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    • 22. 发明申请
    • VISCOUSLY COUPLED DUAL BEAM ACCELEROMETER
    • VISCOUSLY耦合双梁加速度计
    • WO1992008140A1
    • 1992-05-14
    • PCT/US1991007882
    • 1991-10-22
    • SUNDSTRAND DATA CONTROL, INC.
    • SUNDSTRAND DATA CONTROL, INC.PETERS, Rex, B.
    • G01P15/08
    • G01P15/097G01P2015/0828
    • An accelerometer (60) includes a first proof mass (32') and a second proof mass (42'), which are respectively connected by flexures (36' and 46') to a first base (34') and a second base (44'). The first and second bases are clamped between a top enclosure (62) and a bottom enclosure (64), between which is defined a cavity (66) in which the first and second proof masses are disposed. A quartz crystal resonator (38') extends between the first proof mass and the first base; similarly, a quartz crystal resonator (48') extends between the second proof mass and second base. The quartz crystal resonators experience tension/compression in a push-pull mode when the accelerometer is subjected to acceleration along an acceleration-sensitive axis (26') that extends transversely through the proof-masses. A fluid within the cavity couples the first and second proof masses together through a ''squeeze film damping'', due to their closely-spaced relationship to each other.
    • 加速度计(60)包括分别通过弯曲(36'和46')连接到第一基座(34')和第二基座(34')的第一检验质量块(32')和第二检验质量块(42' 44' )。 第一和第二基座被夹紧在顶部外壳(62)和底部外壳(64)之间,其间限定有空腔(66),第一和第二检验质量块设置在其中。 石英晶体谐振器(38')在第一检测质量块和第一基底之间延伸; 类似地,石英晶体谐振器(48')在第二检验质量块和第二基底之间延伸。 当加速度计沿着横向延伸穿过检验质量的加速度敏感轴(26')进行加速度时,石英晶体谐振器在推挽模式下经受张力/压缩。 腔内的流体由于它们彼此间隔紧密的关系,通过“挤压膜阻尼”将第一和第二检验质量块连接在一起。
    • 25. 发明申请
    • PITCH GUIDANCE SYSTEM
    • 指针系统
    • WO1991015827A1
    • 1991-10-17
    • PCT/US1991002067
    • 1991-03-26
    • SUNDSTRAND DATA CONTROL, INC.
    • SUNDSTRAND DATA CONTROL, INC.GLOVER, J., Howard
    • G06F15/50
    • G05D1/0623G05D1/0661
    • A pitch guidance system for an aircraft utilizes inertially derived pitch information to provide the pilot with information defining the optimum pitch angle for maximum climb during a wind shear condition. The system utilizes a pitch reference modulator (22) that receives a stall warning discrete from a stall warning system to reduce the commanded pitch angle upon the occurrence of a stall warning to reduce the possibility of stalling the aircraft during degraded performance conditions such as tail winds and engine-out conditions. The system utilizes inertially derived pitch information rather than air mass derived angle of attack information to avoid transients in the angle of attack vane signal, and the commanded pitch angle is biased as a function of altitude (70) and vertical speed (58) to optimize the pitch angle for different altitudes and descent rates.
    • 用于飞行器的俯仰引导系统利用惯性导出的俯仰信息来为飞行员提供定义在风切变条件期间最大爬升的最佳俯仰角的信息。 该系统使用俯仰参考调制器(22),其接收从失速警告系统离散的失速警告,以在出现失速警告时减小指令的俯仰角,以减少在退化的性能状况(例如尾风)期间使飞行器停滞的可能性 和发动机的条件。 该系统利用惯性导出的音调信息,而不是空气质量导出的迎角信息,以避免迎角信号的瞬变,并且指令的俯仰角作为高度(70)和垂直速度(58)的函数被偏置以优化 不同高度和下降率的俯仰角。