利索-全球专利检索

  1. 登录
  2. 注册

搜索结果

336 条记录 (耗时 0.017 秒)

    Solder Joint Damage-Prevention Mode for a Computing Device
    1.
    发明申请
    Solder Joint Damage-Prevention Mode for a Computing Device 有权

    公开(公告)号：US20220237059A1

    公开(公告)日：2022-07-28

    申请号：US17316376

    申请日：2021-05-10

    申请人： Google LLC

    发明人： Luke Manuel Brantingham ,  Kavinaath Murugan ,  Yun Sun Lee ,  Aaditya Kandibanda

    IPC分类号： G06F11/00 ,  G06F1/20 ,  G06F1/3206 ,  G06F9/48 ,  G01C19/44

    摘要： This document describes techniques and apparatuses including a solder joint damage-prevention mode for a computing device. In general, the computing device may enter the solder joint damage-prevention mode to transfer heat to solder joints and prevent failure mechanisms such as fracture, creep, and/or fatigue. The solder joint damage-prevention mode may rely upon one or more operations, including identifying a state of the computing device in or following which damage to the solder joints has an increased likelihood and, in response, activating a thermal-conditioning system. The thermal-conditioning system may, in general, increase a temperature of the solder joints to improve mechanical robustness of the solder joints.

    Aircraft body-axis rotation measurement system
    5.
    发明授权
    Aircraft body-axis rotation measurement system 失效
    飞机体轴旋转测量系统

    公开(公告)号：US4387513A

    公开(公告)日：1983-06-14

    申请号：US242790

    申请日：1981-03-11

    申请人： Kenneth T. Cowdin

    发明人： Kenneth T. Cowdin

    IPC分类号： G01C21/18 ,  G01C19/44

    CPC分类号： G01C21/18 ,  Y10T74/1221

    摘要： A two-gyro four-gimbal attitude sensing system having gimbal lock avoidance is provided with continuous azimuth information, rather than roll information, relative to the magnetic cardinal headings while in near vertical attitudes, thereby to allow recovery from vertical on a desired heading. The system is comprised of means (48) for stabilizing an outer roll gimbal (14) that is common to a vertical gyro (12) and a directional gyro (10) with respect to the aircraft platform (50) which is being angularly displaced about an axis substantially parallel to the outer roll gyro axis, and means (38) for producing a signal indicative of the magnitude of such displacement (62, 64) as an indication of aircraft heading. Means are provided to cause stabilization of the outer roll gimbal (14) whenever the pitch angle of the aircraft passes through a threshold prior to entering vertical flight and destabilization of the outer roll gimbal (14) upon passing through the threshold when departing vertical flight.

    摘要翻译： 具有万向节锁避免的双陀螺四万向姿态感测系统在近似垂直姿态下具有相对于磁性主要航向的连续方位信息而不是滚动信息，从而允许在所需航向上从垂直方向恢复。 该系统包括用于稳定垂直陀螺仪（12）共同的外侧卷筒（14）和相对于飞行器平台（50）的定向陀螺仪（10）的装置（48），所述飞行器平台围绕 基本上平行于外滚子陀螺轴的轴线以及用于产生指示作为飞行器航向的指示的这种位移（62,64）的大小的信号的装置（38）。 只要航空器的俯仰角在进入垂直飞行之前通过阈值并且在离开垂直飞行时经过阈值后使外侧卷筒万向节（14）不稳定，则提供装置以使外部卷轴（14）稳定。

    Device for determining vertical direction
    6.
    发明授权
    Device for determining vertical direction 失效
    用于确定垂直方向的装置

    公开(公告)号：US4265111A

    公开(公告)日：1981-05-05

    申请号：US9568

    申请日：1979-02-05

    申请人： Torbern Teiling

    发明人： Torbern Teiling

    IPC分类号： F41G5/16 ,  G01C19/44 ,  G01C21/00

    CPC分类号： G01C19/44 ,  F41G5/16

    摘要： An improved system for determining the vertical direction relative to a moving base includes gyroscopic rate sensors for determining angular velocities of a device such as a weapon mounted on the base, relative to two orthogonal axes; a gyroscopic rate sensor for determining the roll angle velocity of the system and a calculating circuit for determining the roll and pitch angles needed to ascertain the vertical direction.

    摘要翻译： 用于确定相对于移动基座的垂直方向的改进系统包括用于确定相对于两个正交轴线安装在基座上的诸如武器的装置的角速度的陀螺仪速率传感器; 用于确定系统的侧倾角速度的陀螺仪速率传感器和用于确定确定垂直方向所需的滚动和俯仰角的计算电路。

    Aircraft gyrohorizon indicator with signal lamp positional attitude indicating means
    7.
    发明授权
    Aircraft gyrohorizon indicator with signal lamp positional attitude indicating means 失效
    具有信号灯的飞机GYROHORIZON指示器指示手段的位置姿态

    公开(公告)号：US3852710A

    公开(公告)日：1974-12-03

    申请号：US27293572

    申请日：1972-06-13

    申请人： AIRCRAFT INSTR INC

    发明人： HERNANDEZ R

    IPC分类号： G01C19/44 ,  G08G5/00

    CPC分类号： G01C19/44

    摘要： A combination gyrohorizon instrument for aircraft which visually indicates in addition to the dial display presentation of the instrument, by means of signal lamps appropriately placed with respect to the instrument dial and an audible signal indicative of energization of any one of the signal lamps, departures from straight and level flight that exceed reasonable limits of pitch and bank. The signal lamps, indicating ''''nose up,'''' ''''nose down, '''' ''''left wing down'''' and ''''right wing down'''' are in circuits energized by a first switching means controlled by the relative rotational position of the inner and outer gimbals of the instrument for sensing departure beyond reasonable safety limits in one direction or the other in the pitch axis, i.e., either ''''nose up'''' or ''''nose down'''' flight, and a second switch means controlled by the relative rotation position of the outer gimbal and the instrument casing for sensing departure beyond reasonable limits in the roll axis, i.e., either ''''left wing down'''' or ''''right wing down'''' flight.

    摘要翻译： 用于飞行器的组合陀螺仪仪器，除了通过适当放置在仪表盘上的信号灯和指示任何一个信号灯通电的可听信号之外，还可以直观地指示仪器的拨号显示器显示。 直线和水平飞行超过音高和银行的合理限制。 指示“上升”，“下降”，“左翼下降”和“右翼下降”的信号灯由通过仪器的内部和外部万向面的相对旋转位置控制的第一切换装置通电 用于在一个方向或在俯仰轴上的另一个方向（即，“向上”或“向下”）飞行中感测出超出合理的安全限制，以及由外部万向架和仪器的相对旋转位置控制的第二开关装置 用于感测离开超出滚轴轴线合理限度的外壳，即“左翼下降”或“右翼下降”飞行。

    Pitch signal calculator for aircraft
    8.
    发明授权
    Pitch signal calculator for aircraft 失效
    飞机信号计算器

    公开(公告)号：US3744309A

    公开(公告)日：1973-07-10

    申请号：US3744309D

    申请日：1970-07-20

    申请人： UNITED CONTROL CORP

    发明人： ASTENGO R

    IPC分类号： G01C19/44 ,  G01C23/00

    CPC分类号： G01C19/44

    摘要： An instrument for calculating the pitch angle of an aircraft from two pitch signals, one having long term and the other short term pitch accuracy. The long term pitch signal is derived from a longitudinal accelerometer. A measured pitch signal having short term accuracy is provided by a vertical gyroscope. An airspeed acceleration signal is provided by a vertical gyroscope. An airspeed acceleration signal is subtracted from the accelerometer output to eliminate the acceleration component of the signal. The calculated and measured pitch signals are combined or blended in selected inverse proportions.

    摘要翻译： 一种用于从两个音调信号计算飞机的俯仰角的仪器，一个具有长期距离，另一个是短距离精度。 长期的音调信号是从纵向加速度计导出的。 通过垂直陀螺仪提供具有短期精度的测量的音调信号。 空速加速度信号由垂直陀螺仪提供。 从加速度计输出中减去空速加速度信号，以消除信号的加速度分量。