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1. 发明申请

WO1983003281A1 INTERNALLY VENTILATED NOISE SUPPRESSOR WITH LARGE PLUG NOZZLE 审中-公开
标题翻译：内部通风噪音抑制器，带大口径喷嘴
公开(公告)号：WO1983003281A1
公开(公告)日：1983-09-29
申请号：PCT/US1982000327
申请日：1982-03-17
申请人： THE BOEING COMPANY , KLEES, Garry, William , WRIGHT, Charles, Perry
发明人： THE BOEING COMPANY
IPC分类号： F01N01/14
CPC分类号： F02K1/386 , B64D2033/024 , F02K1/1207 , F02K1/625
摘要： A jet engine noise suppressor particularly adapted for supersonic aircraft. The nozzle (10) has an internal wall surface (70) around a generally centrally positioned body (50) and an annular area (62) extending between the wall and the body. In this area there are separate gas and air flow ducts (64, 66) having entrance ends (82, 80) and exit ends (76, 78), the entrance ends of the gas ducts extending annularly around the body (50) to receive gas exhaust from the engine and the air ducts have entrance ends annularly outwardly of the gas ducts along the wall (70). There are openings (26) in a wall (14) upstream of the ducts to supply ambient air to the entrance ends (80) of the air ducts. There are doors (20) and actuators (24) operable to open and close the openings (26). The ducts are arranged to direct the flow patterns at the exit ends (76, 78) in a relationship inverted from that existing at the entrance ends (80, 82) so that the gas ducts (64) discharge annularly outwardly along shroud (100) and the air ducts (66) discharge annuarly inwardly along the body (50). There is an annulus downstream of the ducts extending between the shroud (100) and the body (50) in which there are longitudinally directed flaps extending annularly around the body and within the shroud. The flaps (126) vary the flow path sizes of the gaz exhaust and air ejected outwardly of the ducts according to various flight mode requirements of the engine. There is also thrust reverser (102) in the shroud which is translatable from an inner position to an outer position, the flaps directing the gas flow through the thrust reverser for stopping the airplane on landing.
摘要翻译：特别适用于超音速飞机的喷气发动机噪声抑制器。喷嘴（10）具有围绕大致中心定位的主体（50）的内壁表面（70）和在壁和主体之间延伸的环形区域（62）。在这个区域中，有独立的气体和空气流动管道（64,66），其具有入口端（82,80）和出口端（76,78），气体管道的入口端围绕主体（50）环形地延伸以接收来自发动机和空气管道的气体排出物具有沿着壁（70）的气体管道的环形外侧的入口端。在管道上游的壁（14）中有开口（26），以向空气管道的入口端（80）供应环境空气。存在门（20）和可操作以打开和关闭开口（26）的致动器（24）。导管布置成以与入口端（80,82）处存在的关系相反的关系与出口端（76,78）处引导流动图案，使得气体导管（64）沿着护罩（100）向外环形排出，并且空气管道（66）沿着主体（50）向内排出。在护罩（100）和主体（50）之间延伸的导管下游具有环形空间，其中具有围绕身体环形延伸并且在护罩内的纵向定向翼片。襟翼（126）根据发动机的各种飞行模式要求改变喷嘴排气和管道外部喷出的空气的流路尺寸。在护罩中还具有可从内部位置平移到外部位置的推力反向器（102），翼片引导气体流动通过推力反向器，以使飞机着陆。

2. 发明申请

WO1997027970A1 MULTISHEET METAL SANDWICH STRUCTURES 审中-公开
标题翻译：多金属金属三角结构
公开(公告)号：WO1997027970A1
公开(公告)日：1997-08-07
申请号：PCT/US1996020106
申请日：1996-12-20
申请人： THE BOEING COMPANY , BULDHAUPT, Frederick, W. , GANE, David, H. , KISTNER, Matthew, G. , WILL, Jeffrey, D.
发明人： THE BOEING COMPANY
IPC分类号： B23K26/00
CPC分类号： B64C1/12 , B21D26/055 , B21D47/00 , B23K26/037 , B23K26/123 , B23K26/206 , B23K26/244 , B23K26/26 , B23K26/28 , B23K26/38 , B23K2101/02 , B64C2001/0081 , Y10T29/18 , Y10T29/49371 , Y10T428/1234 , Y10T428/12347 , Y10T428/12361 , Y10T428/12375
摘要： A method of making an expanded metal sandwich structure (42) includes cleaning the appropriate parts prior to each bonding step in the process to remove metal oxides and residues that would interfere with the bonding steps. The core sheets (44, 46) are placed face-to-face and a gas pressure line fitting (52) is inserted between one edge and is welded into place. The core sheets (44, 46) are pressed together and laser welded together into a core pack (45) along lines which will form junction lines between the core sheets (44, 46) when the core pack (45) is superplastically expanded. Two metal face sheets (48, 50) having superplastic characteristics are placed over and under the core pack (45). An envelope gas fitting (54) is placed between the face sheets and is welded in place while seal welding around the entire peripheral edges of the face sheets (48, 50) and the core pack (45) to produce a sealed envelope pack (47) enveloping the core pack (45).
摘要翻译：制造膨胀金属夹层结构（42）的方法包括在除去将干扰键合步骤的金属氧化物和残留物的过程中的每个结合步骤之前清洁适当的部件。芯片（44,46）面对面设置，气体压力线接头（52）插入在一个边缘之间并被焊接就位。当芯组件（44,46）被超塑化时，芯片（44,46）被压在一起并激光焊接在一起，沿着将形成芯片（44,46）之间的连接线的线。具有超塑性特征的两个金属面板（48,50）放置在芯包（45）的上方和下方。封套气体配件（54）被放置在面板之间并且被焊接就位，同时围绕面板（48,50）和芯组件（45）的整个周边边缘进行密封焊接以产生密封的信封包（47 ）封装核心包（45）。

3. 发明申请

WO1997018612A1 FAULT TOLERANT POWER DISTRIBUTION SYSTEM 审中-公开
标题翻译：容错功率分配系统
公开(公告)号：WO1997018612A1
公开(公告)日：1997-05-22
申请号：PCT/US1996016941
申请日：1996-10-23
申请人： THE BOEING COMPANY
发明人： THE BOEING COMPANY , SHI, Fong
IPC分类号： H02J09/00
CPC分类号： H02J9/00 , H02J1/10
摘要： A power distribution circuit is provided that isolates both power source and load faults. In one embodiment, the power distribution circuit includes two power MOSFETs connected with the channels of the power MOSFETs in series and having their gates electrically connected together. The body diode of one power MOSFET is aligned with the opposite polarity with respect to polarity of the body diode of the second power MOSFET. The power MOSFETs are adapted to be coupled between a first power source and a load. The power distribution circuit also includes a first sensor that detects when the power MOSFETs conduct too much current and switches the power MOSFETs off by discharging the gate voltage of both power MOSFETs during such overcurrent conditions. Accordingly, when both power MOSFETs are switched off, the opposing polarity of the body diodes in the power MOSFETs ensures that one of the body diodes will be reversed biased in case of a short circuit failure in either the load or the power source. Incorporating N such power circuits in a power distribution module for distributing power from N power sources to a single load provides a fault tolerant power distribution module that can tolerate up to N-1 power source faults.
摘要翻译：提供了一种隔离电源和负载故障的配电电路。在一个实施例中，功率分配电路包括串联连接功率MOSFET的沟道并且其栅极电连接在一起的两个功率MOSFET。一个功率MOSFET的体二极管与第二功率MOSFET的体二极管的极性相反的极性对准。功率MOSFET适于耦合在第一电源和负载之间。功率分配电路还包括第一传感器，其检测功率MOSFET何时导通太多电流，并且在这种过电流条件期间通过放电两个功率MOSFET的栅极电压来切断功率MOSFET。因此，当两个功率MOSFET都断开时，功率MOSFET中体二极管的相反极性确保在负载或电源中短路故障的情况下，体二极管之一将被反向偏置。将N个这样的电力电路并入用于将电力从N个电源分配到单个负载的配电模块中，提供容忍高达N-1个电源故障的容错配电模块。

4. 发明申请

WO1996019335A1 HAND ASSISTED LAMINATION SYSTEM 审中-公开
标题翻译：手握层压系统
公开(公告)号：WO1996019335A1
公开(公告)日：1996-06-27
申请号：PCT/US1994014666
申请日：1994-12-20
申请人： THE BOEING COMPANY
发明人： THE BOEING COMPANY , KLINE, William, T. , NEILSON, George, V. , MITTELSTADT, Robert, F.
IPC分类号： B29C70/38
CPC分类号： B29C70/30 , B29C31/085 , B29C70/342 , B32B38/1841
摘要： Apparatus (1 or 301) for use in making a laminated article having a three-dimensional contoured shape, said apparatus (1) comprising: (a) lay-up tool means (31 or 308) for receiving plies of a laminating material, said lay-up tool means having a three-dimensional contoured surface; (b) support table means (34) for supporting said lay-up tool (31 or 308); (c) laser projection means (72) for marking the location of a ply by projecting an image defined by a three-dimensional data set (33) onto said lay-up tool (31 or 308); (d) compactor means (35) for compacting a ply of material laid on said surface of said lay-up tool (31 or 308); and (e) control means (47) for controlling said laser projection means (72) and said compactor means (35).
摘要翻译：用于制造具有三维轮廓形状的层压制品的装置（1或301），所述装置（1）包括：（a）用于接收层压材料层的堆叠工具装置（31或308），所述堆叠工具意味着具有三维轮廓表面; （b）用于支撑所述铺设工具（31或308）的支承台装置（34）; （c）用于通过将由三维数据组（33）定义的图像投影到所述叠层工具（31或308）上来标记层的位置的激光投射装置（72）; （d）用于压实铺设在所述铺设工具（31或308）的所述表面上的材料层的压实机装置（35）; 和（e）用于控制所述激光投射装置（72）和所述压实装置（35）的控制装置（47）。

5. 发明申请

WO1995001660A1 NOSE GEAR DOOR INTEGRAL COMPOSITE GLIDE SLOPE ANTENNA 审中-公开
标题翻译： NOSE齿轮门整体复合滑坡斜坡天线
公开(公告)号：WO1995001660A1
公开(公告)日：1995-01-12
申请号：PCT/US1994007338
申请日：1994-06-29
申请人： THE BOEING COMPANY
发明人： THE BOEING COMPANY , RIVERA, Jose, L. , RODMAN, William, L. , SPENCER, Donald, B. , STAPLETON, Brian, P.
IPC分类号： H01Q01/28
CPC分类号： H01Q1/28 , H01Q13/18
摘要： A glide slope antenna for receiving information transmitted from the ground, including elevation guidance for the final approach. The glide slope antenna is integrated with the aft nose wheel door and utilizes the inherent electrical properties associated with the graphite/epoxy composite door.
摘要翻译：一个滑坡天线，用于接收从地面传出的信息，包括最终进近的仰角指导。滑翔天线与后轮门集成，并利用与石墨/环氧复合门相关的固有电气特性。

6. 发明申请

WO1994024430A1 CASCADE ASSEMBLY FOR USE IN A THRUST-REVERSING MECHANISM 审中-公开
标题翻译： CASCADE大会用于扭转机制
公开(公告)号：WO1994024430A1
公开(公告)日：1994-10-27
申请号：PCT/US1994004097
申请日：1994-04-13
申请人： THE BOEING COMPANY
发明人： THE BOEING COMPANY , LUTTGEHARM, Clint, A. , TODD, Marty, J. , WELCH, John, M.
IPC分类号： F02K01/56
CPC分类号： F02K1/563 , F02K1/605 , F02K1/72
摘要： A cascade assembly (14) for use in a thrust reversing mechanism (16) of a jet engine (18) includes at least one group of substantially identically-shaped cascade elements (28) each in the shape of a predefined polygon. The cascade elements (28) are positioned in an array, wherein each cascade element (28) in the group may be interchanged in a location in the array with any other cascade element (28) in the group. In a first preferred embodiment, the predefined polygon is a regular polygon and each cascade element (28) is rotatable in its array position about an axis generally normal to the cascade element (28). The array substantially approximates sections of two intersecting spheres, wherein a central axis of the array is generally coincident with the longitudinal axis of the jet engine (18). The cascade elements (28) are supported in the cascade assembly (14) by a truss structure (30) having a framework defining openings (32) in the shape of the predefined regular polygon for receiving the cascade elements (28).
摘要翻译：用于喷气发动机（18）的推力反向机构（16）中的级联组件（14）包括至少一组基本上相同形状的级联元件（28），每个级联元件（28）均具有预定多边形的形状。级联元件（28）定位在阵列中，其中该组中的每个级联元件（28）可以与该组中的任何其它级联元件（28）在阵列中的位置互换。在第一优选实施例中，预定多边形是正多边形，并且每个级联元件（28）可围绕通常垂直于级联元件（28）的轴在其阵列位置中旋转。该阵列基本上近似于两个相交的球体的部分，其中该阵列的中心轴线大致与喷气发动机（18）的纵向轴线重合。级联元件（28）通过桁架结构（30）支撑在级联组件（14）中，桁架结构（30）具有限定用于接纳级联元件（28）的预定正多边形形状的开口（32）的框架。

7. 发明申请

WO1993018494A1 THERMAL CONDITION SENSOR SYSTEM FOR MONITORING EQUIPMENT OPERATION 审中-公开
标题翻译：用于监控设备操作的热条件传感器系统
公开(公告)号：WO1993018494A1
公开(公告)日：1993-09-16
申请号：PCT/US1993002137
申请日：1993-03-10
申请人： THE BOEING COMPANY
发明人： THE BOEING COMPANY , BROUDY, Robert, Malcolm , GOLDSTICK, Edward, Charles , HOLM, David, Allen , HOLT, Federick, B. , IVERSON, Alan, Neil , RIEMER, Dietrich, E. , TYLEE, James, Louis
IPC分类号： G08B17/12
CPC分类号： G01J5/02 , G01J5/0205 , G01J5/025 , G01J5/026 , G01J5/08 , G01J5/0815 , G01J5/0821 , G01J5/0834 , G01J5/0862 , G01J5/0893 , G01J5/60 , G01J5/62 , G01J2005/068 , G08B17/12
摘要： A thermal condition sensor system monitors equipment such as aircraft engines. The thermal condition sensor system includes a collector which collects radiation from the equipment and a detector assembly which detects collected radiation over a discriminating spectral band region in at least three spectral bands and generates signals representative of detected radiation in each spectral band. A processor receives the signals and generates a report of the thermal conditions of the equipment using interband comparison of the at least three spectral bands.
摘要翻译：热状态传感器系统监视飞机发动机等设备。热条件传感器系统包括收集来自设备的辐射的收集器和检测器组件，该检测器组件在至少三个光谱带中的识别光谱带区域上检测所收集的辐射，并产生表示每个光谱带中检测到的辐射的信号。处理器接收信号并使用至少三个光谱带的区间比较来生成设备的热条件的报告。

8. 发明申请

WO1993005409A1 HIGH ACCURACY OPTICAL POSITION SENSING SYSTEM 审中-公开
标题翻译：高精度光学位置传感系统
公开(公告)号：WO1993005409A1
公开(公告)日：1993-03-18
申请号：PCT/US1992007278
申请日：1992-08-27
申请人： THE BOEING COMPANY
发明人： THE BOEING COMPANY , VERTATSCHITSCH, Edward, J. , ABBAS, Gregory, L. , DE LA CHAPELLE, Michael , McCLURE, J., Doyle
IPC分类号： G01S17/32
CPC分类号： G01S17/32 , G01K11/32
摘要： An optical position sensing system for sensing the position of a displaceable element. An electro-optical unit outputs a modulated optical signal and a chirped rf signal. The envelope of the modulated optical signal has a phase that has a known relation to the phase of the chirped rf signal. The electro-optical unit is coupled to a light guide element and receives and transmits the modulated optical signal along an optical path for reflection off a surface of the displaceable element in order to provide a position sensing optical signal. A reference reflecting element is disposed in the optical path upstream of the displaceable element for partially reflecting the transmitted modulated optical signal in order to provide a reference optical signal. A transducing unit receives the rf signal at one input and has another input optically coupled for receiving the position sensing optical signal and the reference optical signal which have, respectively, first and second time delays with respect to the chirped rf signal. The transducing unit produces a multi-frequency electrical signal which includes first and second frequencies corresponding to the first and second time delays, respectively. A position detecting unit coupled to the output of the transducing unit processes the multi-frequency signal in order to determine a difference frequency corresponding to the difference between the first and second frequencies and representing the position of the displaceable element.

9. 发明申请

WO1993002916A1 DUCTED FAN AND PITCH CONTROLS FOR TAIL ROTOR OF ROTARY WING AIRCRAFT 审中-公开
标题翻译：旋转式飞机尾部转子的风扇和调节控制
公开(公告)号：WO1993002916A1
公开(公告)日：1993-02-18
申请号：PCT/US1992006441
申请日：1992-07-31
申请人： THE BOEING COMPANY
发明人： THE BOEING COMPANY , DESJARDINS, Rene, A. , McCARDLE, Francis, H.
IPC分类号： B64C27/45
CPC分类号： B64C27/82 , B64C27/45 , B64C2027/8254
摘要： A tail rotor (8) for a rotary wing aircraft is located in a laterally directed duct (9) located at the end of a tail cone (7) extending rearward from the aircraft cabin and at the base of an empennage (5) extending upward from the duct. The rotor includes a rotor shaft (50) driveably connected to a power source, a rotor hub (10) connected to the rotor shaft (50), a rotating control shaft (64), a stationary control shaft (124), and an actuator (132) connected to the stationary control shaft (124) for moving the rotating control shaft (64) axially. The rotor hub (10) includes rotor arms (12) each supporting a pitch shaft-blade spar (18, 16) assembly for pivotable movement about a pitch axis. A pitch beam (96) supports flexures (94), each connected to a pitch arm (80) offset laterally from the associated pitch axis. The flexures (94) driveably connect the pitch arms (80) to the pitch beam (96) and transmit pitch control motion to the blades (14) as the pitch beam (96) moves along the rotor axis. Pitch bearings (20, 22), on which the pitch shafts (18) turn about the pitch axes, are supported on a rotor hub shell (46) fixed to the rotor hub (10).
摘要翻译：用于旋转翼飞行器的尾部转子（8）位于位于从飞机机舱向后延伸并在向上延伸的尾翼（5）的底部的尾锥体（7）的端部处的横向定向的管道（9）从管道。转子包括可驱动地连接到电源的转子轴（50），连接到转子轴（50）的转子轮毂（10），旋转控制轴（64），静止控制轴（124）和致动器（132），其连接到用于使旋转控制轴（64）轴向移动的固定控制轴（124）。转子轮毂（10）包括转子臂（12），每个转子臂支撑俯仰轴叶片翼梁（18,16）组件，用于围绕俯仰轴线的可枢转运动。俯仰梁（96）支撑弯曲部（94），每个弯曲部（94）均连接到从关联的俯仰轴线侧向偏移的俯仰臂（80）。当俯仰梁（96）沿着转子轴线移动时，挠曲件94可驱动地将俯仰臂（80）连接到俯仰梁（96）并将桨距控制运动传递到叶片（14）。俯仰轴（18）围绕俯仰轴转动的俯仰轴承（20,22）支撑在固定在转子毂（10）上的转子轮毂壳（46）上。

10. 发明申请

WO1992016024A2 BROADBAND QUANTUM WELL LED 审中-公开
标题翻译：宽带量具LED
公开(公告)号：WO1992016024A2
公开(公告)日：1992-09-17
申请号：PCT/US1992001962
申请日：1992-03-11
申请人： THE BOEING COMPANY
发明人： THE BOEING COMPANY , HAGER, Harold, E. , MANTZ, Joseph, L.
IPC分类号： H01L33/00
CPC分类号： H01L33/38 , B82Y20/00 , H01L33/0045 , H01L33/06 , H01S5/0425 , H01S5/1021
摘要： An LED having a broadband emission spectrum. In one embodiment, the LED comprises a layered semiconductor structure of length L, the structure including an active layer comprising multiple asymmetric quantum wells. A pair of stripe electrodes is formed on a surface of the structure, to thereby form at least one optical cavity having a pumped length less than L. Currents to the cavities are controlled as a function of temperature to produce broadband emission over a range of temperatures.

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