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1. 发明申请

US20130168501A1 PRIMARY FLIGHT CONTROLS 有权
标题翻译：主要飞行控制
公开(公告)号：US20130168501A1
公开(公告)日：2013-07-04
申请号：US13534193
申请日：2012-06-27
申请人： Bruno Chaduc , Boris Grohmann , Christophe Tempier
发明人： Bruno Chaduc , Boris Grohmann , Christophe Tempier
IPC分类号： B64C27/625
CPC分类号： B64C27/625 , B64C13/503 , B64C27/64 , B64C27/68 , Y02T50/44
摘要： Primary flight controls (10) for main and/or tail rotors (4) of helicopters with electro-mechanical interface between any of fly-by-wire and/or fly-by-light controls and hydraulic servo actuators (8) for control force amplification towards said main and/or tail rotor controls (4). For each of the main and/or tail rotor controls (4) there is provided but one of the hydraulic servo actuators (8), connected by one mechanical linkage (7) to one electro motor (5), said one hydraulic servo actuator (8) being of the type having the one mechanical linkage (7) connected to its input (29) and its output (30) and the one electro motor (5) being of the direct drive type, the position of said electro motor (5) having a reference to said one mechanical linkage (7) and the torque delivered by said electro motor (5) to the hydraulic servo actuator (8) being related to the power consumption of said electro motor (5).
摘要翻译：用于直升机的主和/或尾转子（4）的主飞行控制（10），其具有在线控和/或飞越控制之间的电 - 机械接口和用于控制力的液压伺服致动器（8）朝向所述主和/或尾部转子控制器（4）的放大。对于每个主转子控制器和/或尾部转子控制器（4），只有一个液压伺服致动器（8）通过一个机械联动装置（7）连接到一个电动马达（5），所述一个液压伺服致动器 8）是具有连接到其输入端（29）和其输出端（30）的一个机械连杆（7）和一个电动机（5）是直接驱动型的类型，所述电动马达（5）的位置）和所述电动马达（5）传递到所述液压伺服驱动器（8）的扭矩与所述电动马达（5）的功率消耗有关。

2. 发明申请

US20130147242A1 DEVICE FOR PROTECTING AN INDIVIDUAL SITTING ON A SEAT, A SEAT, AND A VEHICLE 有权
标题翻译：用于保护座椅，座椅和车辆上的个人座椅的装置
公开(公告)号：US20130147242A1
公开(公告)日：2013-06-13
申请号：US13710538
申请日：2012-12-11
申请人： EUROCOPTER , EUROCOPTER DEUTSCHLAND GMBH , SCHROTH SAFETY PRODUCTS GMBH , FISCHER + ENTWICKLUNGEN GMBH & CO KG
发明人： Tomas Santana-Gallego , Ulf Gruene , Roland Bauer
IPC分类号： B60R21/231 , B60R22/00
CPC分类号： B60R21/23138 , B60R21/18 , B60R21/207 , B60R22/00 , B60R22/26 , B60R2021/0093 , B60R2021/2074 , B60R2021/2615 , B60R2022/027 , B60R2022/1843 , B64D11/062 , B64D11/06205 , B64D25/04 , B64D2201/00
摘要： A protection device (10) having a set (11) of protection inflatable members (15, 20, 25) including left and right inflatable lateral means (20, 25) that are suitable for co-operating respectively with the left and right shoulder straps (6, 7), said device (10) possessing an inflator (30) for inflating said protection inflatable members (15, 20, 25). The device includes a headrest (35) carrying a nape airbag (15) of said set of inflatable members (15, 20, 25), the nape airbag (15) including one passage (16, 17) per inflatable lateral means (20, 25) in order to convey fluid to each inflatable lateral means (20, 25), said headrest (35) being provided with a hollow support (40) carrying said inflator (30) and with a fluid diffusion box (50) arranged in the nape airbag (15) so as to convey a fluid from the inflator (30) to the nape airbag (15) and to the inflatable lateral means (20, 25).
摘要翻译：一种保护装置（10），其具有包括左和右可膨胀侧向装置（20,25）的保护性可充气构件（15,20,25）的组合（11），所述左右可膨胀横向装置适于与左肩肩带和右肩带（6,7），所述装置（10）具有用于使所述保护性可充气构件（15,20,25）膨胀的充气器（30）。该装置包括承载所述一组充气构件（15,20,25）的颈部安全气囊（15）的头枕（35），所述颈部安全气囊（15）包括每个可充气横向装置（20,20）的一个通道（16,17）为了将流体输送到每个可膨胀的侧向装置（20,25），所述头枕（35）设置有承载所述充气器（30）的中空支撑件（40）和布置在所述充气器中的流体扩散箱（50）从而将来自充气器（30）的流体输送到油包安全气囊（15）和可膨胀的横向装置（20,25）。

3. 发明申请

US20120241563A1 EMERGENCY PILOTING BY MEANS OF A SERIES ACTUATOR FOR A MANUAL FLIGHT CONTROL SYSTEM IN AN AIRCRAFT 有权
标题翻译：用于飞机上的手动飞行控制系统的系列执行机构的紧急引导
公开(公告)号：US20120241563A1
公开(公告)日：2012-09-27
申请号：US13417667
申请日：2012-03-12
申请人： Bruno Chaduc , Patrick Hellio , Bernard Gemmati , Karsten Krok
发明人： Bruno Chaduc , Patrick Hellio , Bernard Gemmati , Karsten Krok
IPC分类号： G05D1/00
CPC分类号： B64C13/30 , B64C13/42 , B64C27/58 , Y02T50/44
摘要： For emergency piloting of a manual flight control system (7) of an aircraft (1), in the event of flexible connection means (26) breaking, an upstream control device (8) takes authority over the electronic control unit (29) of series actuator (21). An output pivoting quadrant (25) is subjected by a centering rod (22) to a blocking and centering action. In the event of the system breaking, the output pivoting quadrant (25) forms a bearing point for the series actuator (21), so that an emergency control actuate a airfoil surface (11).
摘要翻译：对于飞机（1）的手动飞行控制系统（7）的紧急驾驶，在弹性连接装置（26）断开的情况下，上游控制装置（8）对系列的电子控制单元（29）进行授权致动器（21）。输出枢转象限（25）由定心杆（22）承受阻塞和定心作用。在系统断裂的情况下，输出枢转象限（25）形成用于串联致动器（21）的轴承点，使得紧急控制致动翼面（11）。

4. 发明申请

US20150125258A1 ROTARY WING AIRCRAFT HAVING TWO MAIN ENGINES TOGETHER WITH A LESS POWERFUL SECONDARY ENGINE, AND A CORRESPONDING METHOD 有权
标题翻译：具有两台主力发动机的旋转式飞机与一台功率较小的二次发动机相配合，以及相应的方法
公开(公告)号：US20150125258A1
公开(公告)日：2015-05-07
申请号：US14085034
申请日：2013-11-20
申请人： EUROCOPTER
发明人： Bernard Certain
IPC分类号： F01D13/00 , F01D15/12 , B64C27/12
CPC分类号： F01D13/003 , B64C27/12 , B64D35/08 , F01D15/12
摘要： An aircraft (1) having a rotary wing (2) and turboshaft engines (11, 12, 13) for driving said rotary wing (2). The aircraft then includes two main engines (11, 12) that are identical, each capable of operating at at least one specific rating associated with a main power (maxTOP, OEIcont), and a secondary engine (13) capable of operating at at least one specific rating by delivering secondary power (maxTOP′, OEIcont′) proportional to the corresponding main power (maxTOP, OEIcont) in application of a coefficient of proportionality (k) less than or equal to 0.5, said aircraft having a control system (20) for driving the rotary wing by causing each main engine (11, 12) to operate continuously throughout a flight, and by using the secondary engine (13) as a supplement during at least one predetermined specific stage of flight.
摘要翻译：具有用于驱动所述旋转翼（2）的旋翼（2）和涡轮轴发动机（11,12,13）的飞机（1）。飞机然后包括两个相同的主发动机（11,12），每个主发动机能够以至少一个与主功率（maxTOP，OEIcont）相关联的特定额定值和至少能够至少操作的次级发动机（13）所述飞机具有控制系统（20（20）），通过在小于或等于0.5的比例系数（k）的情况下提供与相应的主功率（maxTOP，OEIcont）成比例的次级功率（maxTOP'，OEIcont' ），用于通过使每个主发动机（11,12）在整个飞行中连续地操作并且在至少一个预定的特定飞行阶段期间通过使用二次发动机（13）作为补充来驱动旋转翼。

5. 发明申请

US20150028594A1 REVERSIBLE ELECTRICAL MACHINE FOR AN AIRCRAFT 有权
标题翻译：用于飞机的可逆电机
公开(公告)号：US20150028594A1
公开(公告)日：2015-01-29
申请号：US13945326
申请日：2013-07-18
申请人： Eurocopter
发明人： Damien Mariotto
IPC分类号： H02K7/18 , B64D27/24 , B64D35/02 , H02K7/108 , H02K16/00
CPC分类号： H02K7/1823 , B60L11/12 , B60L2200/10 , B60L2220/42 , B64C27/14 , B64D27/24 , B64D35/02 , B64D2027/026 , H02K7/006 , H02K7/108 , H02K16/00 , H02K16/02 , Y02E20/16 , Y02T10/641 , Y02T10/646 , Y02T10/7077 , Y02T50/64
摘要： A reversible electrical machine (1) comprising: a first electrical device (10) having a first stator (11) and a first rotor (12); a second electrical device (20) including a second rotor (22) and a second stator (21) together with an outlet shaft (50) and first disengageable coupling means (30) enabling said first and second rotors (12, 22) to be associated and dissociated in rotation. Said reversible electrical machine (1) also includes second disengageable coupling means (40) that are disengageable under a predetermined force and that mechanically connect said second rotor (22) to said outlet shaft (50). Said first electrical device (10) is a motor for transmitting high mechanical power to said outlet shaft (50), while said second electrical device (20) is a motor-generator for operating in motor mode to transmit additional mechanical power to said outlet shaft (50), and in generator mode for receiving mechanical power from said outlet shaft (50).
摘要翻译：一种可逆电机（1），包括：具有第一定子（11）和第一转子（12）的第一电气装置（10）包括第二转子（22）和第二定子（21）以及出口轴（50）和第一可脱离联接装置（30）的第二电气装置（20），使得所述第一和第二转子（12,22）能够是相关联和旋转分离。所述可逆电机（1）还包括可在预定力下分离并且将所述第二转子（22）机械地连接到所述出口轴（50）的第二可脱离联接装置（40）。所述第一电气设备（10）是用于将高机械功率传输到所述出口轴（50）的电动机，而所述第二电气设备（20）是用于以电动机模式操作的电动发电机，以将额外的机械动力传递到所述出口轴（50），以及用于从所述出口轴（50）接收机械动力的发电机模式。

6. 发明申请

US20140191613A1 ELECTRIC MACHINE WITH INTERMEDIATE PIECES HAVING MULTIPLE AIR GAPS AND A 3D MAGNETIC FLUX 有权
标题翻译：具有多个空气GAPS和3D磁通量的中间件的电机
公开(公告)号：US20140191613A1
公开(公告)日：2014-07-10
申请号：US14147987
申请日：2014-01-06
申请人： EUROCOPTER , MBDA FRANCE , SINTERTECH
发明人： Damien Mariotto
IPC分类号： H02K1/14
CPC分类号： H02K1/145 , H02K21/24 , H02K2201/12 , Y02E10/725
摘要： The present invention relates to an electric machine (1) consisting of a stator (10) that is provided with at least one exciter unit (11) consisting of a coil (12), at least two annular yokes (13a,13b) and at least one row of intermediate pieces (15), and a rotor (20) having a structure (21) and at least one receiver unit (22) consisting of at least two series (25) of at least two rows (24) of magnets (23). Two sides (131,132) of each yoke (13) consist of the first teeth (14), fitting with the said intermediate pieces (15) on a face (121) of the said exciter unit (11) and alternatingly forming the second north poles and the second south poles. Each series (23) is positioned opposite one face (121), forming an air gap (30) with the said exciter unit (11), with the electric machine (1) thus including at least two air gaps (30), with a flux F thus circulating inside the said electric machine (1), dividing and regrouping itself in the vicinity of the said magnets (23) and of the said yokes (13).
摘要翻译：本发明涉及一种由定子（10）构成的电机（1），该定子（10）设置有至少一个由线圈（12），至少两个环形轭（13a，13b）组成的激励器单元（11）至少一排中间件（15）和具有结构（21）的转子（20）和至少两个由至少两个（24）的磁体组成的系列（25）组成的接收器单元（22）（23）。每个轭架（13）的两侧（131,132）由所述第一齿（14）组成，所述第一齿（14）与所述中间件（15）配合在所述激励器单元（11）的一个面（121）上并交替地形成第二极和第二个南极。每个系列（23）与一个面（121）相对定位，与所述激励器单元（11）形成气隙（30），电机（1）因此包括至少两个空气间隙（30），其中焊剂F因此在所述电机（1）内循环，在所述磁体（23）和所述轭（13）附近分离和重组。

7. 发明申请

US20140170417A1 MULTI-LAYERED TRANSPARENCY AND METHOD OF PRODUCING SUCH A MULTI-LAYERED TRANSPARENCY 审中-公开
标题翻译：多层透明度和生产这种多层透明度的方法
公开(公告)号：US20140170417A1
公开(公告)日：2014-06-19
申请号：US14101432
申请日：2013-12-10
申请人： EUROCOPTER DEUTSCHLAND GMBH
发明人： Wolfgang Kreitmair-Steck , Johann Barnerssoi
IPC分类号： B64C1/14
CPC分类号： B64C1/1484 , B32B27/08 , B32B27/34 , B32B27/365 , B32B27/40 , B32B2250/40 , B32B2307/412 , B32B2307/554 , B32B2307/584 , B32B2307/71 , B32B2605/006 , B32B2605/18 , B64C1/1492 , Y10T428/31507 , Y10T428/31562 , Y10T428/31728
摘要： A multi-layered transparency (2.1, 2.2) for an aircraft cockpit, particularly a multi-layered window for a helicopter cockpit (1), comprising: one core layer (6) made of a polymer of either PC or mcPA and at least one foil extruded, adhesive interlayer film (3.1, 3.2, 3.3) unilaterally bonded to said at least one core layer (6). At least one outer top layer (5.1, 5.2) made of mcPA, preferably containing additives, is unilaterally attached to said at least one foil extruded adhesive interlayer film (3.1, 3.2, 3.3) distal to said at least one core layer (6) and a scratch resistant outer top coating (4.1, 4.2) is provided unilaterally to said at least one outer top layer (5.1, 5.2) distal to said at least one foil extruded adhesive interlayer film (3.1, 3.2, 3.3). The invention is as well related to a method of producing such a multi-layered transparency.
摘要翻译：一种用于飞机驾驶舱的多层透明体（2.1,2.2），特别是用于直升机驾驶舱（1）的多层窗口，包括：由PC或mcPA的聚合物制成的一个芯层（6）和至少一个单向粘合到所述至少一个芯层（6）上的箔挤压粘合层间膜（3.1,3.2,3.3）。由mcPA制成的至少一个外顶层（5.1,5.2）优选地含有添加剂，单侧连接到所述至少一个芯层（6）远侧的所述至少一个箔挤压粘合剂中间膜（3.1,3.2,3.3）并且向所述至少一个箔挤出的粘合层间膜（3.1,3.2,3.3）的远侧的所述至少一个外顶层（5.1,5.2）单向地提供抗划伤外顶涂层（4.1,4.2）。本发明也涉及制备这种多层透明体的方法。

8. 发明申请

US20140170372A1 GRID TYPE FIBER COMPOSITE STRUCTURE AND METHOD OF MANUFACTURING SUCH GRID TYPE STRUCTURE 有权
标题翻译：网格型纤维复合结构及制造这种网格结构的方法
公开(公告)号：US20140170372A1
公开(公告)日：2014-06-19
申请号：US14101458
申请日：2013-12-10
申请人： Eurocopter Deutschland GMBH
发明人： Axel Fink
IPC分类号： B32B3/12
CPC分类号： B32B3/12 , B29C70/68 , B29D24/005 , Y10T29/49826 , Y10T428/24149 , Y10T428/24157
摘要： The invention is related to a grid type fiber composite structure (1) comprising a grid of polygon cell modules (5) comprising at least three substantially u-shaped ribs made of fiber composite layer (8, 13) and a foam core (9) provided inside each cell module (5) for support of said u-shaped ribs. Said foam core (9) is along a base essentially in line with one of said flat cap sections (11, 12). At least one layer of strip (2, 3) is provided outside said flat cap sections (11, 12) and a skin sheet (4) is unilaterally attached to said cell modules (5) essentially in line with one of said flat cap sections (11, 12). The invention is as well related to a method of manufacturing such a grid type fiber composite structure (1).
摘要翻译：本发明涉及一种格栅型纤维复合结构（1），其包括多个光栅模块（5）的格栅，所述多边形单元模块（5）包括由纤维复合层（8,13）和泡沫芯（9）构成的至少三个基本上为U形的肋，设置在每个单元模块（5）内部，用于支撑所述u形肋。所述泡沫芯（9）沿着基本上与所述扁平盖部分（11,12）中的一个基本上一致的基座。至少一层条带（2,3）设置在所述平盖部分（11,12）之外，并且皮肤片（4）单向地附接到所述电池模块（5），基本上与所述扁平盖部分（11,12）。本发明也涉及制造这种格栅型纤维复合结构（1）的方法。

9. 发明申请

US20140117154A1 ROTORCRAFT FITTED WITH A MOUNTING STRUCTURE FOR JOINTLY MOUNTING A CONTROL PANEL AND AN AVIONICS RACK PREVIOUSLY FITTED WITH A UNITARY CABLING ASSEMBLY 有权
标题翻译：旋转轮安装有一个安装结构，用于连接安装控制面板和一个AVIONICS机架，先前安装了一个单元组装
公开(公告)号：US20140117154A1
公开(公告)日：2014-05-01
申请号：US14060833
申请日：2013-10-23
申请人： EUROCOPTER
发明人： Richard Olive
IPC分类号： B64D43/00
CPC分类号： B64D43/00 , B64C27/04 , Y10T29/49004
摘要： A rotorcraft fitted with means for mounting at least one front avionics rack (3, 3′) and man-machine interface instruments (2) on board a fuselage structure (4). A mounting structure (1) comprises a slotted body forming compartments for receiving interface instruments (2), the avionics rack (3, 3′), and a unitary cabling assembly (12) suitable for incorporating as a block with the mounting structure (1). The mounting structure (1) is installed as a block on the fuselage structure (4) after its functioning has been verified. The unitary cabling assembly (12) may also include separation connectors (14) segregating communications of the front avionics rack (3, 3′) respectively with remote computers (5) by means of a primary communications bus of the multiplexed, unidirectional, or bidirectional type, and with ancillary equipment (6) and/or with on-board instruments (7) by means of a secondary fieldbus.
摘要翻译：旋翼航空器配备有用于将至少一个前部航空电子设备机架（3,3'）和人机界面仪器（2）安装在机身结构（4）上的装置。安装结构（1）包括用于接收接口仪器（2），航空电子设备架（3,3'）的开槽主体形成室，以及适合于将其与安装结构（1）结合为一体的单一布线组件（12））。安装结构（1）在其功能被验证之后作为块安装在机身结构（4）上。单一布线组件（12）还可以包括分离连接器（14），分离连接器（14）通过多路复用，单向或双向的主通信总线将前面的航空电子设备机架（3,3'）的通信分别与远程计算机（5）隔离类型，以及辅助设备（6）和/或带有板载仪器（7）的二次现场总线。

10. 发明申请

US20140061367A1 COMPOUND HELICOPTER 有权
标题翻译：化合物直升机
公开(公告)号：US20140061367A1
公开(公告)日：2014-03-06
申请号：US13950570
申请日：2013-07-25
申请人： EUROCOPTER DEUTSCHLAND GMBH
发明人： Axel Fink , Ambrosius Weiss , Andrew Winkworth
IPC分类号： B64C27/26
CPC分类号： B64C27/26 , B64C39/068
摘要： The invention relates to a compound helicopter (1) comprising a fuselage (2), at least one engine (14) and a main rotor (11) driven by said at least one engine (14). At least one pair of fixed wings are mounted in an essentially horizontal plane on a left hand and a right hand side of the fuselage (2) and horizontally oriented propulsion devices (12, 13) are mounted to each of said fixed wings, said fixed wings encompassing each a drive shaft (16) from said at least one engine (14). Each fixed wing comprises a lower main wing (18) and an upper secondary wing (19) being connected to each other within an interconnection region (22). The propulsion devices (12, 13) are arranged at said interconnection region (22) and said upper secondary wing (19) houses the drive shaft (16) from said at least one engine (14).
摘要翻译：本发明涉及一种复合直升机（1），其包括由所述至少一个发动机（14）驱动的机身（2），至少一个发动机（14）和主转子（11）。至少一对固定翼安装在机身（2）的左手和右手侧的基本水平的平面中，并且水平定向的推进装置（12,13）安装到每个所述固定翼，所述固定每个包括来自所述至少一个发动机（14）的驱动轴（16）的机翼。每个固定翼包括在主互连区域（22）内彼此连接的下主翼（18）和上副翼（19）。推进装置（12,13）布置在所述互连区域（22）处，并且所述上副翼（19）从所述至少一个发动机（14）容纳驱动轴（16）。

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