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公开(公告)号：US3947809A
公开(公告)日：1976-03-30
申请号：US540476
申请日：1975-01-22
Applicant: Charles Donald Bateman
Inventor： Charles Donald Bateman
Abstract: For use in an aircraft warning system which measures the descent below a radio glideslope and compares it with the aircraft's altitude above ground to generate a warning when the descent below glideslope exceeds predefined limits for a particular altitude, circuitry is provided to generate an advisory warning above a predefined altitude and a hard warning, or command to take immediate action, below the predetermined altitude.
Abstract translation: 用于测量无线电滑翔机下方下降的飞机警告系统，并将其与飞机在地面以上的高度进行比较，以在下滑道下降超过特定高度的预定限制时产生警告，提供电路以产生上述咨询警告 在预定高度以下的预定高度和硬警告或立即采取行动的命令。
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公开(公告)号：US3947808A
公开(公告)日：1976-03-30
申请号：US540475
申请日：1975-01-22
Applicant: Charles Donald Bateman
Inventor： Charles Donald Bateman
CPC classification number: G01C5/005 , G05D1/0607
Abstract: In a system that compares the rate of descent of an aircraft with its altitude above ground and generates a warning signal when the sink rate exceeds a predetermined limit for a particular altitude, the maximum warning time is limited to a specified value in order to minimize nuisance warnings at higher altitudes. At a descent rate above a certain value, the excessive sink rate warning signal is inhibited for combinations of descent rates and aircraft altitudes which would provide a warning greater than a selected time to impact, such as 30 seconds.
Abstract translation: 在比较飞机的下降速度及其高度高于地面的系统中，当汇率超过特定高度的预定限度时，会产生警告信号，最大警告时间被限制在规定值以便最小化滋扰 在高海拔地区发出警告。 在下降速率高于某一值的情况下，下降速率和飞机高度的组合可以抑制过大的下沉速率警告信号，这将提供大于所选时间的警告，例如30秒。
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43.发明授权Terrain closure warning system with climb inhibit and altitude gain measurement 失效地形闭合预警系统，具有爬升抑制和高度增益测量
公开(公告)号：US3934222A
公开(公告)日：1976-01-20
申请号：US564512
申请日：1975-04-02
Applicant: Charles Donald Bateman , Hans Rudolf Muller , Frank Joseph Brem
Inventor： Charles Donald Bateman , Hans Rudolf Muller , Frank Joseph Brem
IPC: B64D45/04 , G01C5/00 , G01C5/06 , G01C21/00 , G01C21/20 , G01L7/12 , G01S19/14 , G05D1/04 , G08G5/02
CPC classification number: G01C5/005 , G05D1/0607
Abstract: In a terrain warning system wherein the rate of the aircraft's closure to the terrain is compared to the aircraft's altitude above the terrain in order to generate a warning signal for excessive closure rates, a circuit is provided to inhibit the warning signal when the aircraft begins to climb in response to the warning signal and to measure the altitude gained by the aircraft resulting in the reactivation of the warning signal if the aircraft has leveled off before gaining a predetermined amount of altitude. The circuit includes: a memory element to indicate that a warning signal has been generated; a circuit to generate a climb signal in response to a barometric rate of change signal indicating the aircraft is climbing; and an integrating circuit responsive to the barometric rate signal to determine the amount of altitude the aircraft has gained while climbing. If the aircraft has not gained the predetermined amount of altitude before leveling off, as indicated by the climb signal, the memory element will reactivate the warning signal.
Abstract translation: 在地形警告系统中，其中将飞机关闭到地形的速率与飞机在地形上方的高度进行比较，以便产生用于过度关闭速率的警告信号，提供电路以在飞行器开始时抑制警告信号 在响应警告信号的情况下爬升并测量飞机获得的高度，导致如果飞机在获得预定量的高度之前已经平整，则重新激活警告信号。 电路包括：用于指示已经产生警告信号的存储元件; 响应于指示飞机的气压变化信号而产生爬升信号的电路正在攀爬; 以及响应于气压信号的积分电路，以确定飞机在爬升时获得的高度。 如果飞机在平整之前没有获得预定的高度，如爬升信号所示，则存储元件将重新激活警告信号。
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公开(公告)号：US3925751A
公开(公告)日：1975-12-09
申请号：US56450575
申请日：1975-04-02
Applicant: SUNDSTRAND DATA CONTROL
Inventor： BATEMAN CHARLES DONALD , MULLER HANS RUDOLF
CPC classification number: G05D1/0607 , G01C5/005 , G01S1/02
Abstract: In a system where the aircraft''s distance below a radio glide slope is compared with the aircraft''s altitude above ground to generate either an advisory voice warning or a command voice warning depending upon the aircraft''s altitude and distance below the radial glide slope beam, the repetition rate of the advisory voice warning is varied as both a function of distance below the radio glide slope beam and of altitude in order to generate advisory warnings at a rate reflecting increasing danger to the aircraft. This is accomplished by integrating the glide slope deviation signal over time and comparing it with a radio altitude signal so as to generate a signal for triggering the advisory warning as a function of the glide slope deviation and the radio altitude thereby generating the advisory warnings as a function of decreasing radio altitude and increasing deviation from the glide slope.
Abstract translation: 在将飞机距无线电滑翔坡下方的距离与飞机高于地面高度进行比较的系统中，根据飞机的高度和径向滑翔坡度波束的距离，产生咨询语音警告或指挥声音警告，系统的重复率 咨询语音警告随着无线电滑翔坡的距离和高度的作用而变化，以便以反映对飞机的危险增加的速度产生咨询警告。 这是通过随着时间的推移积分滑翔坡偏差信号并将其与无线电高度信号进行比较来实现的，以便产生用于触发作为滑坡斜率偏差和无线电高度的函数的咨询警告的信号，由此产生咨询警告作为 降低无线电高度并增加偏离滑坡的功能。
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公开(公告)号：US3851303A
公开(公告)日：1974-11-26
申请号：US30772672
申请日：1972-11-17
Applicant: SUNDSTRAND DATA CONTROL
Inventor： MULLER H
CPC classification number: G05D1/0676 , G01C9/005 , G02B27/01 , G02B2027/0154 , G02B2027/0156
Abstract: A collimated head up display of pitch related information for an aircraft operator. A generated pitch signal combines a gyroscope signal referenced to the airframe with an inertial signal referenced to the head up display or combiner screen. A pitch error signal representing the difference between the generated pitch signal and the inertial pitch signal is limited and integrated to develop a pitch correction signal which is added to the gyroscope signal. Reference of the inertial signal to the combiner screen of the display eliminates static alignment errors. The pitch correction signal may be selected for display during alignment of the combiner screen.
Abstract translation: 航空器操作员的俯仰相关信息的准直展示。 产生的音调信号将参考机身的陀螺仪信号与参考头部显示或组合屏幕的惯性信号相结合。 代表产生的音调信号和惯性音调信号之间的差的音调误差信号被限制并积分，以产生加到陀螺仪信号的音调校正信号。 将惯性信号引用到显示器的组合屏幕可以消除静态对准误差。 可以选择音调校正信号以在组合器屏幕的对准期间显示。
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Patent Agency Ranking
公开(公告)号：US3816005A
公开(公告)日：1974-06-11
申请号：US27198372
申请日：1972-07-14
Applicant: SUNDSTRAND DATA CONTROL
Inventor： KIRSCHNER ROBERT K
CPC classification number: G05D1/0676 , B60K2350/2052 , G01S1/02 , G02B27/01 , G02B27/0101 , G02B27/0149 , G02B2027/0154 , G02B2027/0156 , G02B2027/0169
Abstract: An apparatus for displaying collimated images including an ellipsoidal mirror having a focal surface and means for generating a bar and scale image for the mirror in the focal surface. The means generating a scale image includes an elongated strip of film or tape containing indicia which is positioned intermediate an elongated light source and the mirror to display a scale image on the mirror, and the means generating the bar image includes a transverse bar which reflectively defines a bar image on the mirror intersecting the scale image. The generating means includes means for moving the tape strip to modify the scale image and means for moving the bar to displace the bar image on the mirror and modify the position of intersection between the bar and scale images.
Abstract translation: 一种用于显示准直图像的装置，包括具有焦点面的椭圆面镜和用于产生焦点表面中的镜的条形和刻度图像的装置。 产生刻度图像的装置包括细长条带的胶片或带状标记，该标记位于细长光源和反射镜之间，以在镜子上显示刻度图像，并且产生条形图像的装置包括横向条， 镜子上的条形图像与刻度图像相交。 生成装置包括用于移动带条以修改标尺图像的装置和用于移动条以移动反射镜上的条形图像的装置，并且修改条和标尺图像之间的交叉点的位置。
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公开(公告)号：US3801838A
公开(公告)日：1974-04-02
申请号：US3801838D
申请日：1972-05-19
Applicant: SUNDSTRAND DATA CONTROL
Inventor： KISTLER W
Abstract: A piezoelectric pressure transducer particularly adapted for measuring fluid pressure up to and above ballistics levels of the order of 75,000 pounds per square inch with an accurate, linear response over a wide pressure range. The piezoelectric sensing element is housed in a cylindrical sleeve which is threaded into a wall of the chamber within which the pressure to be measured is developed. An end wall extending across the end of the sleeve is exposed to the pressure and deflects, compressing the piezoelectric element to generate an electric signal representing the pressure. A supporting wall for the end wall is located between the sensing element and the housing sleeve. Two flexure zones are formed in the end wall, one between the piezoelectric element and the supporting wall and the other between the wall and the sleeve. The supporting wall is connected with the end wall through a third flexure zone. The compliance of the supporting wall is less than the compliance of the piezoelectric element but greater than the compliance of the housing sleeve. Deformation of the housing sleeve, as by pressure on the mounting threads, is accommodated by the flexure areas and error creating stress on the piezoelectric element is minimized.
Abstract translation: 一种压电式压力传感器，特别适用于在宽的压力范围内具有高达75,000磅/平方英寸量级的流体压力，并具有准确的线性响应。 压电感测元件容纳在圆柱形套筒中，该圆柱形套筒拧入腔室的壁中，待测量的压力在该壁内形成。 延伸穿过套筒端部的端壁暴露于压力并偏转，压缩压电元件以产生表示压力的电信号。 用于端壁的支撑壁位于感测元件和壳体套筒之间。 在端壁中形成两个弯曲区域，一个位于压电元件和支撑壁之间，另一个位于壁与套筒之间。 支撑壁通过第三弯曲区域与端壁连接。 支撑壁的顺应性小于压电元件的顺应性，但大于壳体套筒的顺应性。 通过弯曲区域容纳壳体套筒的变形，如通过安装螺纹上的压力而使压电元件上产生应力的误差最小化。
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公开(公告)号：US3678746A
公开(公告)日：1972-07-25
申请号：US3678746D
申请日：1970-06-10
Applicant: SUNDSTRAND DATA CONTROL
Inventor： COREY VICTOR B
CPC classification number: G01F1/203 , G01P5/005 , Y10T137/2202
Abstract: A method and apparatus for determining the velocity of a fluid flow stream. A fluid jet source is disposed opposite a pair of fluid pressure detectors so that the jet stream equally intersects both detectors when the velocity of the fluid flow stream is zero. Means are provided for relatively laterally displacing the jet with respect to the detectors, and for sensing the pressure difference at the detectors, in order to indicate the velocity of the moving fluid flow stream.
Abstract translation: 一种用于确定流体流动流速度的方法和装置。 流体喷射源与一对流体压力检测器相对设置，使得当流体流动流的速度为零时，喷射流与两个检测器相等。 提供了用于相对于检测器相对地横向移位射流的装置，并且用于感测检测器处的压力差，以便指示运动流体流动流的速度。
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公开(公告)号：US3630169A
公开(公告)日：1971-12-28
申请号：US3630169D
申请日：1970-06-01
Applicant: SUNDSTRAND DATA CONTROL
Inventor： COREY VICTOR B
CPC classification number: B64D43/02
Abstract: A stall warning indicator having no moving parts is mounted on a leading edge of an aircraft wing, near the point of stagnation of airflow when a stall condition occurs. The indicator includes a transmitter emitting transmissions, as a continuous acoustic wave or a jet airstream, which are received by a pair of detectors connected to a differential sensor. When the stagnation point passes the axis of the transmissions, the differential sensor produces a signal to warn of an impending stall.
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50.发明授权
公开(公告)号：US5283574A
公开(公告)日：1994-02-01
申请号：US81562
申请日：1987-07-31
Applicant: Michael M. Grove
Inventor： Michael M. Grove
CPC classification number: G01C5/005
Abstract: Warning systems for aircraft that provide a warning to the pilot of an excessive altitude loss or an excessive descent rate after take-off as long as he is flying below a predetermined altitude have the problem that they require a valid radio altitude signal for proper operation, and tend to generate nuisance warnings when used in low flying aircraft. This problem is solved by comparing the accumulated altitude loss after take-off (12, 14, 62, 34) with the product of a barometrically derived altitude and the length of time the aircraft has been flying (12, 14, 30, 32, 34). A warning is generated if the altitude loss is excessive for the accumulated time-altitude product after take-off (38, 40). Thus, the system is more sensitive immediately after take-off and becomes less sensitive as flight time is accumulated to permit low level maneuvering without generating false or nuisance warnings, and does not require a valid radio altitude signal to generate a warning.
Abstract translation: 只要飞行低于预定高度，对飞行员提供过高的海拔高度损失或过高下降速度的飞行员的警告系统具有需要有效的无线电高度信号进行正常操作的问题， 并且在低飞行飞机上使用时会产生滋扰警告。 通过比较起飞后的累积高度损失（12,14，62,34）与气压导出高度的乘积和飞机飞行时间的长短来解决这个问题（12，14，30，32， 34）。 如果起飞后的累计时间高度产品的高度损失过高，则会产生警告（38,40）。 因此，系统在起飞后立即更加敏感，随着飞行时间的累积而变得不太敏感，从而允许低水平机动，而不会产生假或警告警告，并且不需要有效的无线电高度信号来产生警告。
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