专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

EP3878752B1 VERTICAL TAKEOFF AND LANDING AIRCRAFT USING HYBRID ELECTRIC PROPULSION SYSTEM AND CONTROL METHOD THEREFOR 有权
公开(公告)号：EP3878752B1
公开(公告)日：2024-04-17
申请号：EP19883087.9
申请日：2019-10-29
IPC分类号： B64D27/02 , B64C29/00 , B64C11/46 , B64D35/00 , B64D31/00 , B64D41/00
CPC分类号： B64D27/02 , B64D31/00 , Y02T50/40 , B64C29/0025 , B64C29/0083 , Y02T50/60 , B64D27/026

2. 发明授权

EP3640450B1 A METHOD OF OPERATING AN AIRCRAFT HYBRID GAS TURBOFAN AND RELATIVE HYBRID GAS TURBOFAN 有权
公开(公告)号：EP3640450B1
公开(公告)日：2024-04-17
申请号：EP19191061.1
申请日：2019-08-09
IPC分类号： F02C6/02 , B64D27/02
CPC分类号： F05D2220/5020130101 , F05D2220/7620130101 , F02C6/02 , B60L50/10 , F01D13/02 , F01D13/00 , F01D15/10 , F02C9/42 , Y02T50/60 , B60L2200/1020130101 , B64D31/00 , B64D27/02 , B64D35/00 , B64D41/00 , Y02T10/7072 , B64D27/026

3. 发明公开

EP3412575A1 HYBRID-ELECTRIC PROPULSION SYSTEM FOR AN AIRCRAFT 有权
公开(公告)号：EP3412575A1
公开(公告)日：2018-12-12
申请号：EP18176481.2
申请日：2018-06-07
申请人： General Electric Company
发明人： ADIBHATLA, Sridhar , HON, Robert Charles , GANSLER, Michael Thomas
IPC分类号： B64D27/20 , B64D27/24 , F02C3/113 , F02C7/36 , F02K5/00 , B64D27/02
CPC分类号： B64D27/24 , B64D27/02 , B64D27/10 , B64D31/02 , B64D31/06 , B64D35/08 , B64D2027/026 , F02C3/113 , F02C7/36 , F02C9/42 , F02K5/00 , F05D2220/76 , F05D2270/304
摘要： A hybrid-electric propulsion system 50 for an aircraft 10 includes a turbomachine 102, the turbomachine 102 including a first spool 124 and a second spool 122. A method 400 of operating the hybrid-electric propulsion system includes operating at 402, by one or more computing devices, the turbomachine such that the first spool mechanically drives a prime propulsor of the hybrid-electric propulsion system; and modifying at 404, by the one or more computing devices, a speed relationship parameter defined between the first spool and second spool by providing electrical power to, or drawing electrical power from, an electric machine mechanically coupled to the first spool, the second spool, or both.

4. 发明授权

EP3093235B1 AIRCRAFT 有权
公开(公告)号：EP3093235B1
公开(公告)日：2018-11-21
申请号：EP16166183.0
申请日：2016-04-20
申请人： Rolls-Royce plc
发明人： Moxon, Matthew
IPC分类号： B64C15/00 , B64C21/00 , B64D27/00 , B64D33/02 , B64D27/02
CPC分类号： B64D33/02 , B64C3/50 , B64C11/001 , B64C15/00 , B64C21/00 , B64D27/02 , B64D27/10 , B64D27/24 , B64D29/04 , B64D33/04 , B64D2027/026 , B64D2033/0226 , Y02T50/166 , Y02T50/44
摘要： An aircraft (10) comprises trailing edge flaps (17), a wing mounted propulsor (26) positioned such that the flaps (17) are located in a slipstream of the first propulsor in use when deployed. The aircraft (10) further comprises a thrust vectorable propulsor configured to selectively vary the exhaust efflux vector of the propulsor in at least one plane. The thrust vectorable propulsor comprises a ducted fan (30) configurable between a first mode, in which the fan (30) provides net forward thrust to the aircraft (10), and a second mode in which the fan (30) provides net drag to the aircraft. (10). The fan (30) is positioned to ingest a boundary layer airflow in use when operating in the first mode.

5. 发明授权

EP3187420B1 AIRCRAFT WITH REAR MOUNTED ENGINES 有权
公开(公告)号：EP3187420B1
公开(公告)日：2018-05-23
申请号：EP15382681.3
申请日：2015-12-31
申请人： Airbus Operations S.L.
发明人： MARTÍNEZ MUÑOZ, José Luis
IPC分类号： B64D27/02
CPC分类号： B64D27/02 , B64D2027/005 , Y02T50/44 , Y02T50/66
摘要： Aircraft (1, 1') with rear mounted engines (2, 2'), comprising a vertical tail plane (3) and a horizontal tail plane (4), in which the engines (2, 2') are mounted on top of the horizontal tail plane (4), such that the horizontal tail plane (4) comprises an inner fixed part (5) attached to the fuselage (8) of the aircraft (1, 1'), the inner fixed part (5) comprising an elevator (7), and two outer movable parts (6), each one of the outer movable parts (6) being located at each side end of the horizontal tail plane (4) which is furthest away from the fuselage (8) of the aircraft (1, 1'), such that both the inner fixed part (5) and the outer movable parts (6) are at least partially subjected to the flow coming from the engines (2, 2') when they are in use.

6. 发明公开

EP3318495A1 SYSTEM AND METHOD FOR TEMPORARY AUGMENTING POWER FROM A PRIMARY POWER PLANT 有权
标题翻译：用于临时增加来自主电厂电力的系统和方法
公开(公告)号：EP3318495A1
公开(公告)日：2018-05-09
申请号：EP17180516.1
申请日：2017-07-10
申请人： The Boeing Company
发明人： GOLSHANY, Sina S. , ERICKSON, Todd W. , ALDERKS, Derek R.
IPC分类号： B64D35/08 , B64D31/06 , B64D27/16 , B64D27/24 , B64D27/02 , F02C7/36
CPC分类号： B64D35/08 , B64D27/02 , B64D27/16 , B64D27/24 , B64D31/06 , B64D2027/026 , F02C6/06 , F02C7/36 , F05D2220/323 , F05D2220/70 , F05D2260/4023
摘要： An aircraft propulsion system (1300) includes a fan (602), a primary powerplant (606), an augmenting powerplant (608) and a controller (610). The primary powerplant (606) is coupled to the fan (602) and configured to rotate the fan (602) during a first flight stage and during a second flight stage. The augmenting powerplant (608) is coupleable with the fan (602). The controller (610) is configured to cause the augmenting powerplant (608) to drive the fan (602) during the first flight stage, and to cause the augmenting powerplant (608) to cease driving the fan (602) based on an indication of a transition from the first flight stage to the second flight stage.
摘要翻译：飞行器推进系统（1300）包括风扇（602），主动力装置（606），增强动力装置（608）和控制器（610）。主动力装置（606）联接到风扇（602）并且构造成在第一飞行阶段和第二飞行阶段期间旋转风扇（602）。增强动力装置（608）可与风扇（602）联接。控制器（610）被配置成使增强动力装置（608）在第一飞行阶段期间驱动风扇（602），并且基于以下指示使增强动力装置（608）停止驱动风扇（602）从第一飞行阶段过渡到第二飞行阶段。

7. 发明公开

EP2607236A3 Apparatus and method for paragliders 审中-公开
标题翻译：滑翔伞的装置和方法
公开(公告)号：EP2607236A3
公开(公告)日：2017-11-22
申请号：EP12197743.3
申请日：2012-12-18
申请人： Dreamscience Propulsion Limited
发明人： Contoret, Adam Edward Alexander
IPC分类号： B64D27/02 , B64D27/24
CPC分类号： B64C39/026 , B64C31/028 , B64C31/036 , B64D17/30 , B64D27/02 , B64D27/24 , Y02T50/62
摘要： Apparatus (10) and method for propelling a user wearing paragliding equipment are disclosed The apparatus includes at least one thruster (16) for providing thrust in a predetermined direction; and an attachment element f(34) or attaching the at least one thruster to a user's body such that the thruster is secured against the front portion of the user's body.
摘要翻译：公开了用于推进佩戴滑翔伞设备的用户的设备（10）和方法。该设备包括用于沿预定方向提供推力的至少一个推进器（16）和附接元件f（34），或者将所述至少一个推进器附接至使用者的身体，使得所述推进器抵靠使用者身体的前部被固定。

8. 发明公开

EP3228544A1 HYBRID ELECTRIC AIRCRAFT PROPULSION INCORPORATING A RECUPERATED PRIME MOVER 审中-公开
标题翻译：混合式电动飞机推进装备了一种再生式发动机
公开(公告)号：EP3228544A1
公开(公告)日：2017-10-11
申请号：EP17165254.8
申请日：2017-04-06
申请人： Hamilton Sundstrand Corporation
发明人： HIMMELMANN, Richard A. , TONGUE, Stephen E.
IPC分类号： B64D27/02 , F02C3/04 , B64D27/10
CPC分类号： B64D27/24 , B60Y2400/112 , B60Y2400/431 , B60Y2400/602 , B64D27/02 , B64D27/10 , B64D2027/026 , F01D15/10 , F02C3/04 , F02C3/34 , F02C6/00 , F02C7/10 , F02K3/00 , F02K5/00 , F05D2220/323 , F05D2220/76 , Y02T50/64 , Y10S903/903
摘要： A hybrid-electric propulsion system (10) includes a gas turbine engine (12), an electric machine (14) coupled to and rotatably driven by the gas turbine engine to produce AC electric power, an energy storage system (18), and a propulsion unit (16). The gas turbine engine includes a combustor (26) and a recuperator (20) that places an exhaust air flow that is downstream from the combustor in a heat exchange relationship with a compressed air flow that is upstream from the combustor to transfer thermal energy from the exhaust flow to the compressed flow. The propulsion unit includes a fan (44) and an electric motor (42) rotably coupled to the fan, the electric motor being driven by electric power from one of the electric machine or the energy storage system.
摘要翻译：一种混合动力电动推进系统（10），包括燃气涡轮发动机（12），联接到燃气涡轮发动机并由燃气涡轮发动机可旋转地驱动以产生AC电力的电机（14），储能系统（18）和推进单元（16）。该燃气涡轮发动机包括燃烧器（26）和换热器（20），该换热器（20）将与燃烧器上游的压缩空气流成换热关系的位于燃烧器下游的排气流放置成从燃烧器排气流向压缩流。推进单元包括风扇（44）和可旋转地联接到风扇的电动机（42），电动机由来自电机或能量存储系统之一的电力驱动。

9. 发明公开

EP3165453A1 METHOD AND SYSTEM FOR CROSS ENGINE DEBRIS AVOIDANCE 审中-公开
标题翻译：方法和系统避免了交叉WRAPPING碎片电机间
公开(公告)号：EP3165453A1
公开(公告)日：2017-05-10
申请号：EP16194096.0
申请日：2016-10-17
申请人： General Electric Company
发明人： MILLER, Brandon Wayne , PRENTICE, Ian Francis
IPC分类号： B64C11/48 , B64D27/00
CPC分类号： B64D27/02 , B64C11/48 , B64D27/12 , B64D2027/005 , Y02T50/66
摘要： A propulsion system 300,400,500,600,700,800 for an aircraft 100 includes at least two propulsion engines 202,212. Each propulsion engine 202,212 with a longitudinal rotational axis 206,216, and a propulsive fan 204,214 associated with each propulsion engine 202,212 rotates in a plane 208,218 perpendicular to the longitudinal rotational axis 206,216. Each plane 208,218 is at least one of: spaced axially along a longitudinal axis of the aircraft 100, and canted such that each plane 208,218 does not intersect any other plane 208,218 associated with another propulsion engine 202,212 and propulsive fan 204,214.
摘要翻译：为300,400,500,600,700,800到100架飞机的推进系统，包括至少两个推进发动机202.212。每个推进发动机202.212具有纵向旋转轴线206.216，以及与每个推进引擎202.212旋转的平面中垂直于纵向208.218旋转轴线206.216相关联的推进风扇204.214。每个计划208.218是中的至少一个：沿飞行器100的纵向轴线轴向地间隔开，并且倾斜的搜索做每个计划208.218不相交与另一推进引擎202.212和204.214推进风扇相关联的任何其他计划208.218。

10. 发明公开

EP3095695A1 PROCEDE POUR ACTIVER UN MOTEUR ELECTRIQUE D'UNE INSTALLATION HYBRIDE D'UN AERONEF MULTIMOTEUR, ET UN AERONEF 有权
标题翻译：控制方法的多引擎飞机的混合动力系统的电动机以及相应的飞机
公开(公告)号：EP3095695A1
公开(公告)日：2016-11-23
申请号：EP16167495.7
申请日：2016-04-28
申请人： Airbus Helicopters
发明人： ROSSOTTO, Régis
IPC分类号： B64C27/12 , B64D27/02
CPC分类号： B64C27/14 , B64C27/12 , B64D27/02 , B64D27/10 , B64D27/24 , B64D2027/026 , Y02T50/64
摘要： La présente invention concerne un procédé pour entraîner en rotation un rotor (2) d'un aéronef (1), ledit aéronef (1) comportant au moins deux moteurs thermiques (10) et un moteur électrique (50) aptes à entraîner en rotation ledit rotor (2). On entraîne ledit rotor (2) en sollicitant lesdits moteurs thermiques (10) conjointement. On génère une autorisation uniquement durant au moins une phase de vol prédéterminée, ladite autorisation autorisant l'utilisation du moteur électrique (50) afin d'entraîner en rotation ledit rotor (2). Lorsque ladite autorisation est générée, on génère un ordre de fonctionnement pour requérir le fonctionnement dudit moteur électrique (50) si un desdits moteurs thermiques (10) est en panne. Lorsque ledit ordre de fonctionnement est généré, on entraîne ledit rotor (2) conjointement avec chaque moteur thermique (10) qui n'est pas en panne et ledit moteur électrique (50).
摘要翻译：驱动飞机的转子的旋转的方法，所述具有至少两个燃料燃烧发动机和一种适用于驱动所述转子的旋转电动机的飞机。所述转子是通过使用所述发动机一起被驱动。仅在飞行的至少一个预定阶段中产生的授权，所述授权授权使用电动马达，以便驱动所述转子旋转。而所述授权是有效的，如果所述发动机中的一个出现故障，则在操作顺序生成要求所述电动马达来操作。而所述操作命令是有效的，所述转子是由每个发动机驱动与所述电动机并处理不当失败在一起。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式