公开(公告)号：WO1994009276A1

公开(公告)日：1994-04-28

申请号：PCT/US1992008884

申请日：1992-10-16

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  MAHER, John, F., Jr. ,  MERRITT, Brent, J. ,  MCAULIFFE, Christopher ,  DZIORNY, Paul, J.

IPC: F04D25/04

CPC classification number: F04D29/057 ,  B64D13/00 ,  F04D25/04

Abstract: An air cycle machine (10) has four wheels mounted on a common shaft (20) for rotation therewith about a longitudinal axis (12) including a second stage turbine rotor (30) mounted to a first end (20a) of the shaft, a fan rotor (40) mounted to a second end (20b) of the shaft, a first stage turbine rotor (50) mounted to a central portion (20c) of the shaft, a compressor rotor (60) mounted to the central portion of the shaft in back to back relation to the first stage turbine rotor, the first and second stage turbine torors being operative to extract energy from a flow of compressed air for driving the shaft (20), and the fan rotor (40) and the compressor rotor (60), in rotation about the axis, and first and second hydrodynamic gas film foil bearings (70, 80) for supporting the shaft for rotation about the longitudinal axis (12).

Abstract translation: 空气循环机（10）具有安装在公共轴（20）上的四个轮子，用于围绕包括安装在轴的第一端（20a）上的第二级涡轮机转子（30）的纵向轴线（12）旋转， 安装在所述轴的第二端（20b）的风扇转子（40），安装在所述轴的中心部分（20c）上的第一级涡轮机转子（50），安装在所述轴的中心部分的压缩机转子 所述第一和第二级涡轮机可操作以从用于驱动所述轴（20）的压缩空气流中提取能量，并且所述风扇转子（40）和所述压缩机转子 （60），围绕所述轴线旋转的第一和第二流体动力气体膜箔片轴承（70,80），用于支撑所述轴以围绕所述纵向轴线（12）旋转。

公开(公告)号：WO1994007743A1

公开(公告)日：1994-04-14

申请号：PCT/US1993009048

申请日：1993-09-24

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  DEL MONTE, Berardino

IPC: B64C25/50

CPC classification number: B64C25/50

Abstract: An aircraft landing locking pin (12) automatically repositions from an engage position, wherein a rotating portion (15) of the landing gear is prevented from rotating, to a released position, wherein the rotating portion if free to rotate, in response to excessive side loading on the landing gear. The locking pin comprises a spring loaded actuator (32, 34, 60) which urges a roller (19) of a lock pin assembly (20) in contact with a bushing (22). In response to a side loading on the landing gear in excess of a predetermined loading, the locking pin is automatically released wherein the roller is expelled from the bushing. The threshold loading is determined as a function of the spring force applied to the lock pin assembly via the actuator linkage. The locking pin automatically reengages when the lock pin assembly is aligned with the bushing.

Abstract translation: 飞机着陆锁定销（12）自动地从接合位置重新定位，其中起落架的旋转部分（15）被防止旋转到释放位置，其中旋转部分如果响应于过度的一侧而自由旋转 装载起落架。 锁定销包括弹簧加载的致动器（32,34,60），其推动与套管（22）接触的锁销组件（20）的辊（19）。 响应于超过预定负载的起落架上的侧向负载，锁定销自动释放，其中辊从衬套排出。 根据通过致动器连接件施加到锁销组件的弹簧力来确定阈值负载。 当锁销组件与衬套对齐时，锁定销自动重新接合。

公开(公告)号：WO1994002731A1

公开(公告)日：1994-02-03

申请号：PCT/US1993002755

申请日：1993-03-18

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  BARCZA, William, Kevin

IPC: F02K01/12

CPC classification number: F02K1/1223 ,  F02K1/008 ,  F02K1/805 ,  F05D2250/31 ,  F05D2250/323 ,  F05D2250/324

Abstract: A divergent flap hinge seal (22) for a thrust vectoring nozzle (10) is pivotally connected to the convergent flap (12), and the divergent flap (14) is pivotally connected to this flap hinge seal (22). An extension (48) on the hinge seal sealingly overlies a recess (50) in the divergent flap (14).

Abstract translation: 用于推力矢量喷嘴（10）的发散翼片铰链密封件（22）枢转地连接到会聚翼片（12），并且发散片（14）枢转地连接到该翼片铰链密封件（22）。 铰链密封件上的延伸部（48）密封地覆盖发散片（14）中的凹部（50）。

公开(公告)号：WO1994000962A1

公开(公告)日：1994-01-06

申请号：PCT/US1993006245

申请日：1993-06-30

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  KAPOOR, Mohan, L. ,  REBESCHI, Thomas, J.

IPC: H05B33/08

CPC classification number: G09G3/2011 ,  G09G3/30 ,  G09G2310/0259 ,  G09G2310/027

Abstract: Pixel luminance of an electroluminescent display panel (22) is controlled by a row driver (24) applying a voltage equal to the panel's threshold voltage, and column drivers (26) applying the voltage value above the threshold voltage to bring the pixel (30) to the desired luminance. Each column driver (26) independently samples a stepped ramp voltage signal at its own predetermined time selected as a function of the desired luminance. Each column driver (26) then holds the sampled voltage value, and applies to its corresponding column electrode at the appropriate time a voltage equal to the sampled voltage value. The voltage rate of change of each individual step of the stepped ramped voltage signal can be controlled to vary the luminance levels, and to uniformly separate each of the luminance levels.

Abstract translation: 电致发光显示面板（22）的像素亮度由施加与面板阈值电压相等的电压的行驱动器（24）控制，并且列驱动器（26）施加高于阈值电压的电压值以使像素（30） 达到期望的亮度。 每个列驱动器（26）独立地以其所选择的预定时间作为期望亮度的函数来采样阶梯斜坡电压信号。 每个列驱动器（26）然后保持采样的电压值，并在适当的时间将其对应的列电极施加到等于采样的电压值的电压。 可以控制阶梯式斜坡电压信号的每个步骤的电压变化率，以改变亮度级别，并且均匀地分离每个亮度级。

公开(公告)号：WO1993024677A1

公开(公告)日：1993-12-09

申请号：PCT/US1993004969

申请日：1993-05-25

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  CARLSON, Hugh, A. ,  LEONIDA, Andrei ,  MCELROY, James, F. ,  SHANE, Eric, M.

IPC: C25B09/00

CPC classification number: C25B9/08 ,  C25B1/10 ,  C25B9/10 ,  Y02E60/366

Abstract: Due to the limited structural integrity of the ion exchange membrane, operation at pressure gradients exceeding about 200 psi can cause electrolyzer failure due to the ion exchange membrane being physically forced into the holes of the screen set forming the chamber on the lower pressure side of the ion exchange membrane. Utilizing a porous sheet (14) between the anode electrode (7) and the screen set (1) provides additional structural integrity to the ion exchange membrane and allows simultaneous dual-directional flow of water to the anode electrode while oxygen flows from the anode electrode, thereby allowing high pressure gradient operation.

公开(公告)号：WO1993023797A1

公开(公告)日：1993-11-25

申请号：PCT/US1993003911

申请日：1993-04-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  FOWLER, Donald, W. ,  LAPPOS, Nicholas, D.

IPC: G05D01/08

CPC classification number: G05D1/0858 ,  B64C13/503 ,  F41G3/12 ,  G05D1/0833

Abstract: During operation of an integrated fire and flight control (IFFC) system in a coupled aiming mode, the occurrence of a weapon (172), weapon mount (145) or sensor (146) reaching a constraint limit (210) induces a fade-in of a constraint limiting axis command signal (140) for a respective attitude axis as the aircraft attitude reference, replacing the flight control system attitude feedback error signal (111) for the respective attitude axis. The constraint limiting axis command signals provide the aircraft attitude reference only while the pilot manually depresses and holds an enable switch (920). The pilot command stick input (90) remains the primary input to the IFFC system to thereby provide override capability for pilot command maneuvers.

公开(公告)号：WO1993023715A1

公开(公告)日：1993-11-25

申请号：PCT/US1993004336

申请日：1993-05-07

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  FOWLER, Donald, W. ,  LAPPOS, Nicholas, D. ,  DRYFOOS, James, B. ,  KELLER, James, F.

IPC: F41G03/22

CPC classification number: F41G3/22 ,  G05D1/085 ,  G05D1/0858

Abstract: A fire control system (55) azimuth command and elevation command provides a flight control system attitude reference in response to operation of the flight control system in a coupled aiming mode. The coupled aiming mode is engaged in response to the continuous operation of a pilot switch (920), the azimuth command and elevation command being below respective threshold magnitudes (940, 941), and the operation of the fire control system (55). During operation in the coupled aiming mode, the azimuth command and elevation command replace the yaw attitude feedback error signal and pitch attitude error signal, respectively, as the aircraft attitude reference. During integration of the fire control system and the flight control system, the flight control system is made less sensitive to small pilot command stick inputs below a stick input threshold magnitude, so that small or inadvertent pilot commanded yaw and pitch maneuvers will not affect the yaw and pitch attitude reference commanded by the fire control system azimuth and elevation commands. However, intended pilot commanded yaw and pitch maneuvers (70) maintain full authority at all times.

Abstract translation: 消防控制系统（55）方位指令和仰角命令提供飞行控制系统姿态参考，以响应飞行控制系统在耦合瞄准模式下的操作。 响应于先导开关（920）的连续操作，方位指令和仰角指令低于相应的阈值大小（940,941）以及消防控制系统（55）的操作而被耦合的瞄准模式。 在联合瞄准模式下，方位指令和仰角指令分别代替飞行姿态反馈误差信号和俯仰姿态误差信号作为飞机姿态参考。 在消防控制系统和飞行控制系统的集成期间，使飞行控制系统对小型导向指令杆输入的敏感度低于杆输入阈值大小，从而小型或无意的飞行员指挥的偏航和俯仰机动不会影响偏航 以及由消防控制系统方位角和仰角指令指示的俯仰姿态参考。 然而，预期的飞行员指挥偏航和俯仰机动（70）始终保持完全的权威。

公开(公告)号：WO1993022689A1

公开(公告)日：1993-11-11

申请号：PCT/US1993004225

申请日：1993-05-04

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  BEATRICE, Finton, J.

IPC: G01P03/486

CPC classification number: G01D5/39 ,  G01P3/486

Abstract: An optic speed sensor for sensing the speed of a rotating component such as a gear includes a sensor such as an electromagnetic speed sensor disposed in proximity to teeth of the gear. Within the housing of the sensor are one or more electrical signal lines having electrical signals imposed thereon, the electrical signals being indicative of the rotational speed of the gear. Physically connected to the sensor housing is a mating connector. Disposed within the housing of the mating connector are corresponding one or more LEDs, each LED being electrically connected to the electrical speed signals provided by the sensor. Each LED provides an optical signal indicative of the speed of the gear, each LED having fiber optic cable connected thereto which transmits the optical energy output by the associated LED to an optical receiver disposed away from the sensor, such as a control unit for the device incorporating the gear. The optical receiver transforms the optical signal into a form, such as to an electrical signal, more suitable for the type of signal processing performed at the predetermined location.

公开(公告)号：WO1993022127A1

公开(公告)日：1993-11-11

申请号：PCT/US1993003865

申请日：1993-04-23

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  MCINTYRE, Allen, J. ,  DAVIS, Geoffrey, C.

IPC: B29C65/00

CPC classification number: B29C65/342 ,  B29C37/0078 ,  B29C65/3448 ,  B29C65/3452 ,  B29C65/3468 ,  B29C65/3476 ,  B29C65/362 ,  B29C66/1222 ,  B29C66/1224 ,  B29C66/1226 ,  B29C66/5344 ,  B29C66/612 ,  B29C66/721 ,  B29C66/72143 ,  B29C66/73751 ,  B29C66/73755 ,  B29C66/73771 ,  B29C66/73773 ,  B29C66/7392 ,  B29C66/73921 ,  B29C66/7394 ,  B29L2031/75 ,  F16C3/026

Abstract: Methods for bonding metallic structures to thermoplastic and thermoset composite structures are described. The methods include steps for preparing the metallic structure (14) for bonding by knurling a mating surface of the metallic structure and molding a layer of thermoplastic material (50) over the knurled mating surface to produce a bonding surface. To bond a metallic structure (14) to a thermoplastic composite structures (16), the bonding surface of the metallic fitting is consolidated with the thermoplastic composite structure (50). To bond a metallic structure to a thermoset composite structure, a bonding surface is formed on the thermoset composite structure by partially embedding a layer of dry fibre reinforcement in a thermoplastic material layer, coating the exposed dry fiber reinforcement with thermoset resin, and curing the coating dry fiber reinforcement into the thermoset composite structure. The bonding surfaces of the thermoset composite structure and the metallic structure are then fused together by applying heat sufficient to melt the thermoplastic material layers of the bonding surfaces. A resistance heating element (54) is disposed between the bonding surfaces of the thermoset composite structure (16) and the metallic structure to provide the heat required to melt the thermoplastic material layers of the bonding surfaces.

Abstract translation: 描述了将金属结构粘合到热塑性和热固性复合结构上的方法。 所述方法包括用于通过滚花金属结构的配合表面来制备用于接合的金属结构（14）的步骤，并且在滚花配合表面上成型一层热塑性材料（50）以产生粘合表面。 为了将金属结构（14）结合到热塑性复合结构（16）上，金属配件的接合表面与热塑复合结构（50）固结。 为了将金属结构结合到热固性复合结构上，通过在热塑性材料层中部分地包埋干纤维增强层，在热固性复合结构上形成接合表面，用热固性树脂涂覆暴露的干纤维增强材料，并固化涂层 干纤维增强成热固性复合结构。 然后通过施加足以熔化粘合表面的热塑性材料层的热量将热固性复合结构和金属结构的粘合表面熔合在一起。 电阻加热元件（54）设置在热固性复合结构（16）和金属结构的接合表面之间，以提供熔化接合表面的热塑性材料层所需的热量。

公开(公告)号：WO1993022097A1

公开(公告)日：1993-11-11

申请号：PCT/US1993004326

申请日：1993-05-06

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  PIETRUSKA, Norman ,  KURPASKA, Michael, S.

IPC: B23K35/30

CPC classification number: B23P6/002 ,  B23K35/3046 ,  B23P6/007 ,  C22F1/10 ,  F01D5/005

Abstract: An improved method is described for repairing Co-base superalloy gas turbine engine components by applying a mixture of base alloy powder and base alloy powder with a melting point depressant to the surface of the component and heating at 2250-2300 DEG F to diffuse the melting point depressant isothermally into the base alloy. A protective coating is then applied, during which a heating cycle which ages the base material is used. The resultant component has high temperature creep properties which are significantly better than achieved using the prior art process. The same temperature cycle is also useful in the initial heat treatment of Co-base superalloys, and can also be used for rejuvenation of components which have experienced extensive exposure to engine operating conditions.

Abstract translation: 描述了一种改进的方法，用于通过将基础合金粉末和基底合金粉末与熔点低于组分表面的基础合金粉末混合并在2250-2300°F加热来扩散熔融物来修复Co基超合金燃气轮机发动机部件 点状抑制剂等温进入基体合金。 然后施加保护涂层，在此期间使用使基材老化的加热循环。 所得组分具有高温蠕变性能，其明显优于使用现有技术方法的实施。 相同的温度循环在共碱基超级合金的初始热处理中也是有用的，并且还可以用于经历大量暴露于发动机操作条件的部件的复原。