公开(公告)号：US20190241245A1

公开(公告)日：2019-08-08

申请号：US16263877

申请日：2019-01-31

申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH

发明人： Andreas RACK ,  Thomas JOACHIM ,  Rupert PFALLER

IPC分类号： B64C1/06

CPC分类号： B64C1/069 ,  B32B3/06 ,  B64C1/061 ,  B64C1/12 ,  B64C1/26 ,  B64C3/26 ,  B64C27/82 ,  F16B5/0088 ,  F16B11/006

摘要： A shear connection for interchangeably connecting two airframe parts of an aircraft. The shear connection may include first and second interface parts. The second interface part may overlap in the longitudinal direction at an overlap section with at least one of the first interface part and the first airframe part. The shear connection may further comprise means that rigidly and non-interchangeably attach the first interface part to the first airframe part and the second interface part to the second airframe part and a shear bolt that rigidly and interchangeably connects the second interface part with the at least one of the first interface part and the first airframe part at the overlap section, thereby interchangeably connecting the first and second airframe parts.

公开(公告)号：US20180327079A1

公开(公告)日：2018-11-15

申请号：US15593304

申请日：2017-05-11

申请人： Bell Helicopter Textron Inc.

发明人： Brendan P. Lanigan ,  Joshua R. O'Neil

IPC分类号： B64C5/06 ,  B64C27/82 ,  B64C5/02

CPC分类号： B64C5/06 ,  B64C27/82 ,  B64C2027/8272 ,  B64C2027/8281

摘要： In one embodiment, a vertical stabilizer comprises an airfoil structure configured to be mounted to an aircraft at a vertical orientation. The airfoil structure comprises a leading edge and a trailing edge, wherein the trailing edge is configured to form a blunt shaped edge. The airfoil structure further comprises a root end and a tip end, wherein the airfoil structure is tapered from the root end to the tip end. The airfoil structure is also cambered. Finally, the airfoil structure is further configured to be mounted with a rotor, and is also further configured to house one or more internal components associated with the aircraft.

公开(公告)号：US10053212B2

公开(公告)日：2018-08-21

申请号：US15313730

申请日：2015-05-22

申请人： SIKORSKY AIRCRAFT CORPORATION

发明人： William G. Sheridan

IPC分类号： B64C27/10 ,  B64C27/12 ,  B64C27/82 ,  F16H1/46

CPC分类号： B64C27/10 ,  B64C27/12 ,  B64C27/82 ,  B64C2027/8236 ,  F16H1/46

摘要： A coaxial, dual rotor system includes a first rotor assembly located at a rotor axis and rotatable thereabout and a second rotor assembly located at the rotor axis radially inboard of the first rotor assembly and rotatable thereabout. A rotationally fixed static mast is located radially between the first rotor assembly and the second rotor assembly. A transmission includes a rotor input shaft including a first sun gear and a second sun gear. A star gear arrangement is operably connected to the first sun gear and to the static mast to drive rotation of the first rotor assembly about the rotor axis and a planetary gear arrangement is operably connected to the second sun gear and to the static mast to drive rotation of the second rotor assembly about the rotor axis.

公开(公告)号：US20180148167A1

公开(公告)日：2018-05-31

申请号：US15826851

申请日：2017-11-30

申请人： AIRBUS HELICOPTERS

发明人： Jean-Romain BIHEL ,  Zouhair SASSI

IPC分类号： B64C27/56 ,  B64C13/14 ,  B64C27/82

CPC分类号： B64C27/56 ,  B64C11/30 ,  B64C13/0421 ,  B64C13/044 ,  B64C13/14 ,  B64C27/82 ,  B64C2027/8227 ,  B64D31/04

摘要： A control member that is operable by a pilot to vary thrust from a thrust system of an aircraft. The control member comprises a stick and a movable assembly including a grip. The grip is linked to the stick via a helical link, rotation of the grip about the stick giving rise to movement in translation of the grip together with the movable assembly along the stick, the grip being movable in translation in both a first direction in translation and in a second direction in translation that is opposite to the first direction in translation.

公开(公告)号：US20180087561A1

公开(公告)日：2018-03-29

申请号：US15702958

申请日：2017-09-13

申请人： Bell Helicopter Textron Inc.

发明人： Andrew Jordan Birkenheuer ,  Keith David Weaver ,  Jon Damon Bennett

IPC分类号： F16C3/16 ,  F16C3/02 ,  B64C27/12 ,  B64D35/00

CPC分类号： F16C3/16 ,  B64C27/12 ,  B64C27/14 ,  B64C27/82 ,  B64D35/00 ,  B64D45/00 ,  B64D2045/009 ,  F16C3/02 ,  F16C3/026 ,  F16C2326/06 ,  F16C2326/43 ,  F16H57/0416

摘要： The present invention includes a thermal management system and method including: a drive shaft; one or more fans or impellers in fluid communication with at least a portion of the drive shaft; and one or more air management baffles configured to direct air flow between the impeller and the portion of the drive shaft. In one embodiment, the system and method further includes insulation positioned about the at least a portion of the drive shaft.

公开(公告)号：US09878785B2

公开(公告)日：2018-01-30

申请号：US14258003

申请日：2014-04-21

申请人： The Boeing Company

发明人： Steven D. Richardson

IPC分类号： B64C27/82 ,  B64C3/38 ,  B64C15/02 ,  B64C15/14 ,  B64C27/18 ,  B64C27/24 ,  B64C27/26

CPC分类号： B64C27/82 ,  B64C3/385 ,  B64C15/02 ,  B64C15/14 ,  B64C27/18 ,  B64C27/24 ,  B64C27/26 ,  Y02T50/14

摘要： A method of operating an aircraft having a rotor/wing assembly and a nozzle comprises vectoring the nozzle into a position for creating vertical thrust, and using the rotor/wing assembly and the nozzle together to create vertical thrust during a rotary mode of operation.

公开(公告)号：US20180022450A1

公开(公告)日：2018-01-25

申请号：US15547757

申请日：2016-02-05

申请人： Jean-Claude Tourn

发明人： Jean-Claude Tourn

IPC分类号： B64C27/82

CPC分类号： B64C27/82 ,  B64C27/12 ,  B64C27/18 ,  B64C2027/8245

摘要： The present invention relates to a device for controlling the yaw of an aviation device, such as a helicopter, said aviation device comprising a bearing structure and a rotating member connected to the bearing structure to be mobile in rotation, around an axis of rotation, relative to said bearing structure, wherein the rotating member comprises fixing means for fixing at least one blade, the yaw control device comprising a rotor and a stator which form, in combination, an electrical machine, wherein the bearing structure is connected to the first of this stator and this rotor, and wherein the rotating member is connected to the second of this stator and this rotor, wherein the electrical machine is suitable for generating an electromotive force applied to the rotating member.

公开(公告)号：US20170263130A1

公开(公告)日：2017-09-14

申请号：US15502446

申请日：2015-09-14

申请人： SIKORSKY AIRCRAFT CORPORATION

发明人： Harshad S. Sane ,  George Nicholas Loussides ,  Igor Cherepinsky ,  Brendan J. Englot

IPC分类号： G08G5/00 ,  B64C29/00 ,  B64D45/08 ,  B64C27/82 ,  B64D47/08 ,  B64C39/02 ,  B64C27/06

CPC分类号： G08G5/006 ,  B64C27/06 ,  B64C27/82 ,  B64C29/0025 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/145 ,  B64D45/08 ,  B64D47/08 ,  G08G5/0008 ,  G08G5/0013 ,  G08G5/0021 ,  G08G5/0034 ,  G08G5/0039 ,  G08G5/0078 ,  G08G5/0086 ,  G08G5/045

摘要： A method for path planning for a plurality of vehicles in a mission space includes determining, with a processor, information indicative of a first local graph of a first vehicle; receiving, with the processor over a communication link, information indicative of a second local graph from a second vehicle; assembling, with the processor, information indicative of a global graph in response to the receiving of the second local graph; wherein the global graph includes information assembled from the first local graph and the second local graph; and wherein the global graph indicates connectivity of objectives for each vehicle of the plurality of vehicles in the mission space.

公开(公告)号：US20170241539A1

公开(公告)日：2017-08-24

申请号：US15285232

申请日：2016-10-04

申请人： TEXTRON INNOVATIONS INC.

发明人： Scott D. Poster ,  David A. Elliott ,  Gary A. Cope

IPC分类号： F16H57/04 ,  B64C27/82 ,  B64C27/06 ,  B64D35/00 ,  B64C27/12

CPC分类号： F16H57/0447 ,  B64C27/06 ,  B64C27/12 ,  B64C27/82 ,  B64D35/00 ,  F16H57/027 ,  F16H57/0424 ,  F16H57/0438 ,  F16H57/0442 ,  F16H57/045 ,  F16H57/0471

摘要： A lubrication system includes a reserve housing configured to retain a lubrication fluid. A supply line in fluid communication with the reserve housing is configured to provide pressurized lubrication fluid to the reserve housing. An overflow tube has an overflow port, the overflow tube being configured to prevent the volume of the lubrication fluid from exceeding a certain amount. A metering jet is configured to allow the lubrication fluid to flow from the reserve housing onto a component, such as a bearing, in the gearbox at a predetermined rate. The metering jet provides flow of the lubrication fluid onto the bearing even when the supply line no longer provides pressurized lubrication fluid to the reserve housing.

公开(公告)号：US20170210461A1

公开(公告)日：2017-07-27

申请号：US15329411

申请日：2015-09-28

申请人： SIKORSKY AIRCRAFT CORPORATION

发明人： Sunny K. SIU ,  Cody FEGELY ,  Kenneth S. WITTMER ,  John KNAG ,  Aaron L. GREENFIELD

IPC分类号： B64C11/44 ,  B64C27/10 ,  B64C27/82

CPC分类号： B64C11/44 ,  B64C27/10 ,  B64C27/82 ,  B64C2027/8236 ,  B64C2027/8272 ,  B64C2027/8281

摘要： A method for controlling a propeller of an aircraft, comprises receiving, with a processor, one or more signals indicative of commanded collective pitch of the propeller; receiving, with the processor, one or more sensed signals indicative of propeller axial speed, propeller rotational speed, and air density; estimating, with the processor, a propeller torque and propeller thrust from one or more of the propeller axial speed, the propeller rotational speed, and the air density; determining, with the processor, information indicative of an error value between a desired torque and a measured torque in the propeller; determining, with the processor, information indicative of a corrected pitch command in response to the determining of the error value; combining, with the processor, the corrected pitch command with the propeller rotational speed into an adjustment solution; providing, with the processor, the propeller with the adjustment solution.