15812165

申请日：2017-11-14

申请人： AIRBUS OPERATIONS LIMITED

发明人： David BRAKES

IPC分类号： F16H19/04 ,  F16H55/10 ,  F16H55/26 ,  B64C3/28 ,  B64C13/28

CPC分类号： F16H19/04 ,  B64C9/18 ,  B64C13/34 ,  F16H55/10 ,  F16H55/26

摘要： A roller component configured to engage with a toothed component such that when the roller component is engaged with the toothed component, rotational movement of one of the roller component and the toothed component drives linear movement along an actuation direction of the other one of the roller component and the toothed component. The roller component includes a support member and cantilevered first rollers, each of which has a mounted end connected to a first side of the support member such that each first roller is rotatable relative to the support member about a roller axis perpendicular to the actuation direction, and an unsupported end distal from the mounted end.

公开(公告)号：US20180119763A1

公开(公告)日：2018-05-03

申请号：US15802531

申请日：2017-11-03

申请人： Hamilton Sundstrand Corporation

发明人： Kamil BABICKI ,  Anna SZEWCZYK ,  Pawel SKORUPA ,  Piotr ZAJAC

IPC分类号： F16D67/02 ,  F16D41/066 ,  F16D63/00 ,  B64C13/28

CPC分类号： F16D67/02 ,  B64C13/32 ,  F16D41/02 ,  F16D41/066 ,  F16D41/067 ,  F16D63/006

摘要： The present disclosure relates to an apparatus for a torque limiter, comprising an indication device configured to provide an indication that the torque limiting device has tripped, and of the direction of torque applied to the torque limiting device when the torque limiting device tripped, in use.

公开(公告)号：US09950782B2

公开(公告)日：2018-04-24

申请号：US14529694

申请日：2014-10-31

申请人： The Boeing Company

发明人： Neal Van Huynh ,  John A. Standley

IPC分类号： B64C13/30 ,  B64C9/02 ,  B64C13/28 ,  B64C9/00

CPC分类号： B64C13/30 ,  B64C9/00 ,  B64C9/02 ,  B64C13/28 ,  B64C2009/005

摘要： Methods and apparatus for reacting rotary actuator and control surface loads into a wing structure using reaction links. The apparatus incorporates a structural interface feature that can facilitate a change of the component(s) in the load loop, such as the path connecting a control surface to a fixed aircraft structure via a rotary actuator. In particular, the structural interface between the rotary actuator and the rear spar of a wing can be tuned for stiffness to achieve an optimized load path that reacts actuator and control surface loads back into the wing structure. An actuator integration objective can be met for any rotary actuator using an integration method which tolerates wing and/or hinge line deflection.

公开(公告)号：US20180086434A1

公开(公告)日：2018-03-29

申请号：US15567585

申请日：2016-04-20

申请人： George Michael Cook

发明人： George Michael Cook ,  Jonathan Edward Cook ,  Michael Kevin Cook

IPC分类号： B64C13/28 ,  B64C3/56 ,  B64C1/06 ,  B64C31/02 ,  B64C39/02

CPC分类号： B64C13/30 ,  B64C1/061 ,  B64C3/56 ,  B64C13/28 ,  B64C31/02 ,  B64C39/024 ,  B64C2001/0054 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2211/00

摘要： An aircraft for the autonomous aerial delivery of a load to a target location, the aircraft comprising an airframe having at least one adjustable control structure for controlling the flight of the aircraft and a main body adapted to receive a load a self-contained control module releaseably connected to the airframe, the control module containing an actuator for adjusting the control structure and a controller for producing an electrical drive signal for controlling the actuator; and at least one linkage extending from the control module to the at least one adjustable control structure so as to operably connect the control module to the at least one adjustable control structure, wherein the actuator of the control module is adapted to adjust the at least one adjustable control structure using the at least one linkage so as to control the flight of the aircraft and to steer the aircraft to the target location.

公开(公告)号：US09800119B2

公开(公告)日：2017-10-24

申请号：US14556641

申请日：2014-12-01

申请人： Hamilton Sundstrand Corporation

发明人： Derick S. Balsiger ,  Ravi Adimula

IPC分类号： H02K5/18 ,  H02K9/20 ,  B64C13/28 ,  H02K5/20 ,  H02K9/19 ,  H02K15/14 ,  H02K7/14 ,  H02K9/22 ,  B64C13/50

CPC分类号： H02K9/20 ,  B64C13/28 ,  B64C13/504 ,  H02K5/18 ,  H02K5/20 ,  H02K7/14 ,  H02K9/19 ,  H02K9/22 ,  H02K15/14 ,  Y02T50/44

摘要： A cooling system of an electromechanical actuator is provided. The cooling system includes a housing and a stator located within the housing and defining a central bore. A first body including a sleeve portion is configured to extend into the central bore of the stator, with the first body defining a first chamber including a first cavity within the sleeve portion and a second cavity fluidly connected to the first cavity. A heat sink is provided in thermal communication with the second cavity.

公开(公告)号：US09797490B2

公开(公告)日：2017-10-24

申请号：US14671327

申请日：2015-03-27

申请人： Russel Hugh Marvin ,  David H. Leach

发明人： Russel Hugh Marvin ,  David H. Leach

IPC分类号： H01F27/24 ,  F16H25/20 ,  H02K9/22 ,  B64C13/28 ,  B64C13/42 ,  H02K7/06 ,  H02K16/00

CPC分类号： F16H25/205 ,  B64C13/28 ,  B64C13/42 ,  F16H2025/2075 ,  H02K7/06 ,  H02K9/22 ,  H02K16/00 ,  Y02T50/44 ,  Y10T74/18624

摘要： An actuator for moving a first component relative to a second component includes a first actuating mechanism secured to the first component and having a first motor, a first nut, and a first shaft secured to the first motor and the first nut such that the first nut is rotatable with the first motor. A second actuating mechanism is secured to the second component and has a second motor, a second nut, and a second shaft secured to the second motor and the second nut such that the second nut is rotatable with the second motor. A screw is threadably engaged with the first nut and the second nut such that rotation of at least one of the first motor and the second motor causes movement between the first and second nuts to move the second component relative to the first component.

公开(公告)号：US20170276182A1

公开(公告)日：2017-09-28

申请号：US15466075

申请日：2017-03-22

申请人： Goodrich Actuation Systems Limited

发明人： Stephen Davies ,  Mark Hubberstey ,  David Holman

IPC分类号： F16D3/06 ,  B64C13/28 ,  B64C9/24

CPC分类号： F16D3/06 ,  B64C13/28 ,  F16D3/185 ,  F16D3/77 ,  F16D2300/06 ,  Y10T403/7032

摘要： A splined coupling comprises a radially inner shaft and a radially outer shaft having a cavity for receiving the inner shaft. First splines are provided on a radially outwardly facing surface of the inner shaft. Second splines are provided on a radially inwardly facing surface of the cavity of the outer shaft. The first splines are slidably engaged with the second splines. At least one biasing element, for example a diaphragm is arranged to act between the radially inner and radially outer shafts for locating the first splines in a desired axial position relative to the second splines and to provide a biasing force resisting the axial movement of the first splines relative to the second splines upon relative axial movement of the inner and outer shafts.

公开(公告)号：US09701396B2

公开(公告)日：2017-07-11

申请号：US14291198

申请日：2014-05-30

申请人： Airbus Operations GmbH

发明人： Tanno Zantz

IPC分类号： B64C13/28 ,  F16D3/223 ,  F16D3/24 ,  F16D3/10 ,  F16D3/2233 ,  F16D3/224

CPC分类号： B64C13/28 ,  F16D3/10 ,  F16D3/2233 ,  F16D3/224 ,  F16D3/24 ,  F16D2003/22303 ,  Y10S464/906

摘要： A joint arrangement includes an outer joint component, an inner joint component, a cage and at least two balls located between the outer and inner joint component and in openings of the cage. The balls run in ball recesses, while at least two are in a mechanical contact with pressing devices, which are adapted for holding the respective balls in a radially flexible position relative to one of the inner joint component, the outer joint component and the cage and for pressing the respective balls into the corresponding recesses.

公开(公告)号：US09682769B2

公开(公告)日：2017-06-20

申请号：US13832483

申请日：2013-03-15

申请人： AIRBUS OPERATIONS GMBH

发明人： Martin Richter

IPC分类号： B64C13/28 ,  B64C13/30 ,  B64D45/00

CPC分类号： B64C13/28 ,  B64C13/30 ,  B64D45/0005 ,  B64D2045/001 ,  Y02T50/44

摘要： A high-lift system on a wing of an aircraft is provided. The wing includes a right-hand and a left-hand wing half with movably held high-lift flaps and the right-hand and left-hand wing half are attached to an aircraft fuselage, thus forming a wing root. Each wing half in a region in close proximity to the wing root, includes a drive unit. In each case this drive unit is joined to a transmission shaft mechanically connected to the respective drive unit, which transmission shaft extends from the drive unit in the direction of the end of the respective wing half and is designed to mechanically move the high-lift flaps arranged in the respective wing half. By means of such an arrangement it is possible to do without deflection gear arrangements from a central drive unit to the individual wing halves.

公开(公告)号：US20170158313A1

公开(公告)日：2017-06-08

申请号：US15367286

申请日：2016-12-02

申请人： RATIER FIGEAC

发明人： Nicolas TILLOY ,  Olivier BRUCELLE

IPC分类号： B64C13/28

CPC分类号： B64C13/28 ,  F16H25/2015

摘要： Disclosed is an actuator of an aircraft including at least one limit stop in which at least one of the bearing surfaces, named destructible bearing surface (19), has at least one destructible portion which is able to, and is arranged to, be irreversibly deformed under the effect of the co-operation by limit contact between the driving member bearing surface (19) and the driven member bearing surface (20), each destructible portion of each destructible bearing surface being mounted to be removable with respect to the stop so as to be able to be replaced. It relates to an aircraft including at least one actuator provided with such an actuator.