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3564 条记录 (耗时 0.02 秒)

    Aerodynamic window
    1.
    发明授权
    Aerodynamic window 失效
    气动窗

    公开(公告)号：US3907409A

    公开(公告)日：1975-09-23

    申请号：US43711474

    申请日：1974-01-28

    申请人： UNITED AIRCRAFT CORP

    发明人： HAUSMANN GEORGE F

    IPC分类号： H01S3/034 ,  H01S3/22 ,  G02B5/00

    CPC分类号： H01S3/0343

    摘要： An improved aerodynamic window is provided for laser systems where the pressure in the lasing cavity is lower than ambient pressure. An opening is located in the system to permit a laser beam to pass from the lasing cavity to the exterior thereof. A window is needed in the opening to prevent a flow of air from the ambient pressure into the low pressure in the lasing cavity. The window consists of a multiplicity of inlet ducts on one side of the opening supplied with a high pressure gas with each duct having a Laval nozzle for expanding the gas. The ducts are curved in a manner to provide a prescribed radial variation in velocity and static pressure therein. The pressure and Mach number in the ducts associated therewith provide a centrifugal flow across the opening. An outlet duct on the other side of the opening receives the flow from the inlet ducts after the flow has crossed the opening.

    摘要翻译： 为激光系统提供改进的空气动力学窗口，其中激光腔中的压力低于环境压力。 开口位于系统中，以允许激光束从激光腔传递到其外部。 在开口中需要一个窗口，以防止空气从环境压力流入激光腔中的低压。 窗口由开口的一侧上的多个入口管道组成，每个管道具有用于膨胀气体的拉瓦尔喷嘴。 这些管道以其中的速度和静压力提供规定的径向变化的方式弯曲。 与其相关联的管道中的压力和马赫数提供穿过开口的离心流。 开口另一侧的出口管道在流动已经穿过开口后接收来自入口管道的流动。

    High speed hydraulic sensor
    5.
    发明授权
    High speed hydraulic sensor 失效
    高速液压传感器

    公开(公告)号：US3896675A

    公开(公告)日：1975-07-29

    申请号：US41863373

    申请日：1973-11-23

    申请人： UNITED AIRCRAFT CORP

    发明人： STEARNS CHARLES F ,  HANSEN KENNETH P

    IPC分类号： G01P3/28

    CPC分类号： G01P3/28

    摘要： A hydromechanical high speed sensor is designed to accurately measure speed by utilizing a rotating valve providing a pumping action and a buoyant ball mounted in the valve for metering fluid in a closed circuit and being sized to compensate for changes in fluid density.

    摘要翻译： 液压机械式高速传感器被设计为通过利用提供泵送作用的旋转阀和安装在阀中的浮力球来精确测量速度，用于在闭合回路中计量流体并且其尺寸适于补偿流体密度的变化。

    Gas turbine engine for subsonic flight
    6.
    发明授权
    Gas turbine engine for subsonic flight 失效
    用于亚音速飞行的燃气涡轮发动机

    公开(公告)号：US3896615A

    公开(公告)日：1975-07-29

    申请号：US51228674

    申请日：1974-10-04

    申请人： UNITED AIRCRAFT CORP

    发明人： SLATKIN MARTIN S ,  MOTYCKA DAVID L ,  DISABATO VINCENT J

    IPC分类号： F02K1/00 ,  F02K3/06 ,  F02K1/24

    CPC分类号： F02K1/00

    摘要： A gas turbine engine for use on an aircraft which flies entirely within a subsonic velocity range is provided with a fixed area convergent-divergent nozzle to provide better overall engine performance.

    摘要翻译： 用于在亚音速范围内完全飞行的飞机上的燃气涡轮发动机设置有固定区域会聚发散喷嘴，以提供更好的整体发动机性能。

    High speed electric generator
    7.
    发明授权
    High speed electric generator 失效
    高速电力发电机

    公开(公告)号：US3896320A

    公开(公告)日：1975-07-22

    申请号：US19050971

    申请日：1971-10-19

    申请人： UNITED AIRCRAFT CORP

    发明人： MOFFATT E MARSTON

    IPC分类号： H02K9/19 ,  H02K11/04 ,  H02K19/26 ,  H02K1/32

    CPC分类号： H02K9/19 ,  H02K11/042 ,  H02K19/26

    摘要： A high speed, high voltage, square wave voltage, single slot per pole per phase, two phase, saturated rotary field AC generator having a rotary armature exciter, is comprised of noncompressible, rigid rotary coils utilizing oxided metal conductors having coolant fluid flowing therethrough, at least one surface of every electrical current conductor in the generator being in contact with flowing coolant fluid. The rotary structure is provided with a complete peripheral structural wrapping to oppose the centrifugal force generated in the coils due to high velocity. Rotary diodes between an exciter armature and the main generator, rotary field, a single static DC input and static AC output, and magnetic coupling comprising the sole energy coupling between the stator and the rotor, eliminate the need for slip rings or other electrical conduction through relatively moving parts. One embodiment utilizes turbine-like annular entrance of centrifugal pumping for coolant fluid in the rotary coils; in this embodiment, rotating diodes are mounted on coaxial shaft-like conductors. Another embodiment uses hollow radial conductors to carry coolant fluid, as well as electrical current, to the coils; in this embodiment the radial fluidcontaining electrical conductors are terminated in annular junctions connected to annular diode housings by longitudinal or axial conductors.

    Differential laser gyro employing reflection polarization anisotropy
    8.
    发明授权
    Differential laser gyro employing reflection polarization anisotropy 失效
    差分激光陀螺采用反射极化各向异性

    公开(公告)号：US3890047A

    公开(公告)日：1975-06-17

    申请号：US80201469

    申请日：1969-02-25

    申请人： UNITED AIRCRAFT CORP

    发明人： WARNER RICHARD T

    IPC分类号： G01C19/66 ,  G01P3/36 ,  H01S3/083 ,  H01S3/10

    CPC分类号： H01S3/083 ,  G01C19/667

    摘要： The polarization anisotropy which is utilized together with directional anisotropy so as to form a differential laser gyro system having two laser gyros operating in the same cavity with cavity modes of different frequencies in the form of mutually perpendicular plane polarization in each of the clockwise and counterclockwise directions, is achieved by providing a cavity having an odd number of dielectric mirrors and a total path length adjusted so that the phase reversal of one plane polarized wave (eg, vertical) results in a frequency difference between it and the other (eg, horizontal) polarized wave. The directional anisotropy may suitably be provided by a Faraday cell disposed in the optical path between quarter wave plates.

    摘要翻译： 与方向各向异性一起使用的偏振各向异性，以便形成具有两个激光陀螺仪的差分激光陀螺仪系统，该激光陀螺仪具有两个激光陀螺仪，该激光陀螺仪在相同的空腔中以不同频率的空腔模式在每个顺时针和逆时针方向上以相互垂直的平面偏振的形式 通过提供具有奇数个电介质反射镜的空腔和被调整的总路径长度来实现，使得一个平面偏振波（例如，垂直）的相位反转导致它与另一个之间的频率差（例如，水平） 极化波。 方向各向异性可以适当地由设置在四分之一波片之间的光路中的法拉第单元提供。

    Variable leading edge stator vane assembly
    10.
    发明授权
    Variable leading edge stator vane assembly 失效
    可变前缘定子叶片组件

    公开(公告)号：US3887297A

    公开(公告)日：1975-06-03

    申请号：US48295574

    申请日：1974-06-25

    申请人： UNITED AIRCRAFT CORP

    发明人： WELCHEK MICHAEL JOHN

    IPC分类号： F01D17/16 ,  F01D17/12

    CPC分类号： F01D17/162 ,  F04D29/563

    摘要： A variable leading edge stator vane assembly, particularly suited for use in a bypass gas turbine engine as a last stage fan stator, includes vane spindles on each end of the movable portion which are rotatably disposed in the gas path walls and which are large relative to the thickness of the airfoil so that they extend downstream of the movable portion; the stationary portion of the vane has its leading edge pinned into cavities positioned on the axis of rotation of the vane spindles and its trailing edge secured directly to the flow path walls.

    摘要翻译： 特别适用于作为最后一级风扇定子的旁通燃气涡轮发动机的可变前缘定子叶片组件包括位于可动部分的每一端上的叶片轴，其可旋转地设置在气体通道壁中，并且相对于 翼型件的厚度使得它们延伸到可移动部分的下游; 叶片的固定部分的前缘被钉入位于叶片主轴的旋转轴线上的空腔中，其后缘直接固定在流路壁上。