公开(公告)号：WO1990003642A1

公开(公告)日：1990-04-05

申请号：PCT/US1989003723

申请日：1989-08-28

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  MATTER, Dennis, Lynn ,  BOYLE, David, James ,  ISAACSON, Mark ,  YEE, Eddy, H., F. ,  MOORE, Daniel, Lowell ,  CORNELIUS, Craig, J.

IPC: G11B07/00

CPC classification number: G11B7/08 ,  G11B7/0857 ,  G11B11/1055 ,  G11B11/10567 ,  G11B11/10576 ,  G11B19/2009 ,  G11B23/0316 ,  G11B25/043 ,  G11B33/1446

Abstract: An optical disk system includes a hermetically sealed optical disk cartridge (10) and a hermetically sealed optical block (12) each having overlying optical windows (14 and 16) for coupling laser light from the optical block (12) to the optical disk contained in the cartridge (10). A split spindle motor is employed with a spindle rotor magnet (44) contained in the optical disk cartridge (10) and spindle drive coils (20) disposed outside of the cartridge (10) so that the optical disk cartridge (10) needs no mechanical or electrical connections. The optical block (12) contains the optical head (68) and, in one embodiment, the seek motor (70) so as to protect the optics (64) as well as the tracking and focusing actuators (66) from contaminants.

Abstract translation: 光盘系统包括密封的光盘盒（10）和密封的光学块（12），每个密封的光学块都具有覆盖的光学窗口（14和16），用于将来自光学块（12）的激光耦合到光盘 盒（10）。 分裂主轴电动机与包含在光盘盒（10）中的主轴转子磁体（44）和设置在盒（10）外侧的主轴驱动线圈（20）一起使用，使得光盘盒（10）不需要机械 或电气连接。 光学块（12）包含光学头（68），并且在一个实施例中包括寻道马达（70），以便保护光学元件（64）以及跟踪和聚焦致动器（66）免受污染物的影响。

公开(公告)号：WO1989009955A1

公开(公告)日：1989-10-19

申请号：PCT/US1989001220

申请日：1989-03-22

Applicant: SUNDSTRAND DATA CONTROL, INC.

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

IPC: G05D01/06

CPC classification number: G05D1/0623

Abstract: A wind shear recovery system (10) for an aircraft utilizes inertially derived pitch information to provide the pilot with information (12) defining the optimum pitch angle for maximum climb during a wind shear condition. The system (10) utilizes a pitch reference modulator (22) that receives a stall warning discrete from a stall warning system (16) to reduce the commanded pitch guidance angle (12) 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 this angle of attack vane signal that are caused by air turbulence encountered during wind shear, and that can cause pilot induced oscillations about the pitch axis.

Abstract translation: 用于飞行器的风切变恢复系统（10）利用惯性导出的俯仰信息来为飞行员提供在风切变条件期间限定最大爬升的最佳俯仰角的信息（12）。 系统（10）使用俯仰参考调制器（22），其接收从失速警告系统（16）离散的失速警告，以在发生失速警告时减小指令的俯仰引导角（12），以减少停止的可能性 飞机在退化的性能条件下，如尾风和发动机的条件。 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，以避免在风切变过程中遇到的空气湍流引起的该迎角信号中的瞬变，并且可能导致围绕俯仰轴的导频感应振荡。

公开(公告)号：WO1989004948A1

公开(公告)日：1989-06-01

申请号：PCT/US1988004071

申请日：1988-11-15

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  MacGUGAN, Douglas, Campbell

IPC: G01C21/00

CPC classification number: G01C19/5776

Abstract: Apparatus and method for determining the angular rate of rotation and linear acceleration of a body with respect to three orthogonal axes (x, y, z). Three pairs of accelerometers (10, 12; 14, 16; and 18, 20) are arranged with their sensitive axes antiparallel to each other, and each pair is vibrated back and forth along one of the orthogonal axes. The signals output from the accelerometers are processed to determine Srate and Svel for each of the rate axes as a function of the sum and differences of the signals produced by each of the accelerometers. The value of Svel for each axis is used by a microprocessor (82) to produce a signal equal to an incremental change in velocity (DELTAV) for each axis. The incremental change in velocity is then used in conjunction with errors estimated from previous fractional portions of the dither period for each pair of accelerometers to calculate the rate of rotation of the body about each of the axes as a function of the values for Srate. As a further aspect of the invention, the incremental change in velocity and incremental changes in angular position (DELTA)p) may be determined as a running average of previous fractional portions of the dither frequency.

公开(公告)号：WO1989002080A1

公开(公告)日：1989-03-09

申请号：PCT/US1988002734

申请日：1988-08-08

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  HULSING, Rand, H., II ,  LEE, Charles, K.

IPC: G01R23/02

CPC classification number: G01R23/10

Abstract: A device and method for measuring the frequency of an input signal (I) by measuring the number of cycles of the input signal (I) that occur in a sample interval between successive sampling time tn. An integer counter (31) determines an estimated integer number of input signal cycles, and fraction counters (32, 33) determine fractional counts by counting cycles of a clock signal (CLK) during time intervals between a first measurement time before the sampling time and a second measurement time after the sampling time. A correction circuit (34) refines the fractional counts by determining the phase relationships between the clock (CLK) and input signals (I) at each measurement time. The correction circuit (56), a first switch (50) connected between the constant current source (52) and a reference potential, a second switch (54) connected between the control circuit (66) for the switches (50, 54). The control circuit (66) disconnects the current source (52) from the reference potential at each measurement time, and disconnects the current source (52) from the capacitor (56) upon the next occurrence of a periodic characteristic of the clock signal (CLK) that occurs after the measurement time. The voltage on the capacitor (56) then provides the required phase relationship.

公开(公告)号：WO1988008182A1

公开(公告)日：1988-10-20

申请号：PCT/US1988001102

申请日：1988-04-05

Applicant: SUNDSTRAND DATA CONTROL, INC.

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

IPC: G08B21/00

CPC classification number: G05D1/0676

Abstract: A ground proximity warning system is disclosed which can recognize when an aircraft is on a final approach to an airport without utilizing a landing flap signal input. Airports (16) together with the surrounding terrain topography are modeled by a simple geometric shape, such as, an inverted truncated cone (4), and stored on-board the aircraft. The system uses navigational data (12, 14) to determine the distance of the aircraft from the geometric model. Once the aircraft is determined to be within the area defined by the geometric model, the system provides an enabling envelope (46) indicative that the aircraft is on a final approach for enabling various ground proximity warning systems. Also disclosed is a system for altering the enabling envelope (46) as a function of the aircraft's alignment with particular runway (50).

公开(公告)号：WO1988002944A1

公开(公告)日：1988-04-21

申请号：PCT/US1987002723

申请日：1987-10-16

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  KELLEY, Arthur, W. ,  OWENS, William, R.

IPC: H02J01/00

CPC classification number: H01F38/22 ,  H01F30/10 ,  H01F2038/305

Abstract: An inductive coupled power system has a transmission circuit with a dual primary comprising two conductor loops (28, 29). First segments (28a, 29a) of the loops extend through an area served by the system adjacent each other and second segments (28b, 29b) of the loops extend through the area one on either side of the adjacent first segments. A small loop configuration minimizes the stray magnetic field. A secondary pickup assembly (31) has a U-shaped core (33) with two legs (34, 35) which embrace the first segments of the two loops and a core element (40) adjacent the first loop segments is positioned between the ends of the legs. Each of the power circuits of a plurality of loads includes a shunt regulator (92).

Abstract translation: 电感耦合电力系统具有一个具有双重原子的传输电路，包括两个导体环路（28,29）。 环的第一段（28a，29a）延伸穿过由系统相邻的区域彼此相邻，并且环的第二段（28b，29b）延伸穿过相邻第一段的任一侧上的区域。 小环配置使杂散磁场最小化。 次级拾取组件（31）具有带有两个支腿（34,35）的U形芯（33），其包围两个环的第一段，并且与第一环段相邻的芯元件（40）位于两端 的腿。 多个负载中的每个电源电路包括分流调节器（92）。

公开(公告)号：WO1987007030A1

公开(公告)日：1987-11-19

申请号：PCT/US1987001087

申请日：1987-05-13

Applicant: SUNDSTRAND DATA CONTROL, INC.

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

IPC: G01S01/16

CPC classification number: G01S11/08 ,  G01S1/10 ,  G01S19/15

Abstract: A system for landing an aircraft, using a ground installation and an airborne installation which are synchronized together using GPS system time. Specifically, the ground installation includes a ground transmitter (32) which radiates the sequence of signals (A, B, C, D) which provide precision guidance information to the aircraft, an aircraft installation which includes a radio receiver (8) and a processor (15) to receive a process the transmitted guidance signals and to provide indications (18, 20) to aid the pilot in landing the aircraft, a GPS receiver in the air (68) and on the ground (60) for producing signals representative of GPS system time, and a channel selector (72) in the aircraft for actuating the processor to synchronize its operation with the ground installation transmitter. Range information is provided by measuring the time interval between the transmission of a reference at the ground and its receipt in the air.

Abstract translation: 一种使用GPS系统时间同步在一起的飞机着陆系统，使用地面安装和机载安装。 具体地说，地面设备包括一个地面发射机（32），其将向航空器提供精确指导信息的信号序列（A，B，C，D）发射，飞机设备包括无线电接收机（8）和处理器 （15），以接收所传送的引导信号的处理并提供指示（18,20）以辅助飞行员着陆飞机，在空中（68）和地面（60）上的GPS接收器用于产生代表 GPS系统时间和飞行器中的通道选择器（72），用于致动处理器以使其操作与地面安装发射器同步。 范围信息是通过测量地面上的参考传输与其在空中的接收之间的时间间隔来提供的。

公开(公告)号：WO1987002468A1

公开(公告)日：1987-04-23

申请号：PCT/US1986002221

申请日：1986-10-20

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  PETERS, Rex, B.

IPC: G01P09/04

CPC classification number: G01C19/5726

Abstract: A system for determining angular rate of rotation of a body about a rate axis. In one arrangement, the system comprises first (10) and second (12) accelerometers, movement means and processing means. The first and second accelerometers have their sensitive axes (16, 18) parallel to a sensing axis that is in turn perpendicular to the rate axis. The first and second accelerometers are adapted to produce first and second output signals (a1, a2), each output signal having a frequency corresponding to the acceleration experienced by the respective accelerometer along its sensitive axis. The movement means includes means (68) for producing a periodic movement signal and means (14) responsive to the movement signal for periodically moving the accelerometers along a movement axis perpendicular to the rate and sensing axes, such that each output signal includes a periodic Coriolis component. The processing means includes means (75) for producing a reference signal that defines one or more first time periods during which the Coriolis components have one polarity and one or more second time periods during which the Coriolis components have the opposite polarity. The first and second time periods together span one or more complete periods of the movement signal. The processing means further comprises means (71, 72) for determining, for each output signal, a phase value representing the difference between the phase change of the output signal during the first time periods and the phase change of the output signal during the second time periods. The processing means further includes means (80) for determining from the phase values a value representing the angular rate of rotation of the body about the rate axis. In a second arrangement, a single accelerometer is periodically moved along the movement axis.

Abstract translation: 用于确定身体围绕速率轴的旋转角度的系统。 在一种布置中，系统包括第一加速度计（10）和第二加速度计（12），运动装置和处理装置。 第一和第二加速度计具有与感测轴平行的敏感轴（16,18），感测轴又与速度轴垂直。 第一和第二加速度计适于产生第一和第二输出信号（a1，a2），每个输出信号的频率对应于各加速度计沿其敏感轴所经历的加速度。 移动装置包括用于产生周期性运动信号的装置（68）和响应于运动信号的装置（14），用于沿着垂直于速率和感测轴的运动轴周期性地移动加速度计，使得每个输出信号包括周期性科里奥利 零件。 处理装置包括用于产生参考信号的装置（75），该参考信号定义了科里奥利分量具有一个极性的一个或多个第一时间段，以及科里奥利分量具有相反极性的一个或多个第二时间段。 第一和第二时间段一起跨越运动信号的一个或多个完整周期。 处理装置还包括装置（71,72），用于为每个输出信号确定表示第一时间段期间输出信号的相位变化与第二时间期间输出信号的相位变化之间的差的相位值 周期。 处理装置还包括用于根据相位值确定表示身体围绕速率轴的角速度的值的装置（80）。 在第二布置中，单个加速度计周期性地沿运动轴线移动。

公开(公告)号：WO1986002750A1

公开(公告)日：1986-05-09

申请号：PCT/US1985002076

申请日：1985-10-22

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  MILLER, Lawrence, D., Jr. ,  OWEN, Robert, J. ,  KILTZ, Richard, M.

IPC: G06F13/00

CPC classification number: G07C5/085

Abstract: A combined flight data recorder data acquisition circuitry (10) and airborne integrated data circuitry (12) that can be variously packaged to supplement and update existing aircraft systems or serve as a stand-alone flight data recording and/or airborne integrated data system. The flight data recorder system circuitry (10) and airborne integrated data system circuitry (12) are separately programmed microprocessor based systems that are capable of processing aircraft parametric signals provided by a variety of aircraft signal sources (e.g. 16 and 22). In the disclosed arrangement, the airborne integrated data system circuitry (12) is arranged and programmed to automatically monitor engine start and shutdown procedures, aircraft takeoff and cruise and to provide a landing report that indicates fuel consumption and landing weight. To minimize memory storage requirements and provide readily available engine condition information, the automatic monitoring consists of a single set of signals for each monitored condition and the information is converted to standard engineering units. Monitoring of selected parametric signals to detect excessive levels also is provided. Stored data is periodically retrieved by means of a ground readout unit (30).

Abstract translation: 组合的飞行数据记录器数据采集电路（10）和机载集成数据电路（12），其可以被不同地打包以补充和更新现有的飞行器系统或用作独立的飞行数据记录和/或机载集成数据系统。 飞行数据记录器系统电路（10）和机载集成数据系统电路（12）是分别编程的基于微处理器的系统，其能够处理由各种飞行器信号源（例如16和22）提供的飞机参数信号。 在所公开的布置中，机载集成数据系统电路（12）被布置和编程以自动监视发动机起动和关闭程序，飞机起飞和巡航，并提供指示燃料消耗和着陆重量的着陆报告。 为了最小化存储器存储要求并提供易于获得的发动机状态信息，自动监控由每个监控条件的单组信号组成，并将信息转换为标准工程单位。 还提供了监测所选择的参数信号以检测过高的水平。 通过地面读出单元（30）周期性地检索存储的数据。

公开(公告)号：WO1986000158A1

公开(公告)日：1986-01-03

申请号：PCT/US1985001080

申请日：1985-06-07

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  SMITH, Jeffrey, Thomas ,  FRAZIER, David, E. ,  LEONARDSON, Ronald, B.

IPC: G06F15/50

CPC classification number: G01C21/16

Abstract: An inertial sensor assembly (ISA) (12) includes a cluster of three ring laser gyros (20), each gyro (42, 44, 46) producing an output signal having a pulse repetition rate representative of the rate of angular deviation of the ISA about one of three coordinate axes X, Y, and Z. The ring laser gyros (42, 44, 46) are asynchronously dithered at a relatively constant rate. The ISA (12) also includes a triad of three accelerometers (30), with each accelerometer (72, 74, 76) producing an output signal representative of the rate of velocity deviation of the ISA (12) along one of the X, Y, and Z coordinate axes. A first processor, P1 (14), accumulates the pulses produced by each ring laser gyro (42, 44, 46) over its dither period. The resultant counts are stored in registers (202, 204, 206) for subsequent sampling by the P1 processor (14) at a periodic sampling rate which is greater than the dither rate. The P1 processor (14) then synchronizes each sampled pulse count to a common sampling interval, thereby eliminating errors otherwise caused by using positional data values taken at different times. The P1 processor (14) also compensates the ring laser gyro and accelerometer-produced signals at the sensor and the system level for effects such as temperature, bias offsets, scale factor and misalignment by the use of compensating coefficients stored in electrically erasable, programmable read-only memory (260, 262). The processed data from the P1 processor (14) are passed to a P2 processor (16) which performs navigational computations to thereby produce computed positional information.