公开(公告)号：US3715718A

公开(公告)日：1973-02-06

申请号：US3715718D

申请日：1970-08-11

Applicant: SUNDSTRAND DATA CONTROL

Inventor： ASTENGO R

IPC: G01P1/10 ,  G01P3/62 ,  G01S13/10 ,  G05D1/06 ,  G01C5/00

CPC classification number: G01P3/62 ,  G01P1/103 ,  G01S13/10 ,  G05D1/0607

Abstract: A ground proximity warning system for an aircraft which produces a warning signal when the rate of descent of the aircraft exceeds a limiting value determined by the aircraft altitude. The rate of descent of the aircraft is calculated from a combination of measurements of the altitude of the aircraft above ground and the barometric altitude of the aircraft. A signal representing the rate of change of the altitude of the aircraft above ground is limited, to minimize false warnings as a result of surface irregularities. The barometric portion of the system is disabled during take-off run and the initial portion of the aircraft climb-out to avoid a false warning resulting from an increased barometric pressure condition during this maneuver. The limits on the aircraft altitude rate signal are modified in accordance with the flight mode of the aircraft, to reduce the sensitivity of the warning system during the final stage of a landing approach. The warning system provides an alarm to the pilot which is an audio tone modulated at a low frequency repetition rate. A soft warning is actuated when the sink rate of the aircraft exceeds a desired level for the altitude at which the aircraft is operating. If the aircraft is also below a limiting altitude, a hard warn signal is provided. The repetition rate of the warning signal, while in a soft warn condition, is a function of the difference between the altitude of the aircraft and the altitude at which the sink rate would be proper. A complementary filter with which the altitude rate signals are combined, includes an operational amplifier connected in an unloading amplifier configuration with a resistive circuit connecting one input signal with the amplifier and a capacitive circuit connecting the other input signal with the amplifier, the resistive and capacitive input circuits forming a low pass filter for the first signal and a high pass filter for the second signal.

公开(公告)号：US3636321A

公开(公告)日：1972-01-18

申请号：US3636321D

申请日：1969-12-10

Applicant: SUNDSTRAND DATA CONTROL

Inventor： KIRSCHNER ROBERT K

IPC: B64D45/00 ,  G06G7/28 ,  G06G7/26 ,  G06G7/78

CPC classification number: G06G7/28

Abstract: An analog position transducer connected to an aircraft flap generates a linear voltage representing flap position. Separate switching stages are responsive to different potential levels of the linear voltage to produce separate output waveforms which are summed by an operational amplifier for each reference program which is to be generated. The disclosed reference programs correlate desired angle of attack to flap position for an aircraft approach program and a climbout program.

公开(公告)号：US5285686A

公开(公告)日：1994-02-15

申请号：US62281

申请日：1993-05-17

Applicant: Rex B. Peters

Inventor： Rex B. Peters

IPC: G01C19/56 ,  G01P9/04

CPC classification number: G01C19/5607

Abstract: A rate detection system (10) uses a balanced resonant sensor (12) having first and second tines (14,16) interconnected with a mounting pad (20). A sensing circuit (50) including a tunnel effect displacement sensor (38) having a first probe (40) connected to the mounting pad (20) and a second probe (42) connected to a reference pad (32) detects an output signal having a Coriolis component. A feedback circuit provides a compensation signal to the balanced resonant sensor (12).

Abstract translation: 速率检测系统（10）使用具有与安装垫（20）互连的第一和第二齿（14,16）的平衡谐振传感器（12）。 一种感测电路（50），包括具有连接到安装垫（20）的第一探头（40）和连接到参考焊盘（32）的第二探头（42）的隧道效应位移传感器（38），检测输出信号， 科里奥利组件。 反馈电路向平衡谐振传感器（12）提供补偿信号。

公开(公告)号：US5136518A

公开(公告)日：1992-08-04

申请号：US505214

申请日：1990-04-04

Applicant: J. Howard Glover

Inventor： J. Howard Glover

IPC: G01P5/00 ,  B64D43/02 ,  B64D45/00 ,  G05D1/06 ,  G05D1/10

CPC classification number: G05D1/0623

Abstract: 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 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 and vertical speed to optimize the pitch angle for different altitudes and descent rates.

Abstract translation: 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。 该系统利用俯仰参考调制器，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，以减少在劣化的性能条件（例如尾风和发动机 - 出来的条件。 该系统利用惯性导出的俯仰信息，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和垂直速度的函数被偏置，以优化不同高度的俯仰角 和下降率。

公开(公告)号：US5095264A

公开(公告)日：1992-03-10

申请号：US581726

申请日：1990-09-12

Applicant: Rand H. Hulsing, II

Inventor： Rand H. Hulsing, II

IPC: G01P3/489 ,  G01R23/10

CPC classification number: G01R23/10

Abstract: A dual-edge frequency counter and method for minimizing the effects of duty cycle modulation. In its simplest form, a dual-edge counter (50) includes a first counter (52) that accumulates reference clock pulses between successive rising edges of an input signal. An input signal is also applied to an inverter (54), which inverts the square wave signal prior to applying it to a second counter (56) that also accumulates reference clock cycles between successive rising edges of the inverted sensor signal. A summation junction (60) totals the accumulated counts from the first and second counters so that they can be averaged by a divider (62), which divides the total count by two. The technique is also employed in connection with a frequency counter that includes an integer counter (72) for totaling the number of cycles of the sensor signal occurring during a sample time defined by successive gate signals. The integer count, N, is then corrected for the compensated average of partial periods of the signal occurring at the beginning and the end of the sample time. The compensated average partial period corrects for variations in the sensor signal duty cycle caused either by noise superimposed on a sinusoidal signal produced by a quartz crystal (12) or as a result of variations in power supply level for the crystal oscillator.

Abstract translation: 一种用于最小化占空比调制效应的双边频率计数器和方法。 在最简单的形式中，双边缘计数器（50）包括在输入信号的连续上升沿之间累积参考时钟脉冲的第一计数器（52）。 输入信号也被施加到反相器（54），该反相器将方波信号在将其施加到也在反相的传感器信号的连续上升沿之间积累参考时钟周期的第二计数器（56）之前将其转换。 求和结（60）总计从第一和第二计数器的累积计数，使得它们可以通过将总计数除以2的分频器（62）来进行平均。 该技术还与包括整数计数器（72）的频率计数器一起使用，该整数计数器用于总计在由连续的门信号定义的采样时间期间发生的传感器信号的周期数。 然后对采样时间开始和结束时出现的信号的部分周期的补偿平均值校正整数计数N。 补偿的平均部分周期校正由于叠加在由石英晶体（12）产生的正弦信号上的噪声或由于晶体振荡器的电源电平变化而导致的传感器信号占空比的变化。

公开(公告)号：US5066911A

公开(公告)日：1991-11-19

申请号：US335141

申请日：1989-04-07

Applicant: Rand H. Hulsing, II.

Inventor： Rand H. Hulsing, II.

IPC: G01B7/00 ,  G01B7/14 ,  G01D5/22

CPC classification number: G01D5/2291 ,  G01B7/14 ,  G01D5/2216

Abstract: A transformer and method for sensing displacement, A linear variable displacement transformer (LVDT) 50, 100, 150, 200, and 250) is disclosed with respect to several embodiment,s each including a core (52, 102, 152, 202, and 252) having a primary leg (56, 104, 154, 204, and 254), and two secondary legs (58 and 60, 106 and 108, 158 and 160, 206 and 208, and 258 and 260). A primary coil (54, 110, 156, 210, and 264) is disposed on the primary leg, and secondary coils (62 and 64, 112 and 114, 162 and 164, 212 and 214, and 266 and 268) are disposed on the secondary legs. Pole pieces (70 and 72, 120 and 122, 170 and 172, 222 and 224, and 274 and 276) are disposed in gaps between the primary leg and each secondary leg, so that they control the reluctance to a magnetic flux produced by an electric current flowing thorugh the primary coil. Displacement of the two pole pieces within the gaps separating facing surfaces of the primary and secondary legs changes the proportion of the magnetic flux through each of the secondary legs and thus varies an electrical signal induced in each of the secondary coils. A differential between the electrical signals thus corresponds to the differential displacement of the pole pieces in each of the embodiments.

Abstract translation: 公开了一种用于感测位移的变压器和方法，线性可变位移变压器（LVDT）50,100,150,200和250），其中每个实施例包括芯（52,102,152,202和250） 具有主支腿（56,104,154,204和254）和两个辅助支脚（58和60,106和108,158,160,206和208以及258和260）。 初级线圈（54,110,156,210和264）设置在主腿上，次级线圈（62和64,112和114,162和164,212和214和266和268）设置在 次要腿。 极靴（70和72,120和122,170和172,222和224和274和276）设置在主腿和每个次腿之间的间隙中，使得它们控制对由 电流流过初级线圈。 在两个极片之间的位移在分离初级和次级腿的相对表面的间隙内改变磁通量通过每个次级腿的比例，从而改变在每个次级线圈中感应的电信号。 因此，电信号之间的差异对应于每个实施例中的极片的差异位移。

公开(公告)号：US5059964A

公开(公告)日：1991-10-22

申请号：US444513

申请日：1989-12-01

Applicant: Charles D. Bateman

Inventor： Charles D. Bateman

IPC: G05D1/06

CPC classification number: G05D1/0615

Abstract: An instrument (10) is disclosed for an aircraft having a windshear warning system to vary the threshold alarm setting as a function of a thermodynamic property of the air and as a function of local geographic and seasonal conditions. Specifically, a function generator 16 and other circuitry is disclosed. The output from the function generator 16 and other circuitry is then added to a fixed threshold acceleraton signal to produce a threshold alarm signal which has a value that is a function of the temperature of the air, in a basic embodiment.

Abstract translation: 公开了一种具有风切变警报系统的飞机的仪器（10），以根据空气的热力学性质和作为当地地理和季节条件的函数改变阈值报警设置。 具体地，公开了功能发生器16和其它电路。 然后，在基本实施例中，来自功能发生器16和其它电路的输出被加到固定的阈值加速度信号上以产生具有作为空气温度的函数的值的阈值报警信号。

公开(公告)号：US5043690A

公开(公告)日：1991-08-27

申请号：US553213

申请日：1990-07-12

Applicant: Karl H. Wahls

Inventor： Karl H. Wahls

IPC: H01H37/54

CPC classification number: H01H37/54

Abstract: A thermal actuator utilizes a bimetallic snap action member such as a disc to actuate a member such as the armature of a switch to effect opening and closing of the switch. A resilient biasing member, such as an elongated curved spring member or a compressible member, engages the bimetallic member on a side opposite that of the actuated member to oppose the force exerted by the actuated member during the operation of the actuator.

Abstract translation: 热致动器利用诸如盘的双金属快动元件来致动诸如开关的电枢的元件以实现开关的打开和关闭。 诸如细长弯曲弹簧构件或可压缩构件的弹性偏压构件在与致动构件相对的一侧上接合双金属构件，以在致动器的操作期间与由致动构件施加的力相对。

公开(公告)号：US4990921A

公开(公告)日：1991-02-05

申请号：US45911

申请日：1987-05-01

Applicant: John P. Chisholm

Inventor： John P. Chisholm

IPC: G01S1/14 ,  G01S3/30 ,  G01S13/42 ,  G01S13/48 ,  G01S13/76 ,  G01S13/91

CPC classification number: G01S3/30 ,  G01S13/42 ,  G01S13/913

Abstract: A guidance system for landing an aircraft is described which uses a source of signals identifiable with the aircraft and a ground station which is linked to the aircraft. Specifically, the ground station includes a receiver which is connected to one or more pairs of antennas having a fixed, overlapping, directional sensitive pattern symmetically located relative to the center of the landing path, a receiver and a processor for measuring the relative sensitivity of the signals received at the antennas and for using the relative signal intensity to determine the location of the aircraft relative to the center of the landing path.

Abstract translation: 描述了用于着陆飞机的引导系统，其使用与飞行器可识别的信号源和与飞机相连的地面站。 具体地说，地面站包括连接到一对或多对天线的接收机，该对天线具有相对于着陆路径的中心对称定位的固定的，重叠的，方向敏感的模式，接收机和处理器，用于测量 在天线处接收的信号并且使用相对信号强度来确定飞行器相对于着陆路径中心的位置。

公开(公告)号：USRE33401E

公开(公告)日：1990-10-23

申请号：US286721

申请日：1988-12-19

Applicant: John P. Chisholm

Inventor： John P. Chisholm

IPC: G01S1/10 ,  G01S1/56

CPC classification number: G01S1/56 ,  G01S1/10

Abstract: The invention provides independent guidance and monitoring to be integrated into an MLS landing system and also provides a scaled-down MLS landing guidance system useable at small airports. In both cases an added fixed beam precision guidance system is integrated into the MLS time sequence format. The fixed beam guidance system is based upon the concept of using paired fixed overlapping beams, sequentially radiated by different fixed antennas. One pair is oriented to left and right of the centerline of the runway, and the other pair is oriented above and below the desired glideslope. The first set of paired beams overlap at the centerline of the runway in such a manner that an aircraft approaching exactly on centerline will intercept equal signal intensities to indicate an on-course approach. Conversely when the aircraft is off-course to one side of the centerline, it will intercept a stronger signal intensity for the fixed guidance beam which is directed to that side of the centerline and a weaker signal intensity for the fixed beam which is directed to the other side of the centerline. Similar operation is provided by the overlapped guidance beams operating in the elevation mode.