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1. 发明授权

EP3880555B1 DOUBLE WING AIRCRAFT 有权
公开(公告)号：EP3880555B1
公开(公告)日：2024-08-28
申请号：EP19884368.2
申请日：2019-10-28
IPC分类号： B64C3/32 , B64C3/10 , B64C39/10 , B64C39/08
CPC分类号： B64C3/10 , B64C3/32 , B64C39/08 , B64C39/10 , B64C2039/10520130101 , Y02T50/10

2. 发明公开

EP4288338A1 HYBRID INFLATABLE AIRCRAFT OF THE UNMANNED TYPE 审中-实审
公开(公告)号：EP4288338A1
公开(公告)日：2023-12-13
申请号：EP22704794.1
申请日：2022-01-13
申请人： C.I.R.A. (Centro Italiano Ricerche Aerospaziali) - S.C.P.A.
发明人： PERSECHINO, Giuseppe , BARANIELLO, Vincenzo Rosario , BORSA, Roberto
IPC分类号： B64C3/10

3. 发明授权

EP3867498B1 STRUCTURE PROFILEE POUR AERONEF OU TURBOMACHINE 有权
公开(公告)号：EP3867498B1
公开(公告)日：2023-04-19
申请号：EP19795038.9
申请日：2019-09-24
发明人： GEA AGUILERA, Fernando , BARRIER, Raphaël , GRUBER, Mathieu Simon Paul , POLACSEK, Cyril , POSSON, Hélène Dominique Jeanne
IPC分类号： F01D5/14 , B64C3/14 , B64C11/18 , B64C21/00 , F04D29/32 , B64C3/10 , B64C5/02 , F04D29/66 , F04D29/68

4. 发明公开

EP4151519A1 AÉRONEF COMPRENANT UN FUSELAGE ET DES AILES PRÉSENTANT CHACUNE UNE PARTIE EXTERNE ET UNE PARTIE INTERNE ÉLARGIE ENTRE LE FUSELAGE ET LA PARTIE EXTERNE 审中-实审
公开(公告)号：EP4151519A1
公开(公告)日：2023-03-22
申请号：EP22194721.1
申请日：2022-09-08
申请人： Airbus SAS , Airbus Operations SAS
发明人： BOOTH, Andrew , LAVERNE, Julien , FORBES, Alistair
IPC分类号： B64C1/00 , B64C3/10
摘要： L'invention a pour objet un aéronef comprenant un fuselage (32), des première et deuxième ailes (34.1, 34.2) positionnées de part et d'autre du fuselage (32), caractérisé en ce que chaque aile (34.1, 34.2) comprend une partie interne (48.1, 48.2) reliée au fuselage (32) et une partie externe (50.1, 50.2) prolongeant la partie interne (48.1, 48.2), l'extrémité (56.2) de chaque partie interne (48.1, 48.2) reliée au fuselage (32) présentant une hauteur supérieure à la moitié de la hauteur du fuselage et s'étendant sur une longueur supérieure ou égale à la moitié d'une distance séparant les pointes avant et arrière (42.1, 42.2) du fuselage (32).

5. 发明授权

EP3509943B1 MODULAR VEHICLE SYSTEM 有权
公开(公告)号：EP3509943B1
公开(公告)日：2022-04-20
申请号：EP17848297.2
申请日：2017-09-11
发明人： BUBLITSKY, Ron
IPC分类号： B64C3/10 , B64C39/02

6. 发明授权

EP3480427B1 AEROFOIL 有权转让
公开(公告)号：EP3480427B1
公开(公告)日：2020-02-26
申请号：EP18198009.5
申请日：2018-10-01
申请人： Rolls-Royce plc
发明人： Paruchuri, Chaitanya , Joseph, Philip
IPC分类号： F01D5/14 , B64C3/10 , B64C3/14 , B64C11/18 , B63H1/26

7. 发明公开

EP3507461A1 BIOMIMETIC AIRFOIL BODIES AND METHODS OF DESIGNING AND MAKING SAME 有权转让
公开(公告)号：EP3507461A1
公开(公告)日：2019-07-10
申请号：EP17847522.4
申请日：2017-08-31
申请人： Shormann, David, E.
发明人： Shormann, David, E.
IPC分类号： F01D5/14 , B64C3/10 , B64C3/14 , B64C3/28 , F01D5/12 , F01D5/16 , F01D1/06

8. 发明公开

EP3476720A1 FLUID SYSTEMS THAT INCLUDE A CO-FLOW JET 审中-实审
公开(公告)号：EP3476720A1
公开(公告)日：2019-05-01
申请号：EP18202156.8
申请日：2018-10-23
申请人： Coflow Jet, LLC
发明人： ZHA, Gecheng
IPC分类号： B64C3/10 , B64C3/36 , B64C21/02
摘要： Fluid systems are described herein. An example embodiment of a fluid system has a first body portion (12), a second body portion (14), a plurality of supports, a plurality of fluid pressurizers (18), and a plurality of ducts (132). The first body portion and the second body portion cooperatively define an injection opening (58), a suction opening (104), and a channel that extends from the injection opening to the suction opening. The fluid pressurizer is disposed within the channel cooperatively defined by the first body portion and the second body portion. Each duct of the plurality of ducts is disposed within the channel cooperatively defined by the first body portion and the second body portion.

9. 发明授权

EP2448819B1 WING AND PROPELLER SYSTEM, METHOD OF OPTIMIZING WING AND PROPELLER/ROTOR SYSTEM AND METHOD OF REDUCING INDUCED DRAG 有权
公开(公告)号：EP2448819B1
公开(公告)日：2018-09-12
申请号：EP10809638.9
申请日：2010-07-05
申请人： Jawaharlal Nehru Centre For Advanced Scientific Research
发明人： NARASIMHA, Roddam , DESHPANDE, Suresh, Madhusudan , PRAVEEN, Chandrashekarappa , RAKSHITH, Belur, Raghavan
IPC分类号： B64F5/00 , G06F17/10 , B64C3/10 , G06Q99/00 , B64C39/10 , B64C3/00
CPC分类号： B64C3/00 , B64C39/10 , Y02T50/12
摘要： The disclosure relates to Aeronautics, more particularly relating to wing planforms that reduce wing drag substantially in aircraft driven by propellers or other rotors in tractor configuration. An aircraft comprising a wing and propeller system (1), said system comprising wing planform (2) characterized into wing chord regions (3) behind each propeller/rotor (5) whose length is relatively varied with respect to length of wing chord regions (4) at outboard of the propeller/rotor (5) towards wing tip and/or at inboard of the propeller (5) towards fuselage, and plurality of propellers (5) fixed ahead of wing leading edge such that induced drag is reduced by exploiting the velocity field generated by the slipstream of the propeller (5). Also, provides for a method of optimizing wing and propeller system and a method reducing induced drag, among other possible parameters of interest.

10. 发明公开

EP3305656A1 WING, FLAP, AND AIRCRAFT 有权
标题翻译： WING，FLAP和AIRCRAFT
公开(公告)号：EP3305656A1
公开(公告)日：2018-04-11
申请号：EP16799702.2
申请日：2016-04-14
申请人： Japan Aerospace Exploration Agency
发明人： MURAYAMA, Mitsuhiro , YAMAMOTO, Kazuomi
IPC分类号： B64C9/18 , B64C3/10 , B64C23/06
CPC分类号： B64C9/20 , B64C3/10 , B64C9/18 , B64C23/06 , Y02T50/162
摘要： [Object] To reduce noise resulting from a wing tip vortex of a wing such as a flap.
[Solving Means] A flap 3 of an aircraft includes a flap main body 8 provided to a parent wing 2 in a deployable manner, and a vortex generation portion 50 including a protruding member 5, the protruding member 5 being provided to protrude from an upper surface 301 at least at an end 40 of the flap main body 8 on an outboard side OTB in a span direction D2 and forming a predetermined angle to an axial direction D1 of the aircraft. A rear end 52 of the protruding member 5 is located on the side adjacent to a side-end edge 301A at the end 40 of the flap main body 8 in the span direction D2 relative to a virtual line VL passing through a front end 51 of the protruding member 5 and being parallel to the axial direction D1.
摘要翻译： [目的]减少机翼的翼尖涡流如翼片产生的噪音。 [解决手段]飞行器的翼3包括以可展开的方式设置于主翼2的翼主体8和包括突出构件5的涡流产生部50，突出构件5设置成从上部至少在外侧OTB上的翼片主体8的端部40处在跨度方向D2上并且与飞行器的轴向方向D1形成预定角度。突出构件5的后端52相对于通过前端51的假想线VL，位于翼片主体8的端部40处的翼端方向D2上的侧端缘301A侧突出构件5并平行于轴向方向D1。

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