公开(公告)号：US4811602A

公开(公告)日：1989-03-14

申请号：US224565

申请日：1988-07-26

Applicant: Rand H. Hulsing

Inventor： Rand H. Hulsing

IPC: G01C19/5783 ,  G01P3/46 ,  G01P15/08

CPC classification number: G01C19/5783 ,  G01P15/08 ,  G01P3/46

Abstract: The apparatus includes a parallelogram frame (50) including two accelerometer support surfaces (24, 26) on which are mounted two accelerometers (20 and 22) having their sensitive axes in parallel alignment. The accelerometer support surfaces are connected to opposite ends of a flex member (52), which includes six flexures (32, 34, 36, 38, 40, 42) having parallel bending axes. Two of the flexures (34, 38) are disposed at opposite ends of one side of each flexure member, and have a "long" axis that is substantially parallel to the sensitive axes of the accelerometers and aligned with a line connecting their centers of percussion. The centers of mass of the accelerometers and their associated supporting surfaces are coincident with the centers of percussion, and are rigidly connected by the two flexures and by one side (30) of each flex member. This solid metal path between the centers of percussion minimizes common mode errors.

Abstract translation: 该装置包括平行四边形框架（50），该平行四边形框架（50）包括两个加速度计支撑表面（24,26），两个加速度计支撑表面（24,26）安装有两个其平行对准的敏感轴的加速度计（20和22）。 加速度计支撑表面连接到柔性构件（52）的相对端，柔性构件包括具有平行弯曲轴线的六个挠曲件（32,34,36,38,40,42）。 两个挠曲件（34,38）设置在每个弯曲构件的一侧的相对端，并且具有基本上平行于加速度计的敏感轴并与连接其打击中心的线对准的“长”轴 。 加速度计及其相关的支撑表面的质心与冲击中心重合，并且通过两个弯曲部和每个柔性部件的一侧（30）刚性连接。 敲击中心之间的这种坚实的金属路径最大限度地减少了共模误差。

公开(公告)号：US4786905A

公开(公告)日：1988-11-22

申请号：US844046

申请日：1986-03-26

Applicant: Hans R. Muller

Inventor： Hans R. Muller

IPC: G01C21/16 ,  B64D43/00 ,  B64D45/00 ,  B64D45/08 ,  G01C23/00 ,  G05D1/06

CPC classification number: G05D1/0615 ,  G01C23/005

Abstract: An aircraft performance instrument which provides a first indicator which represents the line of level flight of the aircraft and a second indicator representative of the maximum permissible angle of attack of the aircraft.

Abstract translation: 一种飞机性能仪器，其提供代表飞机水平线的第一指示器和代表飞机最大允许迎角的第二指示器。

公开(公告)号：US4769645A

公开(公告)日：1988-09-06

申请号：US503219

申请日：1983-06-10

Applicant: Noel S. Paterson

Inventor： Noel S. Paterson

IPC: B64D45/04 ,  G01C5/00 ,  G08B21/00

CPC classification number: G01C5/005

Abstract: A system for warning the pilot of a rotary wing aircraft such as a helicopter of a flight condition that, if left uncorrected, would result in the tail of the aircraft striking the ground monitors the altitude above ground, descent rate, pitch and pitch rate of the aircraft and provides a warning if the relationship between the aforementioned parameters is such that a tail strike is imminent.

Abstract translation: 一种用于警告飞行员的飞行员的系统，例如飞行状态的直升机，如果未校正，将导致飞机撞到地面的尾部，监测地面高度，下降率，俯仰和俯仰速率 并且如果上述参数之间的关系使得尾巴撞击即将发生，则提供警告。

公开(公告)号：US4766768A

公开(公告)日：1988-08-30

申请号：US111984

申请日：1987-10-22

Applicant: Brian L. Norling ,  Craig J. Cornelius

Inventor： Brian L. Norling ,  Craig J. Cornelius

IPC: G01P15/09 ,  G01P15/097 ,  G01P15/10

CPC classification number: G01P15/097

Abstract: An accelerometer comprising a support (52) and a proof mass (40) mounted to the support by a flexure (50) or the like, such that the proof mass can rotate about a hinge axis (HA) perpendicular to sensitive axis (SA). An isolator (42) is also mounted to the support by an isolator suspension system (60, 62) that is relatively compliant for isolator movement parallel to a transducer axis (TA) normal to the hinge axis, and relatively noncompliant for isolator rotation about the hinge axis. Force transducers (80, 82) are connected between the isolator and the proof mass. The force transducers are parallel to the transducer axis, and positioned on opposite sides of the hinge axis from one another, such that rotation of the proof mass about the hinge axis puts one force transducer in tension and the other force transducer in compression. The isolator suspension system reduces the magnitude of common mode inputs, such as those caused by differential thermal expansion of the crystals with respect to other accelerometer components.

Abstract translation: 一种加速度计，包括支撑件（52）和通过挠曲件（50）等安装到支撑件上的检验质量块（40），使得检验物质可以围绕垂直于敏感轴线（SA）的铰链轴线（HA）旋转， 。 隔离器（42）也通过隔离器悬挂系统（60,62）安装到支撑件，隔离器悬挂系统（60,62）对于平行于垂直于铰链轴线的换能器轴线（TA）的隔离器移动是相对顺从的，并且相对不符合隔离器围绕 铰链轴。 力传感器（80,82）连接在隔离器和检测质量块之间。 力传感器平行于换能器轴线，并且彼此相对地定位在铰链轴线的相对侧上，使得校准质量块围绕铰链轴的旋转使一个力传感器处于张紧状态，另一个力传感器处于压缩状态。 隔离器悬挂系统减小了共模输入的大小，例如由晶体相对于其他加速度计组件的不同热膨胀引起的输入。

公开(公告)号：US4729102A

公开(公告)日：1988-03-01

申请号：US664157

申请日：1984-10-24

Applicant: Lawrence D. Miller, Jr. ,  Robert J. Owen ,  Richard M. Kiltz

Inventor： Lawrence D. Miller, Jr. ,  Robert J. Owen ,  Richard M. Kiltz

IPC: G01C23/00 ,  G01D9/00 ,  G06F20060101 ,  G06F11/30 ,  G06F13/00 ,  G06F17/40 ,  G11B5/02 ,  G06F15/74

CPC classification number: G07C5/085

Abstract: Disclosed is a combined flight data recorder data aquisition circuitry (10) and airborne integrated data circuitry (12) that can be variously packaged to supplement and update existing aircraft systems or serve as a standalone 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. 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: 公开了一种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），其可以进行各种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机程序，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：US4727752A

公开(公告)日：1988-03-01

申请号：US10799

申请日：1987-02-04

Applicant: Rex B. Peters

Inventor： Rex B. Peters

IPC: G01P15/097 ,  G01P15/10 ,  H03B5/32

CPC classification number: G01P15/097 ,  Y10S73/01

Abstract: A circuit (62, 64) for receiving a periodic input signal at frequency f, and for producing a pseudosinusoidal staircase output signal at a fundamental frequency f from which predetermined harmonics of the fundamental frequency are absent. Also provided are an oscillator in which such a circuit forms the drive circuit for a piezoelectric crystal, and an accelerometer in which such an oscillator is used as the force sensing means. In the accelerometer, the reaction force of a proof mass (40) is sensed by a resonator that comprises a drive circuit (44) for producing a drive signal and a piezoelectric crystal (42) connected between the proof mass and support (46). In response to the drive signal, the crystal undergoes mechanical vibration at a frequency f that varies with the force applied to the crystal. A resonator signal corresponding to the mechanical vibration is produced and input to drive circuit. The drive circuit responds by producing the drive signal in the form of a periodic, pseudosinusoidal staircase function. The staircase function has fundamental frequency f, and has N steps of M discrete nonzero amplitude levels per period. N and M are integers greater than one, with M being less than N. The drive circuit produces the M amplitude levels such that predetermined harmonics of the fundamental frequency f are not present in the drive signal, thereby reducing the possibility of activity dips in the accelerometer output.

Abstract translation: 一个电路（62,64），用于以频率f接收周期性的输入信号，并产生一个基本频率为f的伪神经阶梯阶梯输出信号，从基频不存在基频的预定谐波。 还提供了一种振荡器，其中这种电路形成用于压电晶体的驱动电路，并且其中使用这种振荡器作为力感测装置的加速度计。 在加速度计中，通过包括用于产生驱动信号的驱动电路（44）和连接在检测质量块（46）之间的压电晶体（42）的谐振器来检测检测质量块（40）的反作用力。 响应于驱动信号，晶体以随着施加到晶体的力而变化的频率f发生机械振动。 产生对应于机械振动的谐振器信号并将其输入到驱动电路。 驱动电路通过产生周期性，假性软件阶梯功能的形式的驱动信号作出响应。 楼梯功能具有基频f，并且每个周期具有M个离散非零幅度电平的N个步长。 N和M是大于1的整数，其中M小于N.驱动电路产生M个幅度电平，使得驱动信号中不存在基频f的预定谐波，从而降低了驱动信号中的活动下降的可能性 加速度计输出。

公开(公告)号：US4725811A

公开(公告)日：1988-02-16

申请号：US829731

申请日：1986-02-13

Applicant: Hans R. Muller ,  John H. Glover

Inventor： Hans R. Muller ,  John H. Glover

IPC: G01P13/00 ,  B64D45/00 ,  G01P7/00 ,  G05D1/06 ,  G08B23/00

CPC classification number: G05D1/0615

Abstract: A wind shear detection and alerting system (30) compares inertially derived accelerations with air speed rate to provide a wind shear warning signal. Inertially derived accelerations are used instead of purely inertial accelerations because purely inertial systems generally require a vertical gyro. By utilizing angle of attack (.alpha.) and flight path angle (.gamma.) instead of pitch angle (.theta.) in the calculation, no vertical gyro signal is required and the system will be responsive to vertical as well as horizontal shear conditions. An enhanced version of the system is also compensated for roll angle (.phi.), with the roll angle being derived from the rate of change of heading (.PSI.) to avoid the need for a vertical gyro. The alerting system is capable of providing visual and aural warnings for a variety of wind shear conditions, such as, head shear, tail shear, head shear followed by tail shear and wind shear trend. The waring system is also capable of providing a wind shear warning which is a function of the radio altitude of the aircraft.

Abstract translation: 风切变检测和警报系统（30）将惯性推导的加速度与空气速率进行比较，以提供风切变警告信号。 使用惯性导出的加速度代替纯惯性加速度，因为纯惯性系统通常需要垂直陀螺仪。 通过在计算中利用迎角（alpha）和飞行路径角（gamma）而不是桨距角（theta），不需要垂直陀螺仪信号，系统将对垂直和水平剪切条件做出响应。 系统的增强版本也可以针对侧倾角（phi）进行补偿，其中滚动角度取决于航向变化率（PSI），以避免需要垂直陀螺仪。 警报系统能够为各种风切变条件提供视觉和听觉警告，例如头剪，尾剪，头剪以及尾剪和风切变趋势。 起搏系统还能够提供与飞机的无线电高度相关的风切变警告。

公开(公告)号：US4712427A

公开(公告)日：1987-12-15

申请号：US908356

申请日：1986-09-17

Applicant: Rex B. Peters

Inventor： Rex B. Peters

IPC: G01P15/097 ,  G01P15/10

CPC classification number: G01P15/097

Abstract: A dual sensor, frequency output accelerometer that does not require either high sampling rates or mechanical matching of the sensors to achieve high levels of accuracy. In one embodiment, the accelerometer comprises a first sensor (12, 14, 16) that produces an output signal S.sub.1 having a frequency f.sub.1 related to acceleration along the sensitive axis, and a second sensor (18, 20, 22) that produces a second signal S.sub.2 having a frequency f.sub.2 related to acceleration along the sensitive axis, the sensors being arranged such that a given acceleration causes the frequency of one output signal to increase and the frequency of the other output signal to decrease. Velocity change .DELTA.V during time interval T is determined according to:.DELTA.V=A[.DELTA..phi.+FT+B.SIGMA..phi.]where A, F and B are constants, .DELTA..phi.is the difference between the phase changes of the output signals over time interval T, and .SIGMA..phi. is the sum of the phase changes of the output signals over time interval T. Higher order correction terms are also described for very high precision applications. Also disclosed is an accelerometer or measuring velocity change during a time interval that includes a subinterval during which electrical power is unavailable.

Abstract translation: 双传感器，频率输出加速度计，不需要高采样率或传感器的机械匹配来实现高水平的精度。 在一个实施例中，加速度计包括产生具有与沿着敏感轴的加速度相关的频率f1的输出信号S1的第一传感器（12,14,16）和产生第二传感器的第二传感器（18,20,22） 具有与沿着敏感轴的加速度相关的频率f2的信号S2，传感器被布置成使得给定的加速度使得一个输出信号的频率增加，另一个输出信号的频率降低。 时间间隔T内的速度变化DELTA V根据以下方式确定：DELTA V = A [DELTA phi + FT + B SIGMA phi]其中A，F和B是常数，DELTA phi是输出信号的相位变化之间的差异 时间间隔T，SIGMA phi是时间间隔T上的输出信号的相位变化的总和。对于非常高精度的应用，还描述了高阶校正项。 还公开了一种加速度计或在包括电力不可用的子间隔的时间间隔期间测量速度变化。

公开(公告)号：US4706259A

公开(公告)日：1987-11-10

申请号：US815352

申请日：1985-12-30

Applicant: Jerome M. Paros ,  Jeffrey F. Tonn ,  Richard B. Wearn, Jr.

Inventor： Jerome M. Paros ,  Jeffrey F. Tonn ,  Richard B. Wearn, Jr.

IPC: G01K7/32 ,  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.

Abstract translation: 用于音叉温度传感器的现有安装系统导致传感器工作范围内的不可预测的活动下降。 通过适用于将温度敏感音叉（20）安装到支撑结构的本发明的安装和隔离系统（32）来消除这个问题。 安装系统包括适于刚性连接到支撑结构的安装构件（34）和将音叉基座连接到安装构件的支撑装置（36），使得音叉仅由支撑装置支撑。 支撑装置包括仅传送小于音叉的频率的操作范围的振动频率的低通机械滤波器。

公开(公告)号：US4684948A

公开(公告)日：1987-08-04

申请号：US512208

申请日：1983-07-08

Applicant: Charles D. Bateman

Inventor： Charles D. Bateman

IPC: G01S13/93 ,  G01C5/00 ,  G01S13/91 ,  G01S13/94 ,  G08G5/00 ,  G08B23/00 ,  G05D1/06

CPC classification number: G01C5/005 ,  G01S13/94

Abstract: An aircraft ground proximity warning system having an excessive terrain closure warning mode and a below glide slope warning mode monitors the glide slope signal and modifies the terrain closure warning envelope to accept a lesser terrain clearance when the aircraft is within the glide slope beam.

Abstract translation: 具有过度地形闭合警告模式和下滑坡警告模式的飞机地面接近警戒系统监视滑翔坡度信号，并修改地形关闭警告信号，以在飞行器处于滑翔坡度波束内时接受较小的地形间隙。