公开(公告)号：WO1992008140A1

公开(公告)日：1992-05-14

申请号：PCT/US1991007882

申请日：1991-10-22

Applicant: SUNDSTRAND DATA CONTROL, INC.

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

IPC: G01P15/08

CPC classification number: G01P15/097 ,  G01P2015/0828

Abstract: An accelerometer (60) includes a first proof mass (32') and a second proof mass (42'), which are respectively connected by flexures (36' and 46') to a first base (34') and a second base (44'). The first and second bases are clamped between a top enclosure (62) and a bottom enclosure (64), between which is defined a cavity (66) in which the first and second proof masses are disposed. A quartz crystal resonator (38') extends between the first proof mass and the first base; similarly, a quartz crystal resonator (48') extends between the second proof mass and second base. The quartz crystal resonators experience tension/compression in a push-pull mode when the accelerometer is subjected to acceleration along an acceleration-sensitive axis (26') that extends transversely through the proof-masses. A fluid within the cavity couples the first and second proof masses together through a ''squeeze film damping'', due to their closely-spaced relationship to each other.

Abstract translation: 加速度计（60）包括分别通过弯曲（36'和46'）连接到第一基座（34'）和第二基座（34'）的第一检验质量块（32'）和第二检验质量块（42' 44' ）。 第一和第二基座被夹紧在顶部外壳（62）和底部外壳（64）之间，其间限定有空腔（66），第一和第二检验质量块设置在其中。 石英晶体谐振器（38'）在第一检测质量块和第一基底之间延伸; 类似地，石英晶体谐振器（48'）在第二检验质量块和第二基底之间延伸。 当加速度计沿着横向延伸穿过检验质量的加速度敏感轴（26'）进行加速度时，石英晶体谐振器在推挽模式下经受张力/压缩。 腔内的流体由于它们彼此间隔紧密的关系，通过“挤压膜阻尼”将第一和第二检验质量块连接在一起。

公开(公告)号：WO1992004634A1

公开(公告)日：1992-03-19

申请号：PCT/US1991006417

申请日：1991-09-04

Applicant: SUNDSTRAND DATA CONTROL, INC.

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

IPC: G01R23/02

CPC classification number: G01R23/10

Abstract: A dual-edge frequency counter and method for minimizing the effects of duty cycle modulation. In its simplest form, a dual-edge counter (50) includes a first counter (52) that accumulates reference clock pulses between successive rising edges of an input signal. An input signal is also applied to an inverter (54), which inverts the square wave signal prior to applying it to a second counter (56) that also accumulates reference clock cycles between successive rising edges of the inverted sensor signal. A summation junction (60) totals the accumulated counts from the first and second counters so that they can be averaged by a divider (62), which divides the total count by two. The technique is also employed in connection with a frequency counter that includes an integer counter (72) for totaling the number of cycles of the sensor signal occurring during a sample time defined by successive gate signals.

公开(公告)号：WO1991019987A1

公开(公告)日：1991-12-26

申请号：PCT/US1991003567

申请日：1991-05-20

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  HOLDREN, Frederick, V. ,  NOVACK, Mitchell, J.

IPC: G01P15/08

CPC classification number: G01P15/132

Abstract: A mounting/coupling structure (16, 216, 316) for use in an accelerometer (10, 210, 310) to mount the electronics assembly (18, 218, 318) with respect to the case (20, 220, 320), and to electrically couple the electronics assembly to the acceleration sensitive structure (14, 214, 314). The mounting/coupling structure may be positioned such that it provides gas damping for the paddle (42, 242, 342), and may also include means for holding the acceleration sensitive structure in a fixed position with respect to the case.

公开(公告)号：WO1991015827A1

公开(公告)日：1991-10-17

申请号：PCT/US1991002067

申请日：1991-03-26

Applicant: SUNDSTRAND DATA CONTROL, INC.

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

IPC: G06F15/50

CPC classification number: G05D1/0623 ,  G05D1/0661

Abstract: A pitch guidance system for an aircraft utilizes inertially derived pitch information to provide the pilot with information defining the optimum pitch angle for maximum climb during a wind shear condition. The system utilizes a pitch reference modulator (22) that receives a stall warning discrete from a stall warning system to reduce the commanded pitch angle 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 the angle of attack vane signal, and the commanded pitch angle is biased as a function of altitude (70) and vertical speed (58) to optimize the pitch angle for different altitudes and descent rates.

Abstract translation: 用于飞行器的俯仰引导系统利用惯性导出的俯仰信息来为飞行员提供定义在风切变条件期间最大爬升的最佳俯仰角的信息。 该系统使用俯仰参考调制器（22），其接收从失速警告系统离散的失速警告，以在出现失速警告时减小指令的俯仰角，以减少在退化的性能状况（例如尾风）期间使飞行器停滞的可能性 和发动机的条件。 该系统利用惯性导出的音调信息，而不是空气质量导出的迎角信息，以避免迎角信号的瞬变，并且指令的俯仰角作为高度（70）和垂直速度（58）的函数被偏置以优化 不同高度和下降率的俯仰角。

公开(公告)号：WO1991004921A1

公开(公告)日：1991-04-18

申请号：PCT/US1990004511

申请日：1990-08-10

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  GROENEWEGE, Johannes, B.

IPC: B65D81/02

CPC classification number: H05K5/0213 ,  Y10S206/811

Abstract: A crash survivable enclosure (10) includes a flight data recorder or memory device (14) physically supported and protected by a solid synthetic wax filler (46) contained in an inner metal shell (24). A second filler (60) of high efficiency heat insulating material is contained in an outer shell (50) for physically supporting the inner shell (24) and its contents.

公开(公告)号：WO1991002942A1

公开(公告)日：1991-03-07

申请号：PCT/US1990004189

申请日：1990-07-19

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  HOWARD, Bruce, S.

IPC: G01C03/00

CPC classification number: G01S1/70 ,  G01S17/87

Abstract: A portable siting system particularly useful for siting a portable localizer (20) for a collocated approach guidance system for aircraft utilizes a laser range finder (32) in conjunction with a shaft encoder (26) to determine the distance between the localizer (20) and two arbitrary points (54, 58) along a runway center line (62) as well as the azimuth offset between the two points (Υ2-Υ1). A microprocessor (38) is used to compute the number of degrees (Υ6) the antenna (22) of the localizer must be rotated so that its beam intersects the extended runway center line at a predetermined point (18) based on trigonometric computations performed on the two measured distances and the measured angle.

公开(公告)号：WO1991001546A1

公开(公告)日：1991-02-07

申请号：PCT/US1990003199

申请日：1990-06-05

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  DAVIDSON, Charles, W.

IPC: G01S01/10

CPC classification number: G01S1/10

Abstract: A method and apparatus for correcting errors introduced into a pulse amplitude comparison system particularly suitable for correcting errors introduced by base line shift (26', 28') and pulse amplitude droop (30', 32') alters the sequence of the pulses to be compared in such a manner that the errors tend to cancel (40, 42, 44, 46, 66, 72), and averages the results of the comparisons to reduce the comparison error (96).

Abstract translation: 用于校正引入到脉冲幅度比较系统中的误差的方法和装置，特别适用于校正由基线偏移（26'，28'）引入的误差，并且脉冲幅度下降（30'，32'）将脉冲序列改变为 以这样的方式进行比较，即错误倾向于抵消（40,42,44,46,66,72），并且对比较的结果进行平均以减少比较误差（96）。

公开(公告)号：WO1990012275A1

公开(公告)日：1990-10-18

申请号：PCT/US1990001337

申请日：1990-03-12

Applicant: SUNDSTRAND DATA CONTROL, INC.

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

IPC: G01B07/14

CPC classification number: G01D5/2291 ,  G01B7/14 ,  G01D5/2216

Abstract: A transformer and method for sensing displacement. A linear variable displacement transformer (LVDT) (50, 100, 150, 200, and 250) is disclosed with respect to several embodiments, each including a core (52, 102, 152, 202, and 252) having a primary leg (56, 104, 154, 204, and 254), and two secondary legs (56 and 60, 106 and 108, 158 and 160, 206 and 208, and 258 and 260). A primary coil (54, 110, 156, 210, and 264) is disposed on the primary leg, and secondary coils (62 and 64, 112 and 114, 162 and 164, 212 and 214, and 266 and 268) are disposed on the secondary legs. Pole pieces (70 and 72, 120 and 122, 170 and 172, 222 and 224, and 274 and 276) are disposed in gaps between the primary leg and each secondary leg, so that they control the reluctance to a magnetic flux produced by an electric current flowing through the primary coil.

公开(公告)号：WO1990000254A1

公开(公告)日：1990-01-11

申请号：PCT/US1989002464

申请日：1989-06-06

Applicant: SUNDSTRAND DATA CONTROL, INC.

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

IPC: G01P15/13

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

Abstract: A transducer having compensation for a deflection due to an applied stress. The transducer includes a support ring (32) having a proof mass (34) cantilevered on a pair of flexures (38) between the magnets (26, 28) of a stator in which the transducer is mounted. Deflection of the support ring due to an imbalanced applied force is compensated by either moving the pads (30) used to mount the support ring, moving the centroid of capacitance (128) of the proof mass, or by modifying the support ring to provide a pair of moment arms (156), each approach insuring that an axis of deflection (102, 130) of the support ring is coaligned with the centroid of capacitance, thereby minimizing a bias error in the transducer output.

公开(公告)号：WO1989006846A1

公开(公告)日：1989-07-27

申请号：PCT/US1988004635

申请日：1988-12-22

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  BATEMAN, Charles, D.

IPC: G08B23/00

CPC classification number: G05D1/0615

Abstract: A wind shear warning system (10) monitors the flight path of an aircraft and wind shear (16) in the vicinity of the aircraft and generates an advisory or cautionary message (34) for the pilot based both on the magnitude (20, 22) of the wind shear and the flight path of the aircraft. When the aircraft is flying a normal flight path, a wind shear warning is generated only when relatively high negative wind shears are present. If the flight path of the aircraft is not normal, for example, if the aircraft is below the glide slope (18) or descending too rapidly (14), a cautionary alert is given at lower values of wind shear. The alert or warning (54) is selected to provide the pilot with information defining the nature of the hazard or potential hazard being encoutered.