公开(公告)号：US5097490A

公开(公告)日：1992-03-17

申请号：US640985

申请日：1991-01-14

Applicant: Rand H. Hulsing, II ,  Charles K. Lee

Inventor： Rand H. Hulsing, II ,  Charles K. Lee

IPC: G01R23/10

CPC classification number: G01R23/10

Abstract: Apparatus and method for counting frequency of a signal with improved resolution. Frequency counters (10, 60, and 100) accumulate clock cycles from a reference oscillator (20) during a sample interval. In the simplest form of the frequency counter, the reference clock signal is inverted and both the noninverted and inverted clock cycles are accumulated in separate counters (40 and 44). The accumulated counts are totaled in a summing circuit (48) and divided by two to determine their average, thereby doubling the resolution of the frequency counter. A more complex embodiment of the invention corrects a raw count of cycles of an input signal (12) that are accumulated during an extended sample interval defined by successive rising edges of a sample signal (114). The fractional portion of a cycle of the input waveform that occurred prior to the beginning of the extended sample interval is added to the raw count and the fractional portion of the input waveform that occurred after the end of the extended sample interval is subtracted. These fractional portions are defined as ratios of a partial count of clock cycles to a full count of clock cycled. The partial count is the number of clock cycles occurring between a rising edge of the sample signal and the next rising edge of the input signal, while the full count is the number of clock cycles occurring between successive rising edges of the input signal. One-half clock logic circuits (126 and 136) double the resolution of the counts accumulated by a partial counter (122) and a full counter (142), thereby doubling the resolution with which the ratios of the two counts are determined.

Abstract translation: 用改进分辨率对信号频率进行计数的装置和方法。 频率计数器（10,60和100）在采样间隔期间从参考振荡器（20）累加时钟周期。 在频率计数器的最简单形式中，参考时钟信号被反相，同相和反相时钟周期都被累积在单独的计数器（40和44）中。 积累的计数总计在求和电路（48）中，并被除以2以确定它们的平均值，从而使频率计数器的分辨率加倍。 本发明的更复杂的实施例校正在由采样信号（114）的连续上升沿限定的扩展采样间隔期间累积的输入信号（12）的周期的原始计数。 在扩展采样间隔开始之前发生的输入波形的周期的小数部分被加到原始计数，并且减去在扩展采样间隔结束之后发生的输入波形的小数部分。 这些小数部分定义为时钟周期的部分计数与循环时钟的完整计数的比率。 部分计数是在采样信号的上升沿和输入信号的下一个上升沿之间发生的时钟周期数，而全部计数是在输入信号的连续上升沿之间发生的时钟周期数。 二分之一时钟逻辑电路（126和136）使由部分计数器（122）和全计数器（142）累积的计数的分辨率翻一倍，从而将确定两个计数的比率的分辨率加倍。

公开(公告)号：US5038141A

公开(公告)日：1991-08-06

申请号：US81557

申请日：1987-07-31

Applicant: Michael M. Grove

Inventor： Michael M. Grove

IPC: G01C21/00 ,  B64D45/04 ,  G01C5/00 ,  G05D1/08 ,  G08B23/00

CPC classification number: G01C5/005

Abstract: Warning systems that monitor the altitude above ground and descent rate of an aircraft and generate a warning if the descent rate of the aircraft is excessive for the altitude in which the aircraft is flying are well suited to aircraft whose flight and operational characteristics are readily predictable but not as suitable for aircraft, such as tactical aircraft whose operating conditions are not so predictable. To overcome this problem, the criteria for providing the warnings are altered (30, 32) as a function of flight configuration (16, 18) to optimize the warnings for different flight conditions.

Abstract translation: 监测飞机高度高于飞机高度的飞行器的下降速率过高的警告系统，如果航空器的飞行高度过大，就会产生警告，这种飞机飞行和操作特性是易于预测的，但是 不适合飞机，如战术飞机的运行条件不可预测。 为了克服这个问题，提供警告的标准被改变（30,32）作为飞行配置（16,18）的功能，以优化不同飞行条件的警告。

公开(公告)号：US5031987A

公开(公告)日：1991-07-16

申请号：US459927

申请日：1990-01-02

Applicant: Brian L. Norling

Inventor： Brian L. Norling

IPC: G01D5/26 ,  G01K5/72 ,  G02B6/35 ,  G02B6/36

CPC classification number: G02B6/3512 ,  G01D5/268 ,  G01K5/72 ,  G02B6/241 ,  G02B6/3516 ,  G02B6/3552 ,  G02B6/3574 ,  G02B6/3576

Abstract: A fiber optic transducer utilizes a single optical fiber having one end surface, disposed adjacent a sensor element, cut at an angle to result in frustrated total internal reflection. The end surface of the optical fiber is spaced away from the sensor element. As the sensor element is displaced with respect to the end surface of the optical fiber, the amount of light reflected from the sensor element varies. Light injected into the optical fiber is reflected back toward the light source until the element comes into relatively close proximity with the angled end of the optical fiber. When this occurs, a portion of the light is transmitted across the gap and absorbed by the sensor element. The ratio of the light reflected from the reflective surface to the total light input into the optical fiber produces a signal representative of the displacement of the sensor element. This signal can then be converted to a corresponding temperature or pressure signal and displayed at a remote location. The transducer is capable of being used with temperature or pressure sensitive elements to provide either an analog output signal or a digital output signal. Also disclosed is a self test circuit for the transducer.

Abstract translation: 光纤传感器利用具有一个端面的单个光纤，其设置在传感器元件附近，以一定角度切割，导致沮丧的全内反射。 光纤的端面与传感器元件间隔开。 当传感器元件相对于光纤的端面移位时，从传感器元件反射的光量变化。 注入到光纤中的光被反射回光源，直到元件与光纤的倾斜端部相对靠近。 当发生这种情况时，一部分光被透过该间隙并由传感器元件吸收。 从反射表面反射的光与输入到光纤的总光的比率产生表示传感器元件的位移的信号。 然后可以将该信号转换成相应的温​​度或压力信号并显示在远程位置。 传感器能够与温度或压敏元件一起使用，以提供模拟输出信号或数字输出信号。 还公开了用于换能器的自检电路。

公开(公告)号：US4939513A

公开(公告)日：1990-07-03

申请号：US642544

申请日：1984-08-20

Applicant: Noel S. Paterson ,  Everette E. Vermilion

Inventor： Noel S. Paterson ,  Everette E. Vermilion

IPC: G01C5/00 ,  G01P1/10

CPC classification number: G01P1/10 ,  G01C5/005

Abstract: A system that warns the pilot of an aircraft performing low level maneuvers of a dangerous flight profile monitors the altitude of the aircraft above ground, and provides a first specific warning to the pilot if the altitude of the aircraft drops below a predetermined minimum altitude above ground. The system further monitors the roll angle and descent rate of the aircraft to provide a second specific warning if the descent rate of the aircraft exceeds a predetermined rate determined by the roll angle of the aircraft if the aircraft is below a second predetermined altitude above ground.

Abstract translation: 警告飞行员飞​​行员执行危险飞行剖面低级别机动的系统会监控飞机高度的地面，并向飞行员提供第一个具体警告，如果飞机高度低于地面以上的预定最小高度 。 如果飞行器的下降速率超过由飞行器的滚动角度确定的预定速率，如果飞行器低于地面上的第二预定高度，则系统进一步监视飞机的侧倾角和下降速率，以提供第二具体警告。

公开(公告)号：US4932258A

公开(公告)日：1990-06-12

申请号：US212785

申请日：1988-06-29

Applicant: Brian L. Norling

Inventor： Brian L. Norling

IPC: G01P15/125 ,  G01P1/00 ,  G01P15/13

CPC classification number: G01P1/006 ,  G01P15/132 ,  G01P2015/0828

Abstract: A transducer having compensation for a deflection due to an applied stress. The transducer includes a support ring (32) having a proof mass (34) cantilevered on a pair of flexures (38) between the magnets (26, 28) of a stator in which the transducer is mounted. Deflection of the support ring due to an imbalanced applied force is compensated by either moving the pads (30) used to mount the support ring, moving the centroid of capacitance (42) of the proof mass, or by modifying the support ring to provide a pair of moment arms (152), each approach insuring that an axis of deflection (102, 130) of the support ring is coaligned with the centroid of capacitance, thereby minimizing a bias error in the transducer output.

Abstract translation: 具有由于施加的应力引起的偏转补偿的换能器。 换能器包括支撑环（32），该支撑环具有悬挂在定子的磁体（26,28）之间的一对挠曲件（38）上的检测质量块（34），其中安装有换能器。 通过移动用于安装支撑环的垫（30），移动检体的电容（42）的质心，或通过修改支撑环来提供由于不平衡施加力而引起的支撑环的偏转， 一对力臂（152），每个方法确保支撑环的偏转轴（102,130）与电容的质心共同对准，从而最小化换能器输出中的偏置误差。

公开(公告)号：US4912990A

公开(公告)日：1990-04-03

申请号：US315964

申请日：1989-02-27

Applicant: Brian L. Norling

Inventor： Brian L. Norling

IPC: G01L1/10 ,  G01L1/18 ,  G01P15/08 ,  G01P15/097 ,  G01P15/10

CPC classification number: G01P15/097 ,  G01L1/183 ,  G01P15/0802 ,  Y10S73/01

Abstract: A vibrating beam force transducer that can be realized in a silicon micromachined device such as a micromachined accelerometer. The transducer includes a beam having a longitudinal axis, and a drive circuit electrically coupled to the beam for causing the beam to oscillate at a resonant frequency that is a function of a force applied along the longitudinal beam axis. The drive circuit provides an electrical current to the beam, and the beam, or a conductive portion thereof, conducts the current along a path that includes an axial component parallel to the longitudinal axis. A magnetic field is created intersecting the axial component, such that the electric current interacts with the magnetic field to produce a force that causes the beam to oscillate at the resonant frequency. In a preferred embodiment, the transducer has a double ended tuning fork configuration, and the current path extends along one beam and back along the other beam.

Abstract translation: 振动梁力传感器，其可以在诸如微机械加速度计的硅微加工装置中实现。 换能器包括具有纵向轴线的光束和电耦合到光束的驱动电路，用于使光束以以沿纵向光束轴线施加的力的函数的谐振频率振荡。 驱动电路为光束提供电流，并且光束或其导电部分沿着包括平行于纵向轴线的轴向分量的路径传导电流。 产生与轴向分量相交的磁场，使得电流与磁场相互作用以产生使光束以共振频率振荡的力。 在优选实施例中，换能器具有双端音叉配置，并且电流路径沿着一个光束延伸并且沿另一个光束向后延伸。

公开(公告)号：US4891982A

公开(公告)日：1990-01-09

申请号：US205194

申请日：1988-06-10

Applicant: Brian L. Norling

Inventor： Brian L. Norling

IPC: G01P1/00 ,  G01P15/097 ,  G01P15/10

CPC classification number: G01P15/097 ,  G01P1/006

Abstract: Prior steady-state accelerometers are subject to errors caused by differential thermal expansion between the force transducers and other accelerometer components. This problem is overcome by the present accelerometer that comprises a housing (32), a proof mass (30), a support (34,36) for mounting the proof mass with respect to the housing, and first and second force sensing elements (38,40). The force sensing elements have DC frequency responses, and are connected between the proof mass and the housing such that differential thermal expansion or contraction between the force sensing elements and the proof mass, support and housing results in rotation of the proof mass about a compensation axis (CA) normal to the sensitive axis (SA). The force sensing elements may extend from their respective points of connection to the proof mass in opposite directions parallel to the sensitive axis to their respective points of connection to the housing, and the force sensing elements may be connected to the proof mass at spaced-apart positions on opposite sides of the compensation axis.

Abstract translation: 先前的稳态加速度计会受到力传感器和其他加速度计部件之间不同热膨胀的误差。 本发明的加速度计克服了这个问题，该加速度计包括壳体（32），检测质量块（30），用于相对于壳体安装证明物质的支撑件（34,36），以及第一和第二力传感元件 ，40）。 力感测元件具有直流频率响应，并且连接在检验质量体和壳体之间，使得力感测元件与检测质量块，支撑件和壳体之间的差别热膨胀或收缩导致检验质量块围绕补偿轴线的旋转 （CA）垂直于敏感轴（SA）。 力感测元件可以从它们各自的连接点延伸到与感测轴线平行的相反方向的连接到壳体的各自的连接点，并且力传感元件可以在间隔开的位置连接到检测质量块 位于补偿轴的相对侧。

公开(公告)号：US4891642A

公开(公告)日：1990-01-02

申请号：US142463

申请日：1988-01-11

Applicant: Hans R. Muller

Inventor： Hans R. Muller

IPC: G01C21/00 ,  B64D45/00 ,  G05D1/06

CPC classification number: G05D1/0615

Abstract: A wind shear detection system compares air-speed with a composite signal derived from signals representative of longitudinal acceleration, normal acceleration, angle of attack and flight path angle to generate a shear signal. An enhanced version of the system is also compensated for roll angle, radio altitude and flap position. In a modified system, the accelerations are calculated along the velocity vector of the aircraft rather than along the horizontal axis to compensate for inaccuracies that could occur under extreme flight conditions such as high bank angle turns and dynamic maneuvers.

Abstract translation: 风切变检测系统将空速与由表示纵向加速度，正常加速度，迎角和飞行路径角度的信号导出的复合信号进行比较，以产生剪切信号。 系统的增强版也可以补偿滚角，无线电高度和襟翼位置。 在改进的系统中，沿着飞行器的速度矢量而不是沿着水平轴计算加速度，以补偿在极限飞行条件下可能发生的不准确性，例如高的倾斜角度和动态的动作。

公开(公告)号：US4870588A

公开(公告)日：1989-09-26

申请号：US789658

申请日：1985-10-21

Applicant: Shmuel J. Merhav

Inventor： Shmuel J. Merhav

IPC: G01C19/56 ,  G01C19/00 ,  G01P9/00 ,  G01P9/04 ,  G01P15/08 ,  G01P15/14

CPC classification number: G01P9/00 ,  G01P15/08

Abstract: Disclosed is a method and apparatus for processing signals supplied by accelerometer assemblies in which one or more accelerometers are cyclically displaced in a predetermined manner so that signals representing the specific force experienced by the accelerometers and the angular rate experienced by the accelerometers are produced. The signal processor separately estimates the signal components of the signal being processed and provides an error signal by subtracting the estimated signal components from the signal being processed. The error signal is fed back through circuitry that controls the magnitude of the estimated signal components so that the value of each estimated signal component rapidly converges to the value of the signal components of the signal being processed. In an arrangement for determining the angular rate of one or more pair of cyclically displaced accelerometers, the signal processor includes a signal component that is in-phase with the signal that oscillates the accelerometer pair, a signal component that is in phase quadrature with the signal that displaces the accelerometer pair and a signal component that corresponds to random unmodulated additive noise. In this arrangement, a signal summing unit subtracts estimates of each signal component from the signal being processed to supply an error signal equal to (a.sub.1 -a.sub.1) Cos .omega.t+(a.sub.2 -a.sub.2) Sin .omega.t+(a.sub.3 -a.sub.3), where a.sub.1, a.sub.2, and a.sub.3, respectively represent the values of the in-phase, quadrature and random noise components of the signal being processed and a.sub.1, a.sub.2, and a.sub.3 represent estimates of those signal component values. To obtain a.sub.3, the error signal is scaled and integrated. To obtain the a.sub.1 Cos .omega.t signal estimate, the error signal is multiplied by Cos .omega.t, and scaled to obtain a signal representative of the derivative with respect to time of a.sub.1. This signal is then integrated and multiplied by Cos .omega.t. The signal component a.sub.2 Sin .omega.t is obtained in a similar manner by multiplying the error signal by Sin .omega.t, scaling, integrating and multiplying the integrated signal by Sin .omega.t. In such an arrangement, angular rate is obtained by scaling the a.sub.1 signal estimate. In addition, the signal estimates can be used in an inertial navigation system that employs the invention to eliminate misalignment of the accelerometer pairs and to improve system operation by eliminating phase shift between the signal source that oscillates the accelerometer pairs and the signals provided by the accelerometer pairs.

公开(公告)号：US4828382A

公开(公告)日：1989-05-09

申请号：US853489

申请日：1986-04-18

Applicant: Everette E. Vermilion

Inventor： Everette E. Vermilion

IPC: G01S13/46 ,  G01C5/00 ,  G01S5/12 ,  G01S13/00 ,  G01S17/46

CPC classification number: G01C5/005 ,  G01S13/003 ,  G01S5/12

Abstract: A method and apparatus is disclosed for passively determining altitude above the ground of an aircraft by use of an active emitter carried on a second higher altitude aircraft. Specifically, the altitude of the aircraft is determined by measuring the time difference between direct path radiation and reflected path radiation, taking into account the distance between an upper antenna which receives the direct path radiation and a lower antenna which receives the reflected path radiation and the angles of travel relative to the vertical between the direct path radiation and the reflected path radiation.

Abstract translation: 公开了一种通过使用在第二高空飞机上运行的有源发射器来被动地确定飞机地面高度的方法和装置。 具体地说，考虑到接收直接路径辐射的上部天线和接收反射路径辐射的下部天线之间的距离，以及通过测量直接路径辐射与反射路径辐射之间的时间差，确定飞行器的高度， 相对于直接路径辐射与反射路径辐射之间的垂直线的行进角度。