公开(公告)号：US4970485A

公开(公告)日：1990-11-13

申请号：US273244

申请日：1988-11-18

Applicant: Karl H. Wahls

Inventor： Karl H. Wahls

IPC: H01H37/54

CPC classification number: H01H37/54

Abstract: A snap action thermal actuator utilizes a pair of mechanically coupled bimetallic members having different temperature characteristics to provide a fast and positive snap action thermal actuator even when a low temperature differential is required. The actuator is particularly useful for controlling the operation of electrical contacts in a thermal switch.

Abstract translation: 快速动作热致动器利用具有不同温度特性的一对机械耦合双金属构件，以便即使在需要低温差时也能提供快速且正向的快速动作热致动器。 致动器特别适用于控制热开关中电触点的操作。

公开(公告)号：US4914436A

公开(公告)日：1990-04-03

申请号：US35112

申请日：1987-04-06

Applicant: Charles D. Bateman ,  Michael M. Grove

Inventor： Charles D. Bateman ,  Michael M. Grove

IPC: G08B21/00 ,  G05D1/06 ,  G08G5/04

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 together with the surrounding terrain topography are modeled by a simple geometric shape, such as, an inverted truncated cone, and stored on-board the aircraft. The system uses navigational data 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 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 as a function of the aircraft's alignment with a particular runway.

Abstract translation: 公开了一种地面接近警报系统，其可以识别何时飞行器最终接近机场而不使用着陆挡板信号输入。 与周围地形地形一起的机场由简单的几何形状建模，例如倒立的截锥，并存储在飞机上。 该系统使用导航数据来确定飞机与几何模型的距离。 一旦飞行器被确定在由几何模型限定的区域之内，系统就提供一个启用信号，指示飞机处于最终方法，以实现各种地面接近警报系统。 还公开了一种用于根据飞机与特定跑道的对准来改变启用包络的系统。

公开(公告)号：US4905000A

公开(公告)日：1990-02-27

申请号：US34807

申请日：1987-04-03

Applicant: Charles D. Bateman

Inventor： Charles D. Bateman

IPC: G01P5/00 ,  B64D45/00 ,  G01P15/00 ,  G05D1/06 ,  G08B21/00 ,  G08B23/00

CPC classification number: G05D1/0615

Abstract: An instrument (10) is disclosed for an aircraft having a windshear warning system to vary the threshold alarm setting as a function of a thermodynamic property of the air and as a function of local geographic and seasonal conditions. Specifically, a function generator 16 and other circuitry is disclosed. The output from the function generator 16 and other circuitry is then added to a fixed threshold acceleration signal to produce a threshold alarm signal which has a value that is a function of the temperature of the air, in a basic embodiment.

Abstract translation: 公开了一种用于具有风切变警报系统的飞机的仪器（10），以根据空气的热力学性质和作为当地地理和季节条件的函数改变阈值报警设置。 具体地，公开了功能发生器16和其它电路。 然后，在基本实施例中，功能发生器16和其它电路的输出被添加到固定阈值加速度信号，以产生具有作为空气温度的函数的值的阈值警报信号。

公开(公告)号：US4901586A

公开(公告)日：1990-02-20

申请号：US316899

申请日：1989-02-27

Applicant: Graeme A. Blake ,  Brian L. Norling

Inventor： Graeme A. Blake ,  Brian L. Norling

IPC: G01L1/10 ,  G01L1/18 ,  G01P15/097 ,  G01P15/10

CPC classification number: G01P15/097 ,  G01L1/10 ,  G01L1/183 ,  Y10S73/01

Abstract: A dual vibrating beam force transducer having an electrostatic drive system. The transducer comprises a body having first and second generally parallel beams, coupled together at their ends. First and second electrodes are positioned adjacent to but not in contact with the respective beams. A drive circuit causes an oscillating voltage to be applied to the electrodes. The beams are thus subjected to electrostatic forces that cause the beams to oscillate in a vibration plane containing both beams. The mechanical resonance of the beams controls the oscillation frequency, such that the frequency is a function of a force exerted along the beams. An embodiment is also described in which the drive means is coupled directly to one of the beams.

Abstract translation: 具有静电驱动系统的双振动束力传感器。 换能器包括具有第一和第二大致平行的梁的主体，它们的端部联接在一起。 第一和第二电极定位成与各个光束相邻而不与其接触。 驱动电路使振荡电压施加到电极。 因此，光束受到静电力的作用，使得光束在包含两个光束的振动平面中振荡。 光束的机械谐振控制振荡频率，使得频率是沿着光束施加的力的函数。 还描述了一种实施例，其中驱动装置直接连接到一个梁。

公开(公告)号：US4872342A

公开(公告)日：1989-10-10

申请号：US222680

申请日：1988-07-21

Applicant: Richard A. Hanson ,  Rex B. Peters ,  Brian L. Norling ,  Edward A. Urbach

Inventor： Richard A. Hanson ,  Rex B. Peters ,  Brian L. Norling ,  Edward A. Urbach

IPC: G01P15/08 ,  G01P15/097 ,  G01P15/10

CPC classification number: G01P15/097 ,  G01P15/0888 ,  G01P2015/0828 ,  Y10T29/49007

Abstract: An accelerometer comprising a body (10, 16, 12), a proof mass (18, 30, 32), a mounting strucutre comprising flexures (20, 22) for mounting the proof mass to the body, and force sensing elements (34, 38). The flexures permit translational motion of the proof mass with respect to the body along a sensitive axis SA and rotation of the proof mass with respect to the body about a hinge axis HA that is perpendicular to the sensitive axis. Acceleration of the accelerometer along the sensitive axis results in translational motion of the proof mass along the sensitive axis. The force sensing elements reacts to such translational motion by producing a signal indicative of acceleration along the sensitive axis. In a preferred embodiment, the mounting structure comprises a pair of fused quartz flexures that are oppositely directed with respect to one another, and the force sensing elements comprise a pair of vibrating beam force transducers that are connected to the proof mass on opposite sides of the hinge axis from one another. The described assembly method for accelerometers comprises forming bridges between the proof mass and body, the bridges being removed after attachment of the force sensing elements.

Abstract translation: 1.一种加速度计，包括主体（10,16,12），检验质量块（18,30,32），安装结构，其包括用于将所述证明物质安装到所述主体的挠曲件（20,22），以及力传感元件（34， 38）。 挠曲件允许检测质量体沿着敏感轴线SA相对于身体的平移运动，并且证明物质相对于身体围绕垂直于敏感轴线的铰链轴线HA旋转。 加速度传感器沿着敏感轴的加速导致检测质量沿着敏感轴的平移运动。 力感测元件通过产生指示沿着敏感轴的加速度的信号来对这种平移运动做出反应。 在优选实施例中，安装结构包括相对于彼此相对地指向的一对熔融石英弯曲部，并且力感测元件包括一对振动梁力传感器，其连接到在 铰链轴彼此。 所描述的用于加速度计的装配方法包括在检验质量块和本体之间形成桥，桥接件在附接力感测元件之后被移除。

公开(公告)号：US4700910A

公开(公告)日：1987-10-20

申请号：US689950

申请日：1985-01-09

Applicant: Arthur R. Brady

Inventor： Arthur R. Brady

IPC: B64C25/02 ,  B64D43/00 ,  G01G3/12 ,  G01G19/07 ,  B64D47/00

CPC classification number: G01G19/07 ,  G01G3/12

Abstract: A mounting and mounting method for a sensor positioned within a tubular axle of an aircraft undercarriage which will provide an output voltage proportional to the angular deflection of an axle for computation of aircraft gross weight. The sensor is not affected by cross-sectional distortions of the tubular axle under loading, undersirable shear frictional effects at the interface between the sensor mounting and the tubular axle and differential angular deflections of the axle.The cylindrical mounting member for the sensor has a pair of O-rings adjacent opposite ends thereof which are positioned to space the periphery of the mounting member from the bore of the tubular axle and which are under radial compression and act to provide uniform radial compressive forces applied about the full circumferential periphery of the cylindrical mounting member and absorb distortions of the axle by elastic deformation thereof. At least one of the O-rings is axially compressed for increased radial compression between the cylindrical mounting and the tubular axle to further improve the action in immunizing the sensor from distortion effects in the axle and maintain the sensor in the desired position endwise of the tubular axle.In the method of mounting the sensor, the cylindrical mounting member which carries the sensor has a pair of O-rings associated therewith adjacent opposite ends thereof and this structure is inserted axially within the tubular axle. The O-rings are sized to achieve radial compression between the mounting member and the tubular axle and with one of the O-rings having additional axial force exerted thereagainst to increase the radial compression to improve the action of the O-rings and assure maintaining the location of the sensor axially of the tubular axle.

Abstract translation: 传感器的安装和安装方法，其位于飞行器底盘的管状轴内，该传感器将提供与用于计算飞行器总重量的轴的角度偏转成比例的输出电压。 传感器不受负载下的管状轴的横截面变形的影响，传感器安装件和管状轴之间的界面处的不希望的剪切摩擦效应以及轴的差异角度偏转。 用于传感器的圆柱形安装构件具有邻近其相对端的一对O形环，其位于将安装构件的周边与管状轴的孔隔开并且处于径向压缩之下并且用于提供均匀的径向压缩力 施加在圆筒形安装构件的整个圆周周围上，并通过其轴的弹性变形吸收轴的变形。 O形环中的至少一个被轴向压缩以在圆柱形安装件和管状轴之间增加径向压缩，以进一步改善免疫传感器对轴的变形作用的作用，并将传感器保持在管状件的最终位置 轴。 在安装传感器的方法中，承载传感器的圆柱形安装构件具有与其相对的两端相关联的一对O形环，并且该结构轴向地插入管状轴内。 O形环的尺寸设计成在安装构件和管状轴之间实现径向压缩，并且其中一个O形环具有施加的另外的轴向力，以增加径向压缩以改善O形环的作用，并且确保保持 传感器在管状轴的轴向位置。

公开(公告)号：US4665748A

公开(公告)日：1987-05-19

申请号：US789655

申请日：1985-10-21

Applicant: Rex B. Peters

Inventor： Rex B. Peters

IPC: G01C19/56 ,  G01C19/574 ,  G01C19/5776 ,  G01P3/46

CPC classification number: G01C19/574 ,  G01C19/56 ,  G01C19/5776

Abstract: An angular rate sensor comprising a pair of accelerometers that includes means for continuously nulling error signals resulting from misalignment of the accelerometers. The first accelerometer (10) has a first force sensing axis and produces a first output signal (a.sub.1) indicating acceleration along the first force sensing axis. The second accelerometer (12) has a second force sensing axis and produces a second output signal (a.sub.2) indicating acceleration along the second force sensing axis. The accelerometers are mounted by mounting means such that their force sensing axes are both parallel to a common sensing axis and such that the accelerometers can be moved along a vibration axis normal to the sensing axis. A signal generator (76) produces a periodic deive signal having a predetermined frequency, and drive means (80, 82, 84) connected to the mounting means is responsive to the drive signal for vibrating the first and second accelerometers along the vibration axis at the predetermined frequency. Signal processing means (104) receives the first and second output signals and generates a Coriolis signal representing the Coriolis acceleration along the sensing axis resulting from movement of the accelerometers along the vibration axis and rotation of the body about a rate axis normal to the vibration axis and to the sensing axis. The signal processing means includes the detection means (92) that receives the Coriolis signal and produces a feedback signal that is a function of those components of the Coriolis signal that are in phase with respect to the drive signal. The drive means includes means (80) for combining the feedback signal with the drive signal, such that the in phase components are continuously driven towards a null value.

Abstract translation: 角速率传感器包括一对加速度计，其包括用于连续归零由加速度计的未对准产生的误差信号的装置。 第一加速度计（10）具有第一力感测轴并且产生指示沿着第一力感测轴的加速度的第一输出信号（a1）。 第二加速度计（12）具有第二力感测轴，并产生指示沿着第二力感测轴的加速度的第二输出信号（a2）。 加速度计通过安装装置安装，使得它们的力感测轴线都平行于共同的感测轴线，并且使得加速度计可以沿着垂直于感测轴线的振动轴线移动。 信号发生器（76）产生具有预定频率的周期性去除信号，并且连接到安装装置的驱动装置（80,82,84）响应于驱动信号，用于在第一和第二加速度计沿着振动轴振动第一和第二加速度计 预定频率。 信号处理装置（104）接收第一和第二输出信号，并且产生科里奥利信号，其表示沿加速度传感器沿着振动轴的运动产生的沿感测轴的科里奥利加速度，并且主体围绕与振动轴垂直的速率轴线的旋转 和传感轴。 信号处理装置包括接收科里奥利信号并产生与相对于驱动信号同相的科里奥利信号的那些分量的函数的反馈信号的检测装置（92）。 驱动装置包括用于将反馈信号与驱动信号组合的装置（80），使得同相分量被连续地朝向空值驱动。

公开(公告)号：US4656585A

公开(公告)日：1987-04-07

申请号：US576538

申请日：1984-02-03

Applicant: Edward A. Stephenson

Inventor： Edward A. Stephenson

IPC: G01C21/00 ,  G01D9/00 ,  G06F3/05 ,  G06F17/00 ,  G06F17/40 ,  G06F15/20

CPC classification number: G01D9/005 ,  G07C5/085

Abstract: A data acquisition system for use in an aircraft flight data recorder receives multiple analog and discrete signals representative of various aircraft parameters. A single address command from the flight data recorder central processing unit (CPU) causes a first multiplexer to select a set of analog signals. Each selected analog signal is amplified by a gain factor under CPU control and passed to track-and-hold circuitry which holds a level of the amplified analog signal upon receipt of a suitable command. The held analog signal levels are passed to a second multiplexer which also receives a set of discrete signals selected by a third multiplexer in response to a CPU address command. A control sequencer sequentially passes each signal at the input of the second multiplexer through an analog-to-digital converter, with the resultant digital signal being loaded into memory. After either all the selected and processed analog signals or the selected discrete signals have been analog-to-digital converted and stored in memory, the control sequencer issues an interrupt signal to the CPU.

Abstract translation: 用于飞行器飞行数据记录器的数据采集系统接收代表各种飞机参数的多个模拟和离散信号。 来自飞行数据记录器中央处理单元（CPU）的单个地址命令使得第一多路复用器选择一组模拟信号。 每个选择的模拟信号在CPU控制下被增益因子放大，并被传送到跟踪和保持电路，该电路在接收到合适的命令时保持放大的模拟信号的电平。 保持的模拟信号电平被传递到第二多路复用器，该第二多路复用器还响应于CPU地址命令接收由第三多路复用器选择的一组离散信号。 控制顺控程序通过模数转换器顺序地通过第二多路复用器的输入端的每个信号，将所得的数字信号加载到存储器中。 在所有选定和处理的模拟信号或所选择的离散信号都经过模数转换并存储在存储器中之后，控制定序器向CPU发出一个中断信号。

公开(公告)号：US4647967A

公开(公告)日：1987-03-03

申请号：US823710

申请日：1986-01-28

Applicant: Robert K. Kirschner ,  Hans R. Muller

Inventor： Robert K. Kirschner ,  Hans R. Muller

IPC: B64D45/08 ,  G02B27/00 ,  G02B27/01 ,  H04N7/18 ,  G02B27/14 ,  G09G3/02

CPC classification number: G02B27/0101 ,  B60K2350/1064 ,  B60K2350/2052 ,  B60K2350/405 ,  G02B2027/0154 ,  G02B2027/0156 ,  G02B2027/0165 ,  G02B2027/0169

Abstract: An independent test sight is described for a pilot's head-up display (HUD). In one embodiment, the independent test site comprises a collimator assembly and an aligned periscope assembly. The collimator assembly comprises a source of light, a reticle, and a lens for projecting the image of the reticle. The periscope assembly comprises a rhomboid prism housed within the chassis of the HUD in such a manner that it can be pivoted from a stowed position to an erect position where it projects a reticle pattern in the field of view of the HUD combiner.

Abstract translation: 飞行员的平视显示（HUD）描述了独立的测试视野。 在一个实施例中，独立测试位置包括准直器组件和对准潜望镜组件。 准直器组件包括光源，光罩和投影掩模版图像的透镜。 潜望镜组件包括容纳在HUD的底架内的菱形棱镜，使得其可以从收起位置枢转到直立位置，在竖立位置，其在HUD组合器的视场中投影掩模版图案。

公开(公告)号：US4634987A

公开(公告)日：1987-01-06

申请号：US656257

申请日：1984-10-01

Applicant: David B. Nolte

Inventor： David B. Nolte

IPC: H03B19/00 ,  H03K5/00 ,  H03K5/1534 ,  G06G7/16 ,  H03K3/017

CPC classification number: H03K5/1534 ,  H03K5/00006

Abstract: VLF communication signals encoded in MSK format contain phase ambiguities that must be resolved in order to use such signals in navigation systems. The ambiguities are resolved by the present frequency multiplying device that in one embodiment operates to double the frequency of an input signal and mix the doubled input signal with a mixing signal to produce an output signal having first and second states. The device includes a transition detector (42) for generating a trigger signal in response to each low-to-high or high-to-low transition of the input signal that occurs when the output signal is in its second state, and a bistable circuit (44) for generating the output signal in response to the trigger signal and to a mixing signal. The bistable circuit responds to the trigger signal to cause the output signal to be in its first state, and responds to a periodic characteristic of the mixing signal to cause the output signal to be in its second state. The transition detector may comprise a positive edge triggered flip-flop (50) and a negative edge triggered flip-flop (52). The bistable means may comprise a third flip-flop (56) having the mixing signal connected to its clock input and the trigger signal connected to its clear input. The frequency doubling device may also include means (58) for selectively disabling the second flip-flop so that the frequency of the input signal is not doubled.

Abstract translation: 以MSK格式编码的VLF通信信号包含必须解决的相位模糊度，以便在导航系统中使用这种信号。 本发明的倍频装置解决了这种不确定性，在一个实施例中，该倍增装置将输入信号的频率加倍，并将双重输入信号与混合信号混合以产生具有第一和第二状态的输出信号。 该装置包括转换检测器（42），用于响应于当输出信号处于其第二状态时发生的输入信号的每个从低到高或高到低的转变来产生触发信号，以及双稳态电路 （44），用于响应于触发信号产生输出信号和混合信号。 双稳态电路响应于触发信号使输出信号处于其第一状态，并响应混频信号的周期特性，使输出信号处于第二状态。 转换检测器可以包括上升沿触发触发器（50）和负沿触发触发器（52）。 双稳态装置可以包括具有连接到其时钟输入的混合信号和连接到其清零输入的触发信号的第三触发器（56）。 倍频装置还可以包括用于选择性地禁用第二触发器使得输入信号的频率不加倍的装置（58）。