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公开(公告)号：US20140292556A1
公开(公告)日：2014-10-02
申请号：US14100580
申请日：2013-12-09
IPC分类号： G01S13/93
CPC分类号： G01S13/9303 , G01S13/93 , G01S13/94 , G01S2013/9082
摘要： Obstacle and terrain warning radar system (1) for a rotorcraft (2), the system having at least two assemblies (10), each having at least one radar unit, said rotorcraft (2) including at least one main rotor (20) having at least two blades (22) and a rotor head (23). Each radar unit transmits a centrifugal radar beam (17) with angular beam width in azimuth α of at least 5° and beam width in elevation ε of at least 5°. Said assemblies (10) of at least one radar unit are positioned directly on said rotor head (23) between said blades (22), said radar system (1) electronically scanning the surroundings with angular coverage in elevation of at least +/−15° and mechanically scanning the surroundings with angular coverage in azimuth of 360°, and then informing the pilot of said rotorcraft (2).
摘要翻译： 用于旋翼航空器（2）的障碍物和地形警告雷达系统（1），所述系统具有至少两个组件（10），每个组件具有至少一个雷达单元，所述旋翼航空器（2）包括至少一个主转子（20） 至少两个叶片（22）和转子头（23）。 每个雷达单元发射具有至少5°的方位角α的角波束宽度和仰角波束宽度的离心雷达波束（17） 至少5°。 至少一个雷达单元的所述组件（10）直接位于所述叶片（22）之间的所述转子头（23）上，所述雷达系统（1）以高度角度覆盖至少+/- 15的电子扫描周围环境 °并以360°的方位角度覆盖机械扫描周围环境，然后通知所述旋翼航空器（2）的飞行员。
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公开(公告)号：US20140061366A1
公开(公告)日：2014-03-06
申请号：US13950517
申请日：2013-07-25
发明人： Axel Fink , Andrew Winkworth , Ambrosius Weiss
IPC分类号： B64C27/26
CPC分类号： B64C27/26 , B64C39/04 , B64C2027/8236
摘要： The present invention is related to a compound helicopter (1) with a main rotor (13) providing lift, a pair of additional propulsion devices (14, 15) providing thrust and anti-torque and a fixed wing structure (16, 17, 26) on each side providing additional lift during horizontal cruise flight. The propulsion devices (14, 15) are arranged at each side of a fuselage body (2) with two tail booms (7, 8), one arranged at each side of said fuselage body (2), each of both tail booms (7, 8) having one of both propulsion devices (14, 15) arranged at its boom rear end (9). Each of the two tail booms (7, 8) houses an engine (21) and a drive shaft (24) driving the corresponding propulsion device (14, 15).
摘要翻译： 本发明涉及具有主转子（13）提供升降机的复合直升机（1），提供推力和抗扭矩的一对附加推进装置（14,15）和固定翼结构（16,17,26 ），在水平巡航飞行期间提供额外的电梯。 推进装置（14,15）布置在机体（2）的两侧，具有两个尾臂（7,8），一个布置在所述机身主体（2）的每一侧，每个尾翼（7） ，8）具有布置在其悬臂后端（9）处的两个推进装置（14,15）中的一个。 两个尾杆（7,8）中的每一个都容纳有一个发动机（21）和一个驱动相应的推进装置（14,15）的驱动轴（24）。
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公开(公告)号：US20140014777A1
公开(公告)日：2014-01-16
申请号：US13937533
申请日：2013-07-09
IPC分类号： G01F23/284 , B64D37/00
CPC分类号： G01F23/2845 , B64D37/005 , G01F23/2921 , G01F23/2927
摘要： An optical level sensor (1) includes: mounting means (11) mounting the sensor (1) to a ceiling of the tank (9); a sensor tube (12, 12.1) provided with support and guidance elements (4) extending with at least three radially distributed positions inside the tank (9) and which collect support and guide optical fibers (3, 3.3, 3.4) to different heights of the tank (9), with each optical fiber (3) having a number of input sides (3.3) and a number of turns forming sensor heads between two input sides (3.3), for a different level (19); the corresponding support and guidance element (4) bending the fiber (3, 3.3, 3.4) in turns forming sensor heads of a small radius r around at least one corresponding guideway (4.3).
摘要翻译： 光学水平传感器（1）包括：将传感器（1）安装到罐（9）的天花板上的安装装置（11）; 设置有支撑和引导元件（4）的传感器管（12,12.1），所述支撑和引导元件（4）在罐（9）内部具有至少三个径向分布的位置延伸，并且收集支撑和引导光纤（3,3.3,3.4）到不同的高度 （9），其中每个光纤（3）具有多个输入侧（3.3），并且在两个输入侧（3.3）之间形成传感器头的数量圈，用于不同的等级（19）; 相应的支撑和引导元件（4）使纤维（3,3.3,3.4）弯曲，从而形成围绕至少一个对应导轨（4.3）的小半径r的传感器头部。
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公开(公告)号：US20130327881A1
公开(公告)日：2013-12-12
申请号：US13909209
申请日：2013-06-04
IPC分类号： B64C27/82
CPC分类号： B64C27/82 , B64C2027/8254
摘要： A helicopter with a longitudinal axis and with a tail portion (1) with a transverse duct (6) and a drive shaft (23) inside a drive shaft fairing (14) for an aerodynamic and acoustic optimized counter-torque device (2) supported within said transverse duct (6).
摘要翻译： 一种具有纵向轴线的直升机和具有横向导管（6）的尾部部分（1）和驱动轴整流装置（14）内部的用于空气动力和声学优化的反向扭矩装置（2）的驱动轴（23）的支撑 在所述横向管道（6）内。
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公开(公告)号：US20130315734A1
公开(公告)日：2013-11-28
申请号：US13785696
申请日：2013-03-05
IPC分类号： B64C27/33
摘要： An aerodynamic blade attachment (1) for a bearingless rotor, particularly a main rotor, of a helicopter, comprising: an airfoil blade (2) having a tip end and a root end and having a pitch axis from said tip end to said root end; a flexbeam (3); a control cuff (4, 22) enclosing and extending along said flexbeam (3) and a separable junction arrangement between said flexbeam (3), said control cuff (4) and said root end of said airfoil blade (2). Said junction arrangement is mechanical between said flexbeam (3), said control cuff (4) and said root end of said airfoil blade (2). Removable fasteners (5, 6) connect said root end of said airfoil blade (2) and said control cuff (4) with said flexbeam (3). Said junction arrangement comprises fairing means (10, 27, 28, 31, 32 and 39) encompass the removable fasteners (5, 6) and said flexbeam (3).
摘要翻译： 一种用于直升机的无轴承转子，特别是主转子的空气动力学叶片附件（1），包括：具有尖端和根端并具有从所述尖端到所述根端的俯仰轴的翼型叶片（2） ; 柔性梁（3）; 沿着所述挠性束（3）包围并延伸的控制箍（4,22）和所述柔性梁（3），所述控制箍（4）和所述翼型叶片（2）的所述根端之间的可分离的连接装置。 所述接合装置在所述挠性梁（3），所述控制箍（4）和所述翼型叶片（2）的所述根端之间是机械的。 可拆卸紧固件（5,6）将所述翼型叶片（2）的所述根端和所述控制箍（4）与所述挠性梁（3）连接。 所述接合装置包括包围可拆卸紧固件（5,6）和所述柔性梁（3）的整流装置（10,27,28,31,32和39）。
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6.发明申请DEVICE FOR PROTECTING AN INDIVIDUAL SITTING ON A SEAT, A SEAT, AND A VEHICLE 有权用于保护座椅，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）。
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7.发明申请Fasteners for attaching a windshield to the fuselage side frame of an aircraft viewing port 有权用于将挡风玻璃附接到飞机观察端口的机身侧框架上的紧固件公开(公告)号：US20030010867A1
公开(公告)日：2003-01-16
申请号：US10180484
申请日：2002-06-27
发明人： Klaus Wojatschek , Mark Drewe
IPC分类号： B64D045/00
CPC分类号： B64C1/1492
摘要： A connecting device for joining a windshield with a fuselage side frame of a viewing port of an aircraft, especially a cockpit frame of a helicopter. The connecting device includes a fastening element which is fixed into position on a section of a peripheral region of the windshield through a bore hole and into a congruent bore hole of the fuselage side frame and in a fastening part with a spring device. A peripheral slit filled with a sealant is arranged in a peripheral region between the fuselage side frame and windshield. The fastening part includes a retaining nut and a spring device which can be moved and guided within a seating element and connected with the fuselage side frame. The spring device is arranged between the retaining nut and the frame.
摘要翻译： 一种用于将挡风玻璃与飞机的观察端口的机身侧框架连接的连接装置，特别是直升机的驾驶舱框架。 连接装置包括紧固元件，该紧固元件通过孔眼固定在挡风玻璃的周边区域的一部分上并进入机身侧框架的一体钻孔中以及具有弹簧装置的紧固部件中。 填充有密封剂的周边狭缝布置在机身侧框架和挡风玻璃之间的周边区域中。 紧固部件包括固定螺母和弹簧装置，该弹簧装置可在座位元件内移动和引导并与机身侧框架连接。 弹簧装置设置在固定螺母和框架之间。
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公开(公告)号：US09213096B2
公开(公告)日：2015-12-15
申请号：US13721145
申请日：2012-12-20
CPC分类号： G01S13/9303 , G01S13/87
摘要： A proximity warning system for a helicopter (22) comprising at least two radar units (1-3), preferably three radar units (1-3) arranged to transmit microwaves and receive reflections of said microwaves from obstacles (10). The at least two radar units (1-3) are fixed next to a main rotor head(s) (20) of the helicopter (22) for horizontally scanning an entire environment of 360° around the helicopter (22), all of said at least two radar units (1-3) operating essentially at the same frequency.
摘要翻译： 一种用于直升机（22）的接近警报系统，包括至少两个雷达单元（1-3），优选地布置成传送微波并且从障碍物（10）接收所述微波的反射的三个雷达单元（1-3）。 至少两个雷达单元（1-3）被固定在直升机（22）的主转子头（20）旁边，用于水平地扫描围绕直升机（22）的360°的整个环境，所有这些 至少两个基本上以相同频率工作的雷达单元（1-3）。
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9.发明申请MULTI-LAYERED TRANSPARENCY AND METHOD OF PRODUCING SUCH A MULTI-LAYERED TRANSPARENCY 审中-公开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
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。
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10.发明申请GRID TYPE FIBER COMPOSITE STRUCTURE AND METHOD OF MANUFACTURING SUCH GRID TYPE STRUCTURE 有权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
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。
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