公开(公告)号：WO1987001356A1

公开(公告)日：1987-03-12

申请号：PCT/US1986001749

申请日：1986-08-25

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  BATEMAN, Charles, D. ,  GLOVER, John, H. ,  MULLER, Hans, R.

IPC: B64D45/00

CPC classification number: G01C5/005

Abstract: Performance of an aircraft ground proximity warning system can be improved, especially where the performance of the aircraft itself has been degraded by a factor such as wind shear, by extending excessive descent rate (24) and negative climb after takeoff (32) warning enveloppes down to within five feet of the ground. Additional immprovements in warning performance can be made by monitoring flight path angle (100) when the aircraft is close to the ground, and by monitoring computed altitude rate (16), phase of flight (208, 236), glide slope deviation (110), angle of attack (10) and stall margin (82).

Abstract translation: 飞机地面接近预警系统的性能可以得到改善，特别是飞机本身的性能由于风切变等因素而降低，通过延长过大的下降速率（24）和起飞后的负爬升（32）警告信封下降 到地面五英尺以内。 通过监测飞机接近地面的飞行路径角度（100），并通过监测计算出的高度（16），飞行阶段（208,236），滑坡偏差（110）， ，迎角（10）和失速余量（82）。

公开(公告)号：WO1986005017A1

公开(公告)日：1986-08-28

申请号：PCT/US1986000391

申请日：1986-02-24

Applicant: SUNDSTRAND DATA CONTROL, INC.

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

IPC: G06F15/50

CPC classification number: G01C19/668 ,  G01C21/16

Abstract: An inertial sensor assembly (ISA) (12) includes a cluster (20) of three ring laser gyros (42, 44, 46), each gyro producing an output signal having a pulse repetition rate representative of the rate of angular deviation of the ISA (12) 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 (30) of three accelerometers (72, 74, 76), with each accelerometer 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 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.

Abstract translation: 惯性传感器组件（ISA）（12）包括三个环形激光陀螺仪（42,44,46）的簇（20），每个陀螺仪产生具有代表ISA的角度偏差速率的脉冲重复率的输出信号 （12）围绕三个坐标轴X，Y和Z中的一个。环形激光陀螺仪（42,44,46）以相对恒定的速率异步抖动。 ISA（12）还包括三个加速度计（72,74,76）的三元组（30），每个加速度计产生代表沿着X，Y之一的ISA（12）的速度偏差速率的输出信号 和Z坐标轴。 第一处理器P1（14）在其抖动周期内累积由每个环形激光陀螺仪（42,44,46）产生的脉冲。 结果计数被存储在寄存器中，以便由P1处理器（14）以大于抖动速率的周期性采样速率进行后续采样。 然后，P1处理器（14）将每个采样的脉冲计数同步到公共采样间隔，从而消除由不同时间使用的位置数据值引起的误差。

公开(公告)号：WO1986004150A1

公开(公告)日：1986-07-17

申请号：PCT/US1985002554

申请日：1985-12-20

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  FOOTE, Steven, A.

IPC: G01R27/26

CPC classification number: G01P15/125 ,  G01R15/09 ,  G01R27/2605

Abstract: Prior detection circuits for measuring capacitance differences have commonly included error sources, such as P-N junctions, in the DC signal path. The present invention provides an improved detection circuit for measuring the capacitance difference between first (C1) and second (C2) capacitive elements. The detection circuit comprises a first capacitor (C3) serially connected to the first capacitive element at a first common node (36) to form a first series circuit, and a second capacitor (C4) serially connected to the second capacitive element at a second common node (38) to form a second series circuit. The detection circuit also includes a switch (means) circuit (32) connected between the common nodes and a reference potential, (drive means) a driver (30) for applying a drive signal across each series circuit, a line for activating the switch (activation means) circuit (48) and (means) a difference detector (34) for measuring the voltage difference between the common nodes. The switch circuit has a first state in which the common nodes are connected to the reference potential and a second state in which the common nodes are isolated from the reference potential and from one another. The drive signal comprises a series of first voltage transitions (104, 106) operative to vary the total voltage drop across each series circuit. The line for activating the switch circuit changes the switch circuit from the first state to the second state at or prior to each first voltage transition. Therefore after each first voltage transition, the difference between the voltages of the first and second common nodes is a measure of the difference between the capacitances of the first and second capacitive elements. A similiar technique may be applied to the measurement of the capacitance of a single capacitor.

公开(公告)号：WO1986001022A1

公开(公告)日：1986-02-13

申请号：PCT/US1985001315

申请日：1985-07-10

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  BATEMAN, Charles, D. ,  GLOVER, J.H. ,  MULLER, Hans, R.

IPC: G08B23/00

CPC classification number: G01C5/005

Abstract: Performance of an aircraft ground proximity warning system can be improved, especially where the performance of the aircraft itself has been degraded by a factor such as wind shear, by extending Mode 1 (24) and Mode 3 (32) warning envelopes down to within five feet of the ground. Additional improvements in warning performance can be made by monitoring flight path angle (46) when the aircraft is close to the ground. Warnings are based on a logic network (28) which uses radio altitude (12), barometric altitude rate (14), airspeed (50), stall margin (82), and a source (10) of signals representative of the angle of attack, vertical acceleration, and phase of flight of the aircraft, whereby a warning (30) is provided that the aircraft should pitch up except when the stall margin is below a predetermined value.

Abstract translation: 飞机地面接近警报系统的性能可以得到改善，特别是当飞机本身的性能由于风切变等因素而降级时，通过将模式1（24）和模式3（32）警告信封延伸到五分之内 脚的地面。 当飞机靠近地面时，可以通过监视飞行路径角度（46）来进一步改善警戒性能。 警告是基于逻辑网络（28），其使用无线电高度（12），气压高度率（14），空速（50），失速余量（82）和代表迎角的信号源（10） ，垂直加速度和飞行阶段，由此提供警告（30），除了当失速余量低于预定值时，飞机应该俯仰。

公开(公告)号：WO1985004847A1

公开(公告)日：1985-11-07

申请号：PCT/US1985000688

申请日：1985-04-18

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  NYE, William, S.

IPC: B64D43/00

CPC classification number: B64D43/00

Abstract: An enclosure for an aircraft inertial unit (IRU) includes a dip-brazed chassis (10) having an inertial sensor assembly (ISA) compartment (40) and an electronics module compartment (36). The ISA compartment (40) is rigid with the ISA (42) being mounted therein via diagonally opposed shock isolation mounts (330, 332). The centers of elasticity of the shock isolation mounts (330, 332) are aligned with the center of gravity of the ISA. A caging system (340, 342) prevents excessive movement of the ISA (42) with respect to the ISA compartment (40). The electronics module compartment (36) includes a thermal mass (62, 64) for heat sinking the electronics module (60) by conduction. The surfaces of the walls in the electronics module (60) are heat reflective to prevent heat in the enclosure from being radiated to the electronics module (60). The remaining surfaces of the enclosure are black to promote heat radiation. The IRU enclosure is mounted to the aircraft by means of a mounting tray (12). The tray (12) has diagonally positioned alignment pins (150, 152) that mate with alignment holes in the IRU enclosure (10) to assure proper IRU alignment. Pliant, heat conductive fingers (136) affixed to the tray (12) contact the thermal mass (62, 64) to promote heatflow from the enclosure (10) to the tray. Thermally conductive feet (140, 142) on the tray provide a path for heat flow to the aircraft.

Abstract translation: 用于飞机惯性单元（IRU）的外壳包括具有惯性传感器组件（ISA）隔室（40）和电子模块隔间（36）的浸镀铜底盘（10）。 ISA隔室（40）是刚性的，ISA（42）通过对角相对的防震架（330,332）安装在其中。 冲击隔离安装座（330,332）的弹性中心与ISA的重心对齐。 笼蔽系统（340,342）防止ISA（42）相对于ISA隔间（40）的过度移动。 电子模块隔室（36）包括用于通过导电散热电子模块（60）的热质量（62,64）。 电子模块（60）中的壁的表面是热反射的，以防止外壳中的热辐射到电子模块（60）。 外壳的其余表面是黑色的，以促进热辐射。 IRU外壳通过安装托盘（12）安装到飞机上。 托盘（12）具有与IRU外壳（10）中的对准孔配合的对角定位的对准销（150,152），以确保正确的IRU对准。 固定到托盘（12）的柔性导热指状物（136）接触热物质（62,64）以促进从外壳（10）到托盘的热流。 托盘上的导热脚（140,142）为飞行器的热流提供了一条路径。

公开(公告)号：WO1985004487A1

公开(公告)日：1985-10-10

申请号：PCT/US1985000445

申请日：1985-03-18

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  LEE, Charles, K. ,  PETERS, Rex, B. ,  GOGIC, Aleksander, M.

IPC: G01R23/00

CPC classification number: G01R23/10 ,  G01R23/02

Abstract: Prior techniques for determining frequency by counting the cycles of an input signal suffer from the limitation that counts are frequently lost between sampling intervals. This limitation is overcome by the present invention that provides an apparatus and method for counting the number of cycles of a sensor signal (FS) and of a reference signal (FR) that occur during respective sensor and reference intervals associate with a sampling interval defined by a sample signal (SAMPLE). The sensor, reference and sample signals are received by gating circuit (30) that generates a sensor gate signal (GATES) and a reference gate signal (GATER), the sensor and reference gate signals respectively defining the sensor and reference intervals. The sensor interval begins and ends synchronously with respect to the sensor signal, and the reference interval begins and ends synchronously with respect to the reference signal. The sensor, reference and sampling intervals are approximately co-extensive with one another. The apparatus further comprises a sensor court circuit (32) and a reference count circuit (34). The sensor count circuit counts cycles of the sensor signal that occur during the sensor interval, and the reference count circuit counts cycles of the reference signal that occur during the reference interval.

Abstract translation: 用于通过对输入信号的周期进行计数来确定频率的现有技术受到在采样间隔之间经常丢失计数的限制。 本发明克服了这个限制，本发明提供了一种用于计数传感器信号（FS）和参考信号（FR）的循环次数的装置和方法，该参考信号（FR）在相应的传感器和参考间隔期间发生，与由 采样信号（SAMPLE）。 传感器，参考和采样信号由生成传感器门信号（GATES）和参考门信号（GATER）的选通电路（30）接收，传感器和参考门信号分别定义传感器和参考间隔。 传感器间隔相对于传感器信号同步开始和结束，参考间隔相对于参考信号同步开始和结束。 传感器，参考和采样间隔彼此大致共同。 该装置还包括传感器法庭电路（32）和参考计数电路（34）。 传感器计数电路对传感器间隔期间发生的传感器信号的周期进行计数，参考计数电路计算参考时间段内发生的参考信号的周期。

公开(公告)号：WO1985003585A1

公开(公告)日：1985-08-15

申请号：PCT/US1985000091

申请日：1985-01-22

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  HANSEN, Steven, D.

IPC: G06F15/00

CPC classification number: H03M7/30

Abstract: A data processing system for use in a solid state flight data recorder (10) wherein a plurality of aircraft parameter signals are processed and stored in electronic memory (34, 36) for later retrieval. The processor identifies those aircraft parameter data signals to be stored and for each such datum signal produces a signal triplet (64, 66, 72, 74) comprised of a parameter label signal, a time tag signal representative of the time interval from a reference time within which the data signal was produced, and the datum signal. A frame of the data bit stream produced by the data processor for storage on the memory (34, 36) includes an initial reference time signal (62) followed at fixed intervals by time tick signals (68, 70). Each signal triplet (64, 66, 72, 74) is positioned in the data bit stream following that initial reference time signal (62) or time tick signal (68, 70) to which its time signal is referenced. By so tiering the data time formatting a substantial compression of data is realized thereby reducing memory size requirements.

公开(公告)号：WO1985003190A2

公开(公告)日：1985-08-01

申请号：PCT/US1985000048

申请日：1985-01-14

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  WHITE, William, F. ,  SPURR, William, F.

IPC: C22C14/00 ,  G12B17/06 ,  H05K5/02

CPC classification number: G12B17/06 ,  C22C14/00 ,  H05K5/0213

Abstract: An aircraft flight data recorder housing (12) comprising a titanium alloy having a nominal composition of 10 weight percent vanadium, 2 weight percent iron, and 3 weight percent aluminum with the balance being titanium and, within limitations, certain trace elements. The alloy is preferably forged into a recorder housing (12) by a two-step isothermal forging process. Working during the first step occurs above the beta transus, while working during the second step occurs near, but below, the beta transus. It is preferred that about 70 to 90 percent of the work introduced into the housing (12) during the isothermal forging be introduced during the second working step. Subsequent heat treatment procedures combined with the above processing result in a fine grained recrystallized microstructure having discontinuous grain boundary alpha which surprisingly provide the alloy with very high penetration resistance.

Abstract translation: 一种飞机飞行数据记录器壳体（12），包括钛合金，标称组成为10重量％的钒，2重量％的铁和3重量％的铝，余量为钛，并且在限制内为某些微量元素。 合金优选通过两步等温锻造工艺锻造成记录器壳体（12）。 在第一步中工作发生在β转子上方，而在第二步骤期间的工作发生在β转子附近但在下方。 优选在第二工作步骤期间引入在等温锻造期间引入壳体（12）的工作的约70％至90％。 随后的热处理程序与上述处理相结合，导致具有不连续晶界α的细晶粒再结晶微结构，这使得合金具有非常高的耐渗透性。