公开(公告)号：EP3724067B1

公开(公告)日：2024-07-17

申请号：EP18888882.0

申请日：2018-12-12

IPC分类号： B64C3/58 ,  B64C23/06

CPC分类号： B64C3/58 ,  Y02T50/10 ,  B64C23/069

公开(公告)号：EP3867145B1

公开(公告)日：2024-05-22

申请号：EP19816439.4

申请日：2019-12-02

IPC分类号： B64C23/06 ,  B64C7/00 ,  B64C3/38 ,  B64C3/54 ,  B64C3/56

CPC分类号： B64C3/38 ,  B64C7/00 ,  B64C3/546 ,  B64C3/56 ,  B64C23/072

公开(公告)号：EP4126672B1

公开(公告)日：2024-04-24

申请号：EP21717152.9

申请日：2021-03-23

IPC分类号： B64D27/02 ,  B64D27/24 ,  B64C23/06

CPC分类号： B64D27/02 ,  B64D27/24 ,  B64C23/065 ,  Y02T50/60 ,  Y02T50/10 ,  B64D27/026

公开(公告)号：EP4015389B1

公开(公告)日：2024-04-10

申请号：EP20383125.0

申请日：2020-12-21

发明人： ALVARO GRANERO, David ,  REDONDO GARCIA, Daniel ,  MARTINO GONZALEZ, Esteban ,  PRIETO PADILLA, Juan Tomas

IPC分类号： B64D13/06 ,  B64D41/00 ,  B64D27/24 ,  B64C23/06 ,  B64D15/04

公开(公告)号：EP3643620B1

公开(公告)日：2024-03-20

申请号：EP18201803.6

申请日：2018-10-22

发明人： JHA, Anil Kumar ,  HESSLING-von HEIMENDAHL, Andre ,  DEPTA, Marion ,  MENNE, Norbert

IPC分类号： B64D47/02 ,  B64C23/06

公开(公告)号：EP4282750A1

公开(公告)日：2023-11-29

申请号：EP23175059.7

申请日：2023-05-24

申请人： Airbus Operations Limited

发明人： BATE, Christopher Alan

IPC分类号： B64C3/56 ,  B64C23/06

摘要： A wing assembly (200) for an aircraft (1) has an actuation assembly configured to move a wing tip device (300) between a flight configuration and a ground configuration. The actuation assembly comprises at least two linear actuation devices (530, 540) mounted within the wing assembly (200). A wing (210) and a wing tip device (300) for the wing assembly (200), and an aircraft (1) comprising the wing assembly (200), wing (210) or wing tip (300), are also described.

公开(公告)号：EP4015371B1

公开(公告)日：2023-11-29

申请号：EP21203546.3

申请日：2021-10-19

发明人： COMMIS, Ben

IPC分类号： B64C23/06 ,  B64C13/16

公开(公告)号：EP4276013A1

公开(公告)日：2023-11-15

申请号：EP22275061.4

申请日：2022-05-09

申请人： BAE SYSTEMS plc

发明人： The designation of the inventor has not yet been filed

IPC分类号： B64C21/10 ,  B64C23/06

摘要： There is provided a control surface arrangement for influencing fluid flow about a vehicle, the control surface arrangement comprising: a first control surface portion; a second control surface portion, the second control surface provided downstream of the first control surface portion relative to a fluid flow direction, the second control surface portion configured to be moveable relative to the first control surface portion; and a vortex generator surface arrangement arranged to induce vortices in a fluid flow passing over the first control surface portion and/or the second control surface portion.

公开(公告)号：EP3546342B1

公开(公告)日：2023-11-15

申请号：EP19175377.1

申请日：2013-08-09

发明人： Dees, Paul W. ,  Good, Mark S. ,  Sakurai, Seiya ,  Kordel, Jan A. ,  Fox, Stephen J. ,  Lassen, Matthew A. ,  Fox, Bruce R. ,  Walker, Steven Paul ,  Santini, Gregory M.

IPC分类号： B64C3/56 ,  B64C23/06

公开(公告)号：EP4230523A1

公开(公告)日：2023-08-23

申请号：EP23171219.1

申请日：2021-06-08

申请人： Textron Innovations Inc.

发明人： ROSS, Brent ,  GRONINGA, Kirk ,  IVANS, Steven ,  HURST, Jason

IPC分类号： B64C29/00 ,  B64C3/38 ,  B64C5/02 ,  B64C23/06 ,  B64C27/28 ,  B64C39/04 ,  B64C27/82 ,  B64U50/19

摘要： Embodiments include an aircraft (400) comprising: a fuselage (402); a wing (404a, 404b) connected to the fuselage (402); and first and second propulsion systems (408a, 408b, 412a, 412b) connected to the wing on opposite sides of the fuselage (402), wherein at least a portion of each of the first and second propulsion systems (408a, 408b, 412a, 412b) are tiltable between a first position in which the aircraft (400) is in a hover mode and a second position in which the aircraft is in a cruise mode; wherein each of the first and second propulsion systems (408a, 408b, 412a, 412b) includes pylon and a rotor assembly comprising a plurality of rotor blades.