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。

公开(公告)号：WO1986003842A1

公开(公告)日：1986-07-03

申请号：PCT/US1985002470

申请日：1985-12-12

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  KIRKPATRICK, Gordon, S.

IPC: G01P15/10

CPC classification number: G01P15/097 ,  G01P2015/0828

Abstract: The elimination of activity dips in the output of vibrating beam accelerometers has often required an adjustment of parameters in conflict with other design criteria. This problem is overcome by the present accelerometer that comprises a pendulum (48) and a force transducer. The pendulum has first (49) and second (52) ends and a first axis (P) extending between the first and second ends. The pendulum is hingedly connected at its first end to a support (50) along a second axis (F) perpendicular to the first axis. The force transducer comprises an oscillator and a dual beam force sensing element (53) connected between the second end of the pendulum and the support. The point of connection of the force sensing element to the pendulum lies along the first axis. The force transducer is adapted for vibration over a predetermined operating range (44) of beam vibration frequencies. The second end of the pendulum is formed so as to cause the frequencies of pendulum vibration modes to lie outside the operating range, preferably by controlling the mass of the pendulum at the outer edges of the second end so as to cause the normal mode frequency of twisting vibration of the pendulum about the first axis to lie outside the operating range. In another aspect, the pendulum has a width dimension parallel to the second axis, and the width of the pendulum decreases from a point intermediate the ends of the pendulum to the second end.

公开(公告)号：WO1986000416A1

公开(公告)日：1986-01-16

申请号：PCT/US1985001143

申请日：1985-06-17

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  STEINKE, Kurt, E.

IPC: G01P15/13

CPC classification number: G01P15/132

Abstract: A servoed accelerometer (10) is connected with an accumulator (21) to provide a binary digital output. The accumulator output is connected with a digital-to-analog converter (25) which provided an analog rebalance signal to the accelerometer.

公开(公告)号：WO1986000143A1

公开(公告)日：1986-01-03

申请号：PCT/US1985001021

申请日：1985-06-10

Applicant: SUNDSTRAND DATA CONTROL, INC.

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

IPC: G01P15/02

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

Abstract: Thermally induced stress between a quartz proof mass (204) and the metal stators (200, 202) which constrain it are relieved by a suspension system employing pliant members. Contact points between the proof mass (110) and the stators (80) are formed by raised pads (224, 226) of the proof mass (204) which contact beams (220, 222) formed in the stators. Each beam (220, 222) has an axis of pliancy, which axis extends through a fixed, stable contact point (98) between the proof mass (204) and the stators (200, 202), the beam (220, 222) being otherwise rigid to applied forces along axes orthogonal to the axis of pliancy. The resulting suspension system exhibits compliance to thermally induced loads while providing rigidity in response to seismic loads. In alternative embodiments of the suspension system, the pliant beams are positioned to provide temperature compensation for components of the transducer.

公开(公告)号：WO1985005058A1

公开(公告)日：1985-11-21

申请号：PCT/US1985000754

申请日：1985-04-25

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  HANSON, Richard, A.

IPC: B23P11/02

CPC classification number: B23P11/025 ,  G01P15/132 ,  Y10T29/43 ,  Y10T29/4902 ,  Y10T29/49863 ,  Y10T29/49865 ,  Y10T29/4987

Abstract: A transducer assembly (10) includes first and second stators (14, 16) which are axially aligned with, and bear upon opposite sides of a proof mass (12). The stators (14, 16) and proof mass (12) are clamped together by means of a sleeve (100) having a side portion (102) with upper and lower flanges (104, 106) projecting therefrom. An inner sleeve element (110), formed from a material having a different coefficient of thermal expansion than the side portion (102), is disposed between the flanges (104, 106). The temperature of the sleeve (100) is controlled such that the inner sleeve element (110) produces a tensile stress on said flanges (104, 106), increasing the spacing therebetween. The flanges (104, 106) are then joined to the stators (14, 16). Thereafter, the temperature of the sleeve (100) is controlled such that the tensile stress produced by the inner sleeve element (110) on the flanges is reduced producing a compression force tending to reduce the flanging spacing. This compression force is transmitted to the stators (14, 16) and proof mass (12) as a controlled compressive axial preload.

公开(公告)号：WO1985003583A1

公开(公告)日：1985-08-15

申请号：PCT/US1985000153

申请日：1985-01-30

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  MULLER, Hans, Rudolph

IPC: G06F01/00

CPC classification number: G11C29/765 ,  G11C16/06 ,  G11C16/20 ,  G11C16/225 ,  G11C16/30

Abstract: A crash survivable memory unit (10) for an aircraft flight data recorder system wherein an electronically erasable solid state memory (38) for storing the flight data and a memory controller circuit (32) are housed in a penetration resistant, thermally insulated enclosure (60). Power dissipation within the insulated enclosure is minimized by an external switching circuit (48) that applies operating potential to the solid state memory (38) only when data are being transferred to and from the memory circuit (38). A data protection circuit (58), located within the insulated enclosure (60) inhibits memory write and erase operations whenever the system operating potential falls below a predetermined level. In continuously storing flight data, the oldest stored data is overwritten with newly arriving flight data and the memory controller (32) maintains an erased boundary that defines the beginning and end of the recorded data. A power monitor circuit (52), located outside the insulated enclosure (60), resets the memory controller (32) to the erased boundary following a power interruption. A dedicated portion of the memory space is utilized to store the address of faulty memory locations (detected during the data storage sequence) and stores the beginning and ending memory address of selected portions of the data record. The memory controller (32) is sequenced to skip both the faulty memory locations and memory storage locations associated with the selected portions of the data record when new flight data are being stored.

Abstract translation: 一种用于飞行器飞行数据记录器系统的碰撞存活存储单元（10），其中用于存储飞行数据的电子可擦除固态存储器（38）和存储器控制器电路（32）被容纳在防穿透绝热外壳（60 ）。 只有当数据被传送到存储器电路（38）和从存储器电路（38）传送到固态存储器（38））时，通过外部开关电路（48）使绝缘外壳内的功率消耗最小化。 位于绝缘外壳（60）内的数据保护电路（58）每当系统工作电位下降到预定水平以下时就禁止存储器写入和擦除操作。 在连续存储飞行数据时，最新的存储数据被新到达的飞行数据覆盖，并且存储器控制器（32）保持定义记录数据的开始和结束的擦除边界。 位于绝缘外壳（60）外部的电力监视器电路（52）在电源中断之后将存储器控制器（32）复位到被擦除的边界。 存储器空间的专用部分用于存储故障存储器位置的地址（在数据存储序列期间检测），并存储数据记录的选定部分的开始和结束存储器地址。 当存储新的飞行数据时，存储器控制器（32）被排序以跳过与数据记录的选定部分相关联的故障存储器位置和存储器存储位置。

公开(公告)号：WO1985003566A1

公开(公告)日：1985-08-15

申请号：PCT/US1985000089

申请日：1985-01-22

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  BATEMAN, Charles, D. ,  GROVE, Michael, M.

IPC: G01C05/00

CPC classification number: G08G5/045 ,  G01C5/005 ,  G08G5/0086

Abstract: A terrain advisory system (10) utilizes stored data (18) representative of terrain and other obstacles in predeterminded geographical areas of interest to provide advisory warnings of the proximity of terrain, obstacles and restricted areas as they are approached. When used in a vehicle such as an aircraft, the system monitors (12, 13) the position, altitude, ground speed, ground track and the vertical speed of the vehicle and provides advisory indications of the position and path of travel of the vehicle with respect to obstacles and terrain. Such advisory indications may take the form of voice warnings (26) describing the nature and position of any obstacles, or a visual display (34, 36) showing the position of the obstacles and terrain with respect to the vehicle.