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51. 发明授权

EP3222518B1 DOUBLE-PROPELLER AIRCRAFT 有权
公开(公告)号：EP3222518B1
公开(公告)日：2019-01-02
申请号：EP16164294.7
申请日：2016-04-07
申请人： Robby Moto Engineering S.r.l.
发明人： Papetti, Roberto
IPC分类号： B64C11/06 , B64C11/30 , B64C11/48 , B64D27/08 , B64D35/06 , B64D35/08

52. 发明公开

EP3222518A1 DOUBLE-PROPELLER AIRCRAFT 有权
标题翻译：双螺旋桨飞机
公开(公告)号：EP3222518A1
公开(公告)日：2017-09-27
申请号：EP16164294.7
申请日：2016-04-07
申请人： Robby Moto Engineering S.r.l.
发明人： Papetti, Roberto
IPC分类号： B64C11/06 , B64C11/30 , B64C11/48 , B64D27/08 , B64D35/06 , B64D35/08
CPC分类号： B64C11/306 , B64C11/06 , B64C11/48 , B64D27/08 , B64D35/06 , B64D35/08
摘要： The double-propeller aircraft (1) comprises a fixed wing structure (2, 3, 4) for the flight of said aircraft (1) and at least a propulsion system (5), wherein the propulsion system (5) comprises:
- a first piston engine (6) to put a first drive shaft (7) in rotation around a first axis of rotation (A) substantially horizontal;
- a second piston engine (8) to put a second drive shaft (9) in rotation around a second axis of rotation (B) substantially horizontal and parallel to the first axis of rotation (A);
- a first propeller (17) keyed on the first drive shaft (7);
- a second propeller (21) mounted idle on the first drive shaft (7), the first propeller (17) and the second propeller (21) being coaxial and counterrotating the one to the other with respect to the first axis of rotation (A);
- transmission means (27, 28, 29) interposed between the second drive shaft (9) and the second propeller (21) for the transmission of motion from the second drive shaft (9) to the second propeller (21).
摘要翻译：双螺旋桨飞行器（1）包括固定机翼结构（2，3，4）的所述飞行器（1）和至少一个推进系统（5），其特征在于，所述推进系统（5）包括飞行： - 一个第一活塞发动机（6），用于使第一驱动轴（7）围绕基本上水平的第一旋转轴线（A）旋转; - 第二活塞发动机（8），用于使第二驱动轴（9）围绕基本上水平且平行于所述第一旋转轴线（A）的第二旋转轴线（B）旋转; - 键合在第一驱动轴（7）上的第一螺旋桨（17）; - 第二推进器（21）安装在第一驱动轴（7），所述第一推进器（17）和所述第二推进器（21）是同轴的和反向旋转的一个到另一个相对于所述第一旋转轴空转（A ）; - 第二驱动轴（9）和用于运动的从第二驱动轴（9）到所述第二推进器（21）发送所述第二推进器（21）之间传输装置（27，28，29）。

53. 发明授权

EP2675705B1 TRIEBWERK FÜR EIN LUFTFAHRZEUG MIT GEGENLÄUFIGEN PROPELLERN 有权转让
标题翻译： TRIEBWERKFÜREIN LUFTFAHRZEUG MITGEGENLÄUFIGENPROPELLERN
公开(公告)号：EP2675705B1
公开(公告)日：2017-01-11
申请号：EP12700650.0
申请日：2012-01-12
申请人： Airbus Defence and Space GmbH
发明人： BAUER, Michael , PONGRATZ, Reinhard , REDMANN, Daniel
IPC分类号： B64C11/18 , B64C11/48
CPC分类号： B64C11/18 , B64C11/48 , B64C2230/14 , B64C2230/22 , B64C2230/28 , B64D2027/005 , Y02T50/166 , Y02T50/66

54. 发明公开

EP2979979A1 SYSTEMS AND METHODS FOR COUNTERING AN UNMANNED AIR VEHICLE 有权
标题翻译：圣彼得堡ZENG ENTGEGNEN EINEES UNBEMANNTEN LUFTFAHRZEUGS
公开(公告)号：EP2979979A1
公开(公告)日：2016-02-03
申请号：EP15178375.0
申请日：2015-07-24
申请人： Insitu, Inc.
发明人： GOODRICH, Wayne
IPC分类号： B64C39/02 , B64C11/48
CPC分类号： B64C39/024 , B64C5/06 , B64C11/48 , B64C2201/042 , B64C2201/108 , B64C2201/121 , B64C2201/141 , B64C2201/162 , F41H11/02 , F41H13/0006 , G05D1/12
摘要： Systems and methods for countering an unmanned air vehicle are disclosed. Representative methods include directing an interceptor UAV (140) toward a target UAV (199), and directing the interceptor UAV back to ground along a controlled flight path, for example, in response to an instruction not to engage with the target UAV, and/or in response to an unsuccessful engagement. Another representative method includes disabling the target UAV by deploying a disabling element (e.g., a net) from the interceptor UAV to contact the target UAV. Representative systems include a target acquisition system, a launch control system, and an engagement system carried by the interceptor UAV. In particular embodiments, the interceptor UAV can have a generally cylindrical fuselage (112), one or more fins (114) carried by the fuselage, counter-rotating propellers (121a, 121b) carried by the fuselage, and a disabling system that is configured to disable the target UAV.
摘要翻译：公开了用于对抗无人驾驶飞行器的系统和方法。代表性的方法包括将拦截器UAV（140）引导到目标无人机（199），并且将拦截器UAV沿着受控飞行路径引导回地面，例如响应于不与目标UAV接合的指令，和/ 或响应不成功的参与。另一个代表性的方法包括通过从拦截器UAV部署禁用元件（例如网）来禁用目标UAV以接触目标UAV。代表性系统包括目标采集系统，发射控制系统和拦截机无人机所携带的接合系统。在特定实施例中，拦截器UAV可以具有大致圆柱形的机身（112），由机身承载的一个或多个翅片（114），由机身承载的反向旋转螺旋桨（121a，121b）和配置的禁用系统禁用目标无人机。

55. 发明公开

EP2809939A4 GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE 有权转让
标题翻译：带有传动炬的燃气轮机发动机的结构
公开(公告)号：EP2809939A4
公开(公告)日：2015-11-25
申请号：EP13786893
申请日：2013-01-29
申请人： UNITED TECHNOLOGIES CORP
发明人： KUPRATIS DANIEL BERNARD , SCHWARZ FREDERICK M
IPC分类号： B63H5/10 , B64C11/48 , B64C27/10 , F02C1/00 , F02C1/06 , F02C3/00 , F02C3/10 , F02C3/107 , F02C3/36 , F02C6/00 , F02K3/00 , F02K3/02 , F02K3/04 , F02K3/06 , F02K3/072
CPC分类号： F02C7/36 , F01D5/06 , F01D9/02 , F01D9/065 , F02C3/04 , F02C3/107 , F02C3/36 , F02C7/06 , F02C9/18 , F02K1/78 , F02K3/04 , F02K3/06 , F02K3/072 , F04D27/009 , F04D29/325 , F05D2220/32 , F05D2220/323 , F05D2240/12 , F05D2240/35 , F05D2240/60 , F05D2260/4031 , F05D2260/40311 , Y02T50/671
摘要： A gas turbine engine (20) typically includes a fan section (22), a compressor section (24), a combustor section (26) and a turbine section (28). A speed reduction device such as an epicyclical gear assembly (48) may be utilized to drive the fan section (22) such that the fan section (22) may rotate at a speed different than the turbine section (28) so as to increase the overall propulsive efficiency of the engine (20). In such engine architectures, a shaft (40) driven by a fan drive turbine section (46) provides an input to the epicyclical gear assembly (48) that drives the fan section (22) at a speed different than the fan drive turbine section (46) such that both the fan drive turbine section (46) and the fan section (22) can rotate at closer to optimal speeds providing increased performance attributes and performance.

56. 发明公开

EP2809940A4 GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE 审中-公开
公开(公告)号：EP2809940A4
公开(公告)日：2015-11-18
申请号：EP13777804
申请日：2013-01-29
申请人： UNITED TECHNOLOGIES CORP
发明人： KUPRATIS DANIEL BERNARD , SCHWARZ FREDERICK M
IPC分类号： B63H5/10 , B64C11/48 , B64C27/10 , F01D25/16 , F02C1/00 , F02C1/06 , F02C3/00 , F02C3/10 , F02C6/00 , F02C7/06 , F02K3/00 , F02K3/02 , F02K3/06 , F02K3/072
CPC分类号： F02C7/06 , F02K3/06 , F05D2260/40311 , Y02T50/671

57. 发明公开

EP2780227A4 METHODS AND APPARATUS FOR VERTICAL/SHORT TAKEOFF AND LANDING 审中-公开
标题翻译：方法和设备垂直/短的启动和着陆
公开(公告)号：EP2780227A4
公开(公告)日：2015-09-23
申请号：EP12849670
申请日：2012-11-13
申请人： RADEUS LABS INC
发明人： HAYDEN RAYMOND
IPC分类号： B64C11/48 , B64C27/10
CPC分类号： B64C39/024 , B64C27/20 , B64C27/39 , B64C27/46 , B64C29/00 , B64C2201/024 , B64C2201/027 , B64C2201/108 , B64C2201/12 , B64C2201/127 , B64C2201/146
摘要： Methods and apparatus for vertical or short takeoff and landing. In one embodiment, the apparatus comprises two or more counter driven rings with one or more airfoils attached. In one variant, there is an upper ring and a lower ring, each with multiple airfoils attached. In one variant, lift is generated largely via ambient air currents, allowing for long term on-station operation of the device.

58. 发明公开

EP2553251A4 ADAPTIVE FAN SYSTEM FOR A VARIABLE CYCLE TURBOFAN ENGINE 有权
标题翻译：自适应系统使用风扇TURBOFANLÜFTER可变冲程
公开(公告)号：EP2553251A4
公开(公告)日：2014-10-01
申请号：EP11798531
申请日：2011-03-27
申请人： ROLLS ROYCE NAM TECH INC
发明人： RESS ROBERT A JR , STRATTON STEVE , STARR MATTHEW J
IPC分类号： F02K3/077 , B64C11/48 , F02C3/113 , F02C7/32 , F02C7/36 , F02K3/06 , F02K3/075 , F16D47/04
CPC分类号： F02K3/075 , F02C3/113 , F02C7/32 , F02C7/36 , F02K3/06 , F02K3/077 , F05D2260/40 , F05D2260/4023 , F05D2260/40311 , F16D21/06 , F16D47/04 , Y02T50/671
摘要： An adaptive fan system for a variable cycle turbofan engine having at least one turbine, includes a shaft structured to receive mechanical power from a turbine in the variable cycle turbofan engine and a first fan stage that is coupled directly to the shaft and is driven directly by the shaft. A transmission system is coupled to the shaft and a second fan stage is coupled to the shaft via the transmission system and is driven by the shaft via the transmission system. The transmission system is structured to selectively vary a speed between high and low speeds at which power is supplied from the shaft to the second fan stage relative to at least one of the shaft and the first fan stage, wherein the first fan stage and the second fan stage are configured to rotate in the same direction and at the same high speed to increase the mechanical power of the turbine.

59. 发明公开

EP2697114A1 DISPOSITIF DE PROPULSION A HELICES CONTRAROTATIVES ET COAXIALES NON-CARENEES 有权
标题翻译：驱动装置MT制导GEGENDREHUNGS-和同轴旋翼
公开(公告)号：EP2697114A1
公开(公告)日：2014-02-19
申请号：EP12724669.2
申请日：2012-04-13
申请人： SNECMA , Centre De Recherche En Aeronautique Asbl - Cenaero
发明人： DEJEU, Clément, Marcel, Maurice , PASCAL, Sébastien , TALBOTEC, Jérôme , LEBORGNE, Michaël , LEPOT, Ingrid Irène Catherine
IPC分类号： B64C11/18 , B64C11/48 , B64C23/06
CPC分类号： F01D5/14 , B64C11/18 , B64C11/48 , B64D2027/005 , F02C3/067 , F02C3/10 , F05D2220/324 , F05D2220/325 , F05D2250/38 , Y02T50/66
摘要： The invention relates to the field of propulsion devices (1) having an unducted upstream rotor (8) and a counter-rotating and coaxial downstream rotor (9). At least one blade (13) of the upstream rotor (8) is configured so as to generate a co-rotating secondary vortex (11) for destabilizing, upstream of the downstream rotor (9), a blade-tip vortex (10) on the same blade (13).

60. 发明授权

EP2391536B1 TRIEBWERK, INSBESONDERE CROR-ANTRIEB, FÜR EIN FLUGZEUG 有权
标题翻译：发动机，尤其是CROR DRIVE FOR A平面
公开(公告)号：EP2391536B1
公开(公告)日：2013-09-18
申请号：EP10704341.6
申请日：2010-01-27
申请人： Deutsches Zentrum für Luft- und Raumfahrt e.V.
发明人： STÜRMER, Arne
IPC分类号： B64C11/48 , B64C11/30 , F02K3/072
CPC分类号： B64C11/48 , B64C11/308 , B64D2027/005 , F02K3/072 , Y02T50/66

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