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71. 发明授权

US4669819A Connector for coupling a medical laser tool to a laser 失效
标题翻译：用于将医疗激光工具耦合到激光器的连接器
公开(公告)号：US4669819A
公开(公告)日：1987-06-02
申请号：US733983
申请日：1985-05-13
申请人： Thomas Hengst , Andreas Hahn
发明人： Thomas Hengst , Andreas Hahn
IPC分类号： A61B18/20 , A61B1/00 , A61B17/00 , A61B18/00 , A61B18/22 , G02B6/38 , G02B6/42 , H01R4/60 , H01R13/717 , G02B6/24
CPC分类号： G02B6/4296 , A61B18/22 , G02B6/3813 , G02B6/3817 , H01R13/717 , H01R4/60 , A61B2017/00482 , A61B2218/005 , G02B6/3891 , G02B6/3895
摘要： A connector for coupling a medical laser tool to a laser has a housing with coupling fitting at one end which is plugged into a laser receptacle and with a light conductor cable connection at the other end. The light conductor cable in turn is connected to the laser tool. The coupling fitting includes, in addition to the optical coupling element, heavy and light duty electrical contact members for an electrical power and data transmission and a gas conduit coupling for a gas transmission through the connector.
摘要翻译：用于将医用激光工具耦合到激光器的连接器具有壳体，其一端具有联接配件，该壳体插入激光器插座中，并且在另一端具有光导体电缆连接。光导体电缆依次连接到激光工具。耦合配件除了光学耦合元件之外还包括用于电力和数据传输的重和轻型电接触构件，以及用于通过连接器的气体传输的气体导管联接。

72. 发明授权

US4660787A Food supply system for an aircraft 失效
标题翻译：飞机食品供应系统
公开(公告)号：US4660787A
公开(公告)日：1987-04-28
申请号：US885380
申请日：1986-07-14
申请人： Wilfried Sprenger , Safa Kirma
发明人： Wilfried Sprenger , Safa Kirma
IPC分类号： B64C1/22 , B64D11/00 , B64D11/04
CPC分类号： B64D11/04 , B64D11/0007
摘要： A food supply system is adapted for installation in an aircraft having an upper and a lower deck. A pantry is located on the upper deck. A food supply carts carrying platform is arranged on the lower deck for cooperation with the pantry on the upper deck. A lifting mechanism is arranged for cooperation with the platform for lifting or lowering selectively any one of a plurality of food supply carts whereby the space requirements on each deck are optimally reduced.
摘要翻译：食品供应系统适于安装在具有上甲板和下甲板的飞机中。厨房位于上甲板上。食物供应车承载平台布置在下甲板上，与上甲板上的厨房进行配合。提升机构被设置成与平台协作，用于选择性地提升或降低多个食物供应车中的任何一个，由此每个甲板上的空间要求被最佳地降低。

73. 发明授权

US4642652A Unfoldable antenna reflector 失效
标题翻译：不可折叠的天线反射器
公开(公告)号：US4642652A
公开(公告)日：1987-02-10
申请号：US664043
申请日：1984-10-23
申请人： Henning Herbig , Horst Heinze , Franz Drachenberg , Knud Pontoppidan
发明人： Henning Herbig , Horst Heinze , Franz Drachenberg , Knud Pontoppidan
IPC分类号： H01Q15/20 , H01Q15/14 , H01Q15/16
CPC分类号： H01Q15/161
摘要： An umbrella type unfoldable antenna reflector net is supported by carrier bs extending radially from a carrier body and by auxiliary ribs extending between adjacent carrier ribs. Bracing wires are connected between the carrier ribs and the auxiliary ribs. The tension of the bracing wires, which in the unfolded state of the reflector net extend substantially in the direction of chords, is adjustable by respective adjustment members so that the bracing tension force has a force component which extends substantially perpendicularly to a plane defined by the unfolded reflector net. The adjustment members permit adjusting the reflector net into a parabolic shape.
摘要翻译：伞型可折叠天线反射器网由从载体主体径向延伸的载体肋和在相邻载体肋之间延伸的辅助肋支撑。支撑线连接在承载肋和辅助肋之间。在反射器网的展开状态下，支撑线的张力基本上在弦的方向上延伸，可通过相应的调节构件来调节，使得支撑张力具有大致垂直于由展开反射网。调节构件允许将反射器网调整成抛物线形状。

74. 发明授权

US4615497A Method and flutter brake for an aircraft 失效
标题翻译：一种飞机的方法和颤振制动
公开(公告)号：US4615497A
公开(公告)日：1986-10-07
申请号：US821217
申请日：1986-01-21
申请人： Hartwig Seeler , Helmut Zimmermann
发明人： Hartwig Seeler , Helmut Zimmermann
IPC分类号： B64C13/16
CPC分类号： B64C13/16
摘要： The invention relates to a method and an arrangement for the wings of a h speed aircraft, for increasing the flutter velocity. Aerodynamic auxiliary flaps or vortex generators are placed into an effective position in response to filtered sensor signals for causing a reduction in the local lift rise or for shifting the local neutral point toward the wing trailing edge to thereby provide an effective "flutter brake". The auxiliary flaps or vortex generators are activated only once when needed and stay in an activated effective position for a length of time sufficient for increasing the flutter velocity or speed and the activation takes place rapidly in about 200 to 400 milliseconds from the time the sensors pick up or provide a signal for such activation.
摘要翻译：本发明涉及一种用于增加颤振速度的用于高速飞行器的机翼的方法和装置。响应于过滤的传感器信号，将空气动力学辅助翼片或涡流发生器置于有效位置，用于引起局部升高降低或使局部中性点朝向机翼后缘移动，从而提供有效的“颤振制动”。辅助襟翼或涡流发生器在需要时仅被激活一次，并保持在激活的有效位置一段足以增加颤振速度或速度的时间，并且激活在传感器拾取时间的大约200至400毫秒内快速发生或提供这种激活的信号。

75. 发明授权

US4603084A Article of manufacture with a connecting element and method for securing the element to the article 失效
标题翻译：具有连接元件的制造品和用于将元件固定到物品的方法
公开(公告)号：US4603084A
公开(公告)日：1986-07-29
申请号：US632422
申请日：1984-07-19
申请人： Franz Drachenberg , Walter Oefner
发明人： Franz Drachenberg , Walter Oefner
IPC分类号： B29C53/70 , B29C53/80 , B29C70/20 , B29C70/86 , F16C7/00 , B65H81/00 , G05G1/00
CPC分类号： F16C7/026 , B29C37/0085 , B29C53/70 , B29C53/8058 , B29C70/205 , B29C70/86 , B29L2031/06 , Y10T428/2936 , Y10T428/2938 , Y10T74/2142
摘要： A connecting element, such as a bearing shell, is secured to and end of anrticle of manufacture having a large length relative to its diameter, by a combination of fiber strands or belts forming at least one loop, the ends of which form slings or bights which are anchored to the article by the turns of an anchoring winding extending around the article and through the slings or bights. The loop with its slings or bights is made simultaneously with the formation of the anchoring winding. This type of operation is possible because the turns of the anchoring winding hold down the fiber strands or belts as they are doubled-up to form the loop, preferably endless loops.
摘要翻译：诸如轴承壳的连接元件通过组合至少一个环的纤维束或带的组合固定到具有相对于其直径的大长度的制品的端部，其端部形成吊索或通过围绕物品延伸并且穿过吊索或跷跷板的锚定绕圈的转弯将锚固件固定在物品上。带有吊索或弯针的环与锚定绕组的形成同时进行。这种类型的操作是可能的，因为当它们被加倍以形成环时，锚定绕组的转动将纤维束或带保持下来，优选地是无端环。

76. 发明授权

US4592701A Rotor blade, especially for a rotary wing aircraft 失效
标题翻译：转子叶片，特别适用于旋翼飞机
公开(公告)号：US4592701A
公开(公告)日：1986-06-03
申请号：US686472
申请日：1984-12-26
申请人： Michael Hahn , Otmar Friedberger , Gerhard Singer
发明人： Michael Hahn , Otmar Friedberger , Gerhard Singer
IPC分类号： B64C27/28 , B64C27/33
CPC分类号： B64C27/28 , B64C27/33
摘要： A rotor blade, for example for a rotary wing aircraft, has a wing section d a root section interconnected by a neck section surrounded by a blade angle adjustment sleeve which is stiff against torque moments for transmitting blade angle adjustment movements through the sleeve to the wing section. The trailing edge of the sleeve is provided with a gap which extends, at least partially, alongside the rear edge of the neck section for visually inspecting the neck section inside the sleeve even when the root section is connected to a rotor hub. A reflecting mirror may be used for inspecting all sides of the neck section through the gap.
摘要翻译：例如用于旋转飞行器的转子叶片具有翼部分和根部，其通过由叶片角度调节套筒包围的颈部部分相互连接，该叶片角度调节套筒刚性地抵抗用于将叶片角度调节运动通过套筒传递到翼部的扭矩部分。套筒的后缘设置有间隙，其至少部分地延伸到颈部部分的后边缘，用于目视检查套管内的颈部部分，即使当根部连接到转子毂时也是如此。反射镜可用于通过间隙检查颈部的所有侧面。

77. 发明授权

US4589594A Thrust nozzle system 失效
标题翻译：推力喷嘴系统
公开(公告)号：US4589594A
公开(公告)日：1986-05-20
申请号：US605286
申请日：1984-04-30
申请人： Walter Kranz
发明人： Walter Kranz
IPC分类号： F02K1/78 , F02K9/80 , F42B19/01 , F42B15/033
CPC分类号： F42B10/663
摘要： The invention relates to a thrust nozzle system, especially for steering arojectile, having a nozzle arrangement (3) which is fed by a propellant source, for example a gas source. The nozzle system is arranged in a housing having at least one exhaust port (11) provided in the housing, and has a control (14) for steering a thrust jet (18) of the nozzle arrangement through the exhaust port. The invention provides a thrust nozzle system of simple construction which is especially suitable for a high miniaturization, and which permits a flexible thrust impulse forming. For this purpose the thrust nozzle system (2) has a rotating nozzle or a swinging nozzle body (3) which is rotatable relative to the housing about an axis, driven by the propellant, for example by the gas stream (P) from the gas source. The drive of the rotating nozzle body is preferably achieved by an acentric thrust nozzle (10) itself. Due to the low mass and hence low inertia of the nozzle body (3), it may be caused to rotate fast. A braking arrangement (14) is provided for the rotating nozzle body for steering the thrust jet (18) in a defined direction. Such a thrust nozzle system may serve for many uses, for example in conjunction with a secondary injection system or a hot gas motor.
摘要翻译：本发明涉及一种特别用于转向抛射体的推力喷嘴系统，其具有由推进剂源例如气体源供给的喷嘴装置（3）。喷嘴系统布置在具有设置在壳体中的至少一个排气口（11）的壳体中，并且具有用于通过排气口转向喷嘴装置的推力射流（18）的控制器（14）。本发明提供了一种结构简单的推力喷嘴系统，特别适用于高度小型化，并且允许柔性的推力冲击形成。为此目的，推力喷嘴系统（2）具有旋转喷嘴或摆动喷嘴体（3），该主体可相对于外壳绕轴承转动，该轴线由推进剂驱动，例如来自气体的气流（P）资源。旋转喷嘴体的驱动优选通过中心推力喷嘴（10）本身实现。由于喷嘴体（3）的质量低，因此惯性较小，可能会使其快速旋转。为旋转喷嘴体提供制动装置（14），用于沿着确定的方向转向推力射流（18）。这种推力喷嘴系统可以用于许多用途，例如与二次喷射系统或热气体马达相结合。

78. 发明授权

US4583891A Structural component having a twisted profile and method and apparatus for producing such structural component 失效
标题翻译：具有扭曲轮廓的结构部件和用于制造这种结构部件的方法和装置
公开(公告)号：US4583891A
公开(公告)日：1986-04-22
申请号：US680583
申请日：1984-12-10
申请人： Peter Eschenfelder , Jorg Quentin
发明人： Peter Eschenfelder , Jorg Quentin
IPC分类号： B23C3/18 , B23Q1/01 , B23Q1/48 , B23Q1/62 , B64C27/46 , B64C27/473 , F03D1/06
CPC分类号： F03D1/0608 , B23Q1/012 , B23Q1/4809 , B23Q1/623 , F05B2250/131 , Y02E10/721 , Y02P70/167 , Y10T409/303136 , Y10T409/307728 , Y10T409/308288
摘要： A structural component having a twisted profile or cross-section, such as aarge scale wing for a windmill or for a helicopter, has an upper portion and a lower portion intimately bonded to each other along an interface formed by two separation surfaces. A longitudinal axis extends in said interface. The interface is defined by simultaneously twisting or rotating and longitudinally moving a polygonal line (PZ) relative to the longitudinal axis while a central portion of the polygonal line extends perpendicularly to the central axis. The machine tool for machining the separation surfaces has a tool carrier (14), and a carrier support (20) for holding the tool carrier (14) in such a manner that the tool carrier is tiltable about the longitudinal axis of the interface. Simultaneously the carrier support is movable in the direction of the longitudinal axis (A).
摘要翻译：具有扭曲轮廓或横截面的结构部件，例如用于风车或直升机的大型机翼，具有沿着由两个分离表面形成的界面彼此紧密地接合的上部和下部。纵轴在所述界面中延伸。界面通过同时扭转或旋转并相对于纵向轴线纵向移动多边形线（PZ）而定义，而多边形线的中心部分垂直于中心轴线延伸。用于加工分离表面的机床具有工具架（14）和用于以使得工具架能够围绕接口的纵向轴线倾斜的方式保持工具架（14）的托架支撑件（20）。同时，载体支撑件可以在纵向轴线（A）的方向上移动。

79. 发明授权

US4549726A Mounting member for mounting an engine or transmission of a motor vehicle 失效
标题翻译：用于安装机动车辆的发动机或变速器的安装构件
公开(公告)号：US4549726A
公开(公告)日：1985-10-29
申请号：US540889
申请日：1983-10-11
申请人： Ralf-Thilo Schulz , Helmut Rapp
发明人： Ralf-Thilo Schulz , Helmut Rapp
IPC分类号： B60K5/12 , B29C70/20 , B29C70/22 , F16F1/366 , F16F15/02 , B32B17/04 , B32B27/04
CPC分类号： F16F1/366 , B29C70/202 , B29C70/228 , B29K2105/108 , B29L2023/00 , B29L2031/721 , Y10S428/902 , Y10T428/24058 , Y10T428/24116 , Y10T428/24124
摘要： A mounting member for mounting an engine or transmission on a supporting ucture of a motor vehicle, is constructed as a one piece integral component made of fiber compound material in which the fiber layers have defined, preselected orientations. The damping characteristics can be optimally tuned for specific types of use or vehicles by controlling the materials and orientation of the fibers in each layer, and by controlling the number of layers. Additional damping may be achieved by inserting an elastomeric intermediate layer between the individual fiber layers. The shape of the mounting member also varies according to the load or stress to which the member will be exposed in use. The available space and the type of motor vehicle in which the member will be used are also taken into account in determining the shape, cross-sectional configuration and other structural details of the mounting member.
摘要翻译：用于将发动机或变速器安装在机动车辆的支撑结构上的安装构件被构造为由光纤复合材料制成的一体式整体部件，其中纤维层具有预定的取向。通过控制各层中的纤维的材料和取向以及控制层的数量，可以对特定类型的使用或车辆优化调节阻尼特性。可以通过在各个纤维层之间插入弹性体中间层来实现附加的阻尼。安装构件的形状也根据构件将在使用中暴露的负载或应力而变化。在确定安装构件的形状，横截面构造和其他结构细节时，也考虑到使用构件的机动车辆的可用空间和类型。

80. 发明授权

US4547127A Wing mounting for a rotary wing aircraft 失效
标题翻译：机翼安装用于旋翼飞机
公开(公告)号：US4547127A
公开(公告)日：1985-10-15
申请号：US544563
申请日：1983-10-24
申请人： Hubert Frommlet , Michael Hahn
发明人： Hubert Frommlet , Michael Hahn
IPC分类号： B64C27/32 , B64C27/33 , B64C27/48 , B64C27/37
CPC分类号： B64C27/33 , B64C27/32 , B64C27/48
摘要： A flexible blade neck of a helicopter rotor blade is bridged by a torsion gid sleeve for the blade angle adjustments. The radially outer end of the blade neck and sleeve are rigidly connected to the wing section of the blade. The radially inner end of the blade neck forms a blade root which is secure to the rotor head or hub. Additionally, the radially inner ends of the blade root and of the sleeve are interconnected by a ball and socket arrangement permitting a universal movement between the sleeve and the blade neck, thereby decoupling sleeve movements from the blade neck and vice versa.
摘要翻译：直升机转子叶片的柔性叶片颈部由扭转刚性套筒桥接，用于叶片角度调整。叶片颈部和套筒的径向外端刚性地连接到叶片的翼部。叶片颈部的径向内端形成叶片根部，叶片根部固定到转子头部或轮毂上。此外，叶片根部和套筒的径向内端部通过允许套筒和叶片颈部之间的通用运动的球窝装置相互连接，从而使套筒运动与叶片颈部脱离，反之亦然。

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