公开(公告)号：WO1988009537A1

公开(公告)日：1988-12-01

申请号：PCT/US1988001224

申请日：1988-04-18

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  GLOVER, J., Howard

IPC: G06F15/31

CPC classification number: H03H17/0263

Abstract: A fast median filter (22) is disclosed for filtering high frequency noise from signals, such as, signals (10, 14) from a radio altimeter. The filter (22) continuously provides the median of a predetermined number of points of the signal, which are received in an array, by successively comparing (60) each data point in the array with each other data point in the array. A counter is either incremented (62) or decremented (64) depending on the result of each comparison. If the counter reaches a predetermined value at the end of the sequence of comparisons, the median is determined. A pointer (30) keeps track of the oldest data point in the array (42). After the median is determined, a new data point is received into the array and written over the oldest data point (34). The median of the array is determined each time the array is updated with a new data point (32). When the pointer reaches the last position in the array, the pointer is reset to the first position and is subsequently incremented in the same manner (40).

Abstract translation: 公开了一种用于从诸如来自无线电高度计的信号（10,14）的信号过滤高频噪声的快速中值滤波器（22）。 滤波器（22）通过将阵列中的每个数据点与阵列中的每个其他数据点相连（60）连续地提供在数组中接收的信号的预定数量的点的中值。 根据每个比较的结果，计数器增加（62）或递减（64）。 如果计数器在比较序列结束时达到预定值，则确定中位数。 指针（30）跟踪阵列中最早的数据点（42）。 在确定中值后，将新的数据点接收到阵列中并写入最旧的数据点（34）。 每次使用新的数据点（32）更新数组时，确定阵列的中值。 当指针到达阵列中的最后一个位置时，指针将被重置为第一个位置，并以相同的方式递增（40）。

公开(公告)号：WO1988000351A1

公开(公告)日：1988-01-14

申请号：PCT/US1987001571

申请日：1987-06-25

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  NORLING, Brian, L.

IPC: G01P15/10

CPC classification number: G01P15/097 ,  G01P1/006 ,  G01P2015/0828

Abstract: Prior vibrating beam accelerometers are subject to errors caused by differential thermal expansion between the vibrating beams and other accelerometer components. This problem is overcome by the present accelerometer that comprises a housing (32), a proof mass (30), support means (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 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 means 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.

公开(公告)号：WO1988000348A1

公开(公告)日：1988-01-14

申请号：PCT/US1987001572

申请日：1987-06-25

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  NORLING, Brian, L. ,  TONN, Jeffrey, F.

IPC: G01P01/00

CPC classification number: G01P1/023 ,  G01D11/30

Abstract: The mounting system of the present invention is adapted to support a precision transducer (14) in spaced alignment with a supporting case (12). The mounting system comprises a plurality of mounting elements (30), each mounting element having one end (34), an opposite end (32) and a resilient intermediate portion (36). One end is adapted to be connected to the transducer, and the opposite end is adapted to be connected to the case. Adjacent mounting elements are joined to one another by bridge sections (38) to form a continuous mounting ring (16) and to define a plurality of gaps (56). At least the end connected to the transducer and bridge sections is composed of a substance that has a coefficient of thermal expansion approximately equal to the coefficient of thermal expansion of the transducer. Each intermediate portion is configured to provide a low resistance to relative movement between the transducer and case in a radial direction, and a high resistance to relative movement in other directions.

Abstract translation: 本发明的安装系统适于支撑与支撑壳体（12）间隔对准的精密换能器（14）。 安装系统包括多个安装元件（30），每个安装元件具有一端（34），相对端（32）和弹性中间部分（36）。 一端适于连接到换能器，并且相对端适于连接到壳体。 相邻的安装元件通过桥接部分（38）彼此连接以形成连续的安装环（16）并且限定多个间隙（56）。 至少连接到换能器和桥接部分的端部由具有大约等于换能器的热膨胀系数的热膨胀系数的物质组成。 每个中间部分构造成对径向方向上的换能器和壳体之间的相对运动提供低阻力，并且对其它方向的相对运动具有高阻力。

公开(公告)号：WO1987006351A1

公开(公告)日：1987-10-22

申请号：PCT/US1987000872

申请日：1987-04-15

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  NORLING, Brian, L.

IPC: G01P15/13

CPC classification number: G01P15/132

Abstract: An accelerometer comprising a proof mass assembly that includes a reed (26) suspended from a support (22) and a cylindrical coil mounted to the reed by a mounting system that minimizes errors due to thermal stress. The mounting system comprises at least three mounting elements. Each mounting element (114) has first and second ends, and a resilient intermediate portion. The first end of each mounting element connected to the coil (78), the second end of each mounting element is connected to the reed (72) and the intermediate portion of each mounting element provides a low resistance to relative movement between the coil and reed in a radial direction, and a high resistance to relative movement between the coil and reed in directions normal to the radial direction. The reed preferably comprises fused quartz, and the mounting system preferably comprises a fused quartz base (106) mounted directly to the reed and connected to the second end of each mounting element. The coil may be mounted on a coil form that is connected directly to the first end of each mounting element.

公开(公告)号：WO1987004582A1

公开(公告)日：1987-07-30

申请号：PCT/US1987000090

申请日：1987-01-14

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  KIRSCHNER, Robert, K. ,  MULLER, Hans, R.

IPC: H04N07/18

CPC classification number: G02B27/0101 ,  B60K2350/1064 ,  B60K2350/2052 ,  B60K2350/405 ,  G02B2027/0154 ,  G02B2027/0156 ,  G02B2027/0165 ,  G02B2027/0169

Abstract: An independant test sight (18) for a pilot's head-up display (HUD). In one embodiment, the independent test sight comprises a collimator assembly (36) and an aligned periscope assembly (38). The collimator assembly comprises a source of light (42), a reticle (46), and a lens (48) for projecting the image of the reticle. The periscope assembly comprises a rhomboid prism (56) housed within the chassis (22) of the HUD (12) in such a manner that it can be pivoted from a stowed position to an erect position where it projects a reticle pattern in the field of view of the HUD combiner.

公开(公告)号：WO1987004241A1

公开(公告)日：1987-07-16

申请号：PCT/US1986002765

申请日：1986-12-19

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  PAROS, Jerome, M. ,  TONN, Jeffrey, Forrest ,  WEARN, Richard, R.

IPC: G01K11/22

CPC classification number: G01K7/32

Abstract: Prior mounting systems for tuning fork temperature sensors have resulted in unpredictable activity dips within the sensor operating ranges. This problem is eliminated by the mounting and isolation system (32) of the present invention that is adapted to mount temperature sensitive tuning fork (20) to a support structure. The mounting system comprises a mounting member (34) adapted for rigid connection to the support structure, and support means (36) connecting the tuning fork base to the mounting member such that the tuning fork is supported solely by the support means. The support means comprises a low pass mechanical filter that transmits only vibration frequencies that are less than the operating range of frequencies of the tuning fork.

公开(公告)号：WO1986005889A1

公开(公告)日：1986-10-09

申请号：PCT/US1986000678

申请日：1986-04-02

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  CHISHOLM, John, P.

IPC: G01S01/16

CPC classification number: G01S1/10 ,  G01S1/56

Abstract: 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 (31, 32 and 33, 34), sequentially radiated by different fixed antennas (80, 81 and 89, 90). One pair (31, 32) is oriented to left and right of the centerline (36) of the runway, and the other pair (89, 90) is oriented above and below the desired glideslope (36'). The first set of paired beams overlap at the centerline (36) of the runway in such a manner that an aircraft approaching exactly on centerline (36) will intercept equal signal intensities to indicate and on-course approach. Conversely when the aircraft is off-course to one side of the centerline (35), it will intercept a stronger signal intensity for the fixed guidance beam (31) which is directed to that side of the centerline and a weaker signal intensity for the fixed beam (32) which is directed to the other side of the centerline. Similar operation is provided by the overlapped guidance beams (33, 34) operating in the elevation mode.

Abstract translation: 独立的指导和监测将整合到一个MLS着陆系统中，并提供了一个可在小型机场使用的按比例缩小的MLS着陆指导系统。 在这两种情况下，添加的固定光束精度指导系统集成到MLS时序格式中。 固定光束引导系统基于使用由不同固定天线（80,81和89,90）顺序辐射的成对固定重叠光束（31,32和33,34）的概念。 一对（31,32）朝向跑道中心线（36）的左侧和右侧，另一对（89,90）定向在所需滑翔伞（36'）上方和下方。 第一组配对梁在跑道的中心线（36）处重叠，使得正好接近中心线（36）的飞行器将截取相等的信号强度以指示和在路线上接近。 相反，如果飞行器偏离中心线（35）的一侧，则它将截取针对固定引导梁（31）的更强的信号强度，该固定引导梁（31）指向中心线的那一侧，并且固定的信号强度较弱 梁（32），其被引导到中心线的另一侧。 通过以仰角模式操作的重叠引导梁（33,34）提供类似的操作。

公开(公告)号：WO1986005023A1

公开(公告)日：1986-08-28

申请号：PCT/US1986000384

申请日：1986-02-21

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  GROVE, Michael, M.

IPC: G08B23/00

CPC classification number: G01C5/005

Abstract: Aircraft ground proximity warning systems that provide the pilot with a warning in the event that the closure rate with terrain is too high have the problem that when such systems are used in aircraft that are intentionally flown at high descent rates, such as occur in dives, nuisance warnings can occur. In order to minimize the problem, the criteria necessary to generate a terrain closure warning are modified as a function of the descent rate of the aircraft (14) to prevent the closure rates encountered as a result of high descent rates from generating nuisance warnings. Closure rate warnings are given based on radio altitude (16), radio and barometric altitude rates (26, 14), airspeed (17), flap and landing gear position (18, 20), mission mode (21) and weight on wheels (22) signal inputs.

Abstract translation: 飞机地面接近警报系统，如果地面闭合率过高，飞行员可以向飞行员提供警告，那么当这种系统用于有意以高下降率飞行的飞机（例如在潜水中发生）时， 可能会发生滋扰警告。 为了最小化问题，产生地形关闭警告所必需的标准被修改为飞行器（14）的下降率的函数，以防止由于高下降率而产生的妨碍警告的闭合速率。 关闭率警告基于无线电高度（16），无线电和大气高度（26,14），空速（17），挡板和起落架位置（18,20），任务模式（21）和车轮重量 22）信号输入。

公开(公告)号：WO1986005022A1

公开(公告)日：1986-08-28

申请号：PCT/US1986000383

申请日：1986-02-21

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  GROVE, Michael, M.

IPC: G08B23/00

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。 这个问题是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的（12，14，30，32， 34）。 如果起飞后的累计时间高度产物的高度损失过高，则会产生警告（38,40）。 因此，系统在起飞后立即更为敏感，随着飞行时间的积累而变得不太敏感，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。

公开(公告)号：WO1986005021A1

公开(公告)日：1986-08-28

申请号：PCT/US1986000382

申请日：1986-02-21

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  GROVE, Michael, M.

IPC: G08B23/00

CPC classification number: G01C5/005

Abstract: A proximity to terrain warning system for aircraft utilizes a first warning envelope (Fig. 3) to generate a warning in the event of insufficient terrain clearance after take off. A different warning envelope (Fig. 4) is employed to generate warnings when the aircraft is in a cruise or approach phase of flight or on a tactical mission. Mode switching (122, 124, 126) is provided to select an excessive descent after take-off warning envelope (Fig. 7) in addition to the first warning envelope (Fig. 3) when appropriate. Warnings are based on take-off power (38), airspeed (12), gear position (85), time delay (94, 146, 150) and time-altitude signals.

Abstract translation: 靠近飞机地形预警系统使用第一个警告信号（图3），在起飞后地形清除不足的情况下产生警告。 当飞机处于巡航或接近飞行阶段或战术任务时，使用不同的警告信号（图4）来产生警告。 提供模式切换（122,124,126）以在适当的时候除了第一个警告信号（图3）之外的起飞警告信号（图7）之后选择过大的下降。 报警基于起飞功率（38），空速（12），档位（85），时间延迟（94,146,150）和时间 - 高度信号。