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公开(公告)号：US20140061367A1
公开(公告)日：2014-03-06
申请号：US13950570
申请日：2013-07-25
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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公开(公告)号：US20130332062A1
公开(公告)日：2013-12-12
申请号：US13908270
申请日：2013-06-03
IPC分类号： G08G5/04
CPC分类号： G08G5/04 , G01C23/00 , G01S7/062 , G01S13/9303 , G01S17/933
摘要： An obstacle information system and method for a helicopter with a warning information processor (3) and a display unit (1) for any obstacle (2) within a predetermined minimum distance d4. Said warning information processor (3) is fed with information related to detected distance d5 and direction of said at least one obstacle (2) detected by an obstacle sensor system (4) to compute and prepare the information for presentation on the display unit (1). Said display unit (1) comprises at least an indication area with a central circular surface (6) and a concentric ring-shaped area (7) around the circular surface (6). Said circular surface (6) is used exclusively for alerts. The ring-shaped area (7) is used for both. Warnings and alerts and the repartition in the indication area of circular surface (6) and ring-shaped area (7) are dependent on the detected distance d5 of said at least one obstacle (2).
摘要翻译： 一种用于具有警告信息处理器（3）的直升机和在预定最小距离d4内的任何障碍物（2）的显示单元（1）的障碍物信息系统和方法。 所述警告信息处理器（3）被馈送与由障碍物传感器系统（4）检测到的检测距离d5和所述至少一个障碍物（2）的方向有关的信息，以计算和准备用于呈现在显示单元（1）上的信息 ）。 所述显示单元（1）至少包括具有中心圆形表面（6）和围绕圆形表面（6）的同心环形区域（7）的指示区域。 所述圆形表面（6）仅用于警报。 环形区域（7）用于两者。 警告和警报以及圆形表面（6）和环形区域（7）的指示区域中的重新分配取决于所述至少一个障碍物（2）的检测距离d5。
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公开(公告)号：US20130264423A1
公开(公告)日：2013-10-10
申请号：US13679079
申请日：2012-11-16
IPC分类号： B64C1/18
CPC分类号： B64C1/18 , B32B3/12 , B32B3/30 , B32B15/08 , B32B27/12 , B32B2250/40 , B32B2274/00 , B32B2307/7242 , B32B2307/744 , B32B2605/003 , B32B2605/18
摘要： An air vehicle with a slip protecting and gas sealing composite floor (1, 10) inside a fuselage, particularly a helicopter with a slip protecting and gas sealing composite floor (1, 10) inside a fuselage. Said slip protecting and gas sealing composite floor (1, 10) is built up of a profiled elastomer layer (2) provided at its bottom side with a cross-linking agent, n-layers (3) of a further component or a variety of different components and partially thermosetting resin covered by a profiled elastomer layer (2), a honey comb layer (4) and lower n-layers (5) of said further component or variety of different components and partially thermosetting resin, said honey comb layer (4) being sandwiched between said n-layers (3) and said lower n-layers (5).
摘要翻译： 机身内有防滑保护气密封复合地板（1,10）的机动车，尤其是在机身内部具有防滑和气密复合地板（1,10）的直升机。 所述滑动保护和气体密封复合地板（1,10）由其底部设置有交联剂的成型弹性体层（2）构成，其另外的组分或各种各样的 不同的组分和部分热固性树脂被异型弹性体层（2），所述另外的组分或各种不同组分的蜂窝梳（4）和下n层（5）覆盖，所述蜂巢层（ 4）夹在所述n层（3）和所述下n层（5）之间。
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公开(公告)号：US20030160131A1
公开(公告)日：2003-08-28
申请号：US10370437
申请日：2003-02-19
IPC分类号： B64C001/14
CPC分类号： B64C1/1407 , E05D3/12 , E05F15/614 , E05Y2900/502 , E05Y2900/531
摘要： An structurally simplified actuation mechanism for swinging an aircraft door from a frame on an aircraft fuselage. The actuation mechanism includes a cantilever rotatably mounted to the frame and including a receiving region, a universal joint supported in the receiving region, and an actuation device disposed on the cantilever. The universal joint defines a vertical axis of rotation and is configured to receive a door fitting. The actuation device includes an output drive connected to the universal joint at the vertical axis of rotation.
摘要翻译： 一种结构简化的致动机构，用于使飞机门从飞机机身上的框架摆动。 所述致动机构包括可旋转地安装到所述框架并包括接收区域的悬臂，支撑在所述接收区域中的万向接头以及设置在所述悬臂上的致动装置。 万向接头限定了垂直的旋转轴线，并被配置为接收门配件。 致动装置包括在垂直旋转轴线处连接到万向接头的输出驱动器。
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15.发明申请Method and device for reproducing a recorded flight mission of an aircraft from an observer position by means of a system for flight simulation 审中-公开用于通过用于飞行模拟的系统从观察者位置再现飞行器的记录飞行任务的方法和装置公开(公告)号：US20020187460A1
公开(公告)日：2002-12-12
申请号：US10165309
申请日：2002-06-10
发明人： Jan Luttmann , Erwin Burlafinger
IPC分类号： G09B009/08 , G09B019/16
摘要： The invention relates to a method for reproducing a recorded flight mission of an aircraft, in particular a helicopter, from an observer position by means of a flight simulation system. Flight data, which are recorded by a storage medium of a simulation computer and whose purpose is reproduction, can be retrieved by the flight simulation system. Furthermore, there is a device for carrying out the method. The object of the invention is to further improve, during reproduction of a recorded flight mission, the intuitive detectability of a deviation from a desired target flight path from an observer position by means of a flight simulation system for an aircraft. The problem is solved in that the simulation computer is equipped with a program for calculating at least one virtual observer position, where the program, with its effect on a program of a display computer, can control the display computer's help program for displaying a flight tunnel and the display computer's help program for displaying a three-dimensional image of the aircraft so that by means of the flight simulation system, a virtual observer position with a view of the aircraft during the flight mission can be displayed.
摘要翻译： 本发明涉及一种用于通过飞行模拟系统从观察者位置再现飞行器，特别是直升机的记录飞行任务的方法。 飞行模拟系统可以检索由仿真计算机的存储介质记录并且其目的是再现的飞行数据。 此外，存在用于执行该方法的装置。 本发明的目的是在记录的飞行任务的再现期间，通过用于飞行器的飞行模拟系统，进一步改善从目标飞行路径偏离观察者位置的直观可检测性。 解决的问题在于，仿真计算机配备有用于计算至少一个虚拟观察者位置的程序，其中程序对其显示计算机的程序的影响可以控制显示计算机的帮助程序来显示飞行隧道 以及显示计算机的用于显示飞行器的三维图像的帮助程序，以便借助于飞行模拟系统，可以显示在飞行任务期间具有飞机视野的虚拟观察者位置。
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16.发明申请Valve arrangement in a feed line to deliver fuel from a tank to an internal combustion engine 有权进料管线中的阀装置，用于将燃料从罐输送到内燃机公开(公告)号：US20010025629A1
公开(公告)日：2001-10-04
申请号：US09819691
申请日：2001-03-29
IPC分类号： F02M001/00
CPC分类号： F02M37/0023 , B60K15/073 , B60K2015/03118 , B60K2015/03144 , F02M37/007 , F02M37/0088 , F16K17/196 , Y10T137/8085
摘要： A valve arrangement is provided for a feed line to supply fuel from a tank to a combustion engine consisting of a valve housing with an inlet channel and outlet channel, and a valve with a movable valve head to seal the outlet channel from the inlet channel, whereby a feed pump is assigned to the feed line, and the valve head is in closed position when there is no feed pressure from the feed pump. The danger of feed line leakage for combustion engines that burn liquid fuel is eliminated using a coaxial second valve using no additional space to solve the problem. The other essentially coaxial valve within the main valve is in open position opposite the feed direction when the pressure at the outlet channel is greater than the feed pressure. The valve arrangement functions as a check valve when the combustion engine is running, and as an overpressure valve when it is off. The solution does not requiring additional installation space, and can be economically integrated into existing fuel systems without any substantial installation effort.
摘要翻译： 提供了一种用于进料管线的阀装置，用于将燃料从罐供给到由具有入口通道和出口通道的阀壳体组成的内燃机，以及具有可移动阀头的阀，以将出口通道与入口通道密封， 由此将进料泵分配给进料管线，并且当没有来自进料泵的进料压力时，阀头处于关闭位置。 燃烧液体燃料的燃烧发动机的进料管线泄漏的危险被消除，使用不具有额外空间的同轴第二阀来解决问题。 当出口通道处的压力大于进给压力时，主阀内的另一个基本上同轴的阀处于与进给方向相反的打开位置。 当内燃机运行时，阀装置用作止回阀，当关闭时作为过压阀。 该解决方案不需要额外的安装空间，并且可以经济地集成到现有燃料系统中，而无需任何实质的安装工作。
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公开(公告)号：US09194285B2
公开(公告)日：2015-11-24
申请号：US13680509
申请日：2012-11-19
CPC分类号： F02B63/04 , B64C27/14 , B64C2027/8209 , B64D27/24 , B64D2027/026 , Y02T50/64 , Y10S903/903
摘要： A hybrid drive system for aircraft, in particular helicopters, with at least one energy generating module having an internal combustion engine and a generator that can be powered by the latter to generate electrical energy, and at least one electric motor for powering a drive means of the aircraft.
摘要翻译： 一种用于飞行器，特别是直升机的混合驱动系统，其中至少一个能量产生模块具有内燃机和发电机，所述内燃机和发电机可由后者供电以产生电能;以及至少一个电动马达， 飞机。
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18.发明授权Landing gear vibration absorber and method of operating said landing gear vibration absorber 有权起落架减振器和操作所述起落架减振器的方法公开(公告)号：US08967536B2
公开(公告)日：2015-03-03
申请号：US13716460
申请日：2012-12-17
发明人： Raphael Rammer , Peter Znika
CPC分类号： B64C27/001 , B64C2025/325 , B64C2027/005 , F16F7/116 , Y10T29/49764
摘要： A landing gear vibration absorber (1) of a helicopter (2) with a landing gear (3) comprising a pair of skids (4, 5) and at least one cross tube (6, 7) for mounting the skids (4, 5) to a helicopter's fuselage (8). At least one spring-mass system (10, 20, 24) is mounted to the landing gear (3). Said at least one spring-mass system (10, 20, 24) is tuned to the helicopter's main excitation frequency and said at least one spring-mass system (10, 20, 24) being located at or near at least one antinode of the landing gear (3). The invention is related as well to a method of operating a landing gear vibration absorber (1) of a helicopter (2).
摘要翻译： 具有起落架（3）的直升机（2）的起落架减震器（1）包括一对滑板（4,5）和至少一个用于安装滑行件（4,5）的横管（6,7） ）到直升机的机身（8）。 至少一个弹簧质量系统（10,20,24）安装到起落架（3）。 所述至少一个弹簧 - 质量系统（10,20,24）被调谐到所述直升机的主激励频率，并且所述至少一个弹簧质量系统（10,20,24）位于或接近所述直升机的至少一个波腹 起落架（3）。 本发明还涉及一种操作直升机（2）的起落架减震器（1）的方法。
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19.发明申请AIR INLET COMBINING A FILTER AND A BYPASS DEVICE FOR USE WITH A TURBINE ENGINE 有权过滤器和旁路装置的空气入口组合使用涡轮发动机公开(公告)号：US20140158833A1
公开(公告)日：2014-06-12
申请号：US14101405
申请日：2013-12-10
发明人： Ralf Braeutigam
IPC分类号： B64D33/02
CPC分类号： B64D33/02 , B64C27/04 , B64D2033/0246 , B64D2033/0293
摘要： An air inlet (10) for an engine (20) of an aircraft (50), the air inlet (10) having a duct (2) feeding outside air to said engine (20) together with a filter system combining at least one filter (3) and at least one bypass device (4). Said filter (3) and said bypass device (4) are fastened on a common support (1) situated at one end of said duct (2) and on a flank of a fuselage (51) of said aircraft (50). Said bypass device (4) comprises a cover (5) and an actuator (6) controlling opening of said cover (5). Thus, when said filter (3) no longer allows outside air to pass therethrough, said cover (5) is opened, and outside air passes via the bypass device (4) in order to feed said engine (20) with outside air.
摘要翻译： 一种用于飞行器（50）的发动机（20）的空气入口（10），所述进气口（10）具有向与所述发动机（20）供给外部空气的管道（2）以及与至少一个过滤器 （3）和至少一个旁路装置（4）。 所述过滤器（3）和所述旁路装置（4）被紧固在位于所述管道（2）的一端和所述飞机（50）的机身（51）的侧翼上的公共支撑件（1）上。 所述旁路装置（4）包括盖（5）和控制所述盖（5）的开口的致动器（6）。 因此，当所述过滤器（3）不再允许外部空气通过时，所述盖（5）打开，并且外部空气经由旁路装置（4）通过，以便向外部空气供给所述发动机（20）。
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公开(公告)号：US20140130985A1
公开(公告)日：2014-05-15
申请号：US14067021
申请日：2013-10-30
发明人： Christian Weimer , Florian Dorn
IPC分类号： C08J5/04
CPC分类号： C08J5/04 , B29C35/16 , B29C70/388 , B29C2035/1616 , B29C2035/1625 , B29C2035/1633 , B29C2035/1658 , B32B37/0053 , B32B37/06 , C08J5/24
摘要： A heat control system for an adaptive consolidation roller (8) for the production of consolidated layers (2) made of fiber reinforced polymers comprising the adaptive consolidation roller (8) for applying, on an application surface (3), a band (4) formed of at least one resin pre-impregnated flat tape (5), and a heating system (6, 7) adapted to emit heat radiation directed towards the band (4). Said adaptive consolidation roller (8) is rotatable on a spindle (9) and comprises a surface made of an elastic deformable, flexible material. At least one additional roller (10) with thermal control means is provided and said at least one additional roller (10) is pressed from radial outside against the surface of the adaptive consolidation roller (8).
摘要翻译： 一种用于生产由纤维增强聚合物制成的固化层（2）的自适应固结辊（8）的热控制系统，包括用于在施用表面（3）上施加带（4）的自适应固结辊（8） 由至少一个树脂预浸渍扁平带（5）形成，以及适于发射朝向带（4）的热辐射的加热系统（6,7）。 所述自适应固定辊（8）可在心轴（9）上旋转并且包括由弹性可变形的柔性材料制成的表面。 提供具有热控制装置的至少一个附加辊（10），并且所述至少一个附加辊（10）从径向外侧压靠自适应固结辊（8）的表面。
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