公开(公告)号：JP2004205511A

公开(公告)日：2004-07-22

申请号：JP2003421863

申请日：2003-12-19

Applicant: Rosemount Aerospace Inc ,  ローズマウント エアロスペイス インコーポレイテッド

Inventor： KOCH DANIEL J ,  KEENAN DAVID R ,  GEPHART GREG L

IPC: B81B3/00 ,  G01Q70/06 ,  G01R1/073 ,  G01R3/00

CPC classification number: G01Q70/06 ,  G01R1/07342 ,  G01R1/0735 ,  G01R3/00

Abstract: PROBLEM TO BE SOLVED: To provide a prove finger structure which can be used for the various testing structures, and to provide a manufacturing method for the probe finger structure. SOLUTION: The manufacturing method of the probe finger structure comprises a preparation step, consisting of an upper layer, an under layer and a wafer or a wafer part having an insulation or an etching stop layer which is located between the upper layer and the under layer. The method includes a step which performs underlayer etching for forming a mounting part and further a step which performs an upper layer etching for forming the plural prove fingers. Furthermore, a step in which a conductive material is mounted in each probe finger is included. COPYRIGHT: (C)2004,JPO&NCIPI

Abstract translation: 要解决的问题：提供可用于各种测试结构的证明指状结构，并且提供用于探针手指结构的制造方法。 解决方案：探针手指结构的制造方法包括由上层，下层和晶片或具有绝缘或蚀刻停止层的晶片部分组成的制备步骤，所述绝缘或蚀刻停止层位于上层和 下层。 该方法包括进行用于形成安装部的底层蚀刻的步骤，以及进行用于形成多个指状指的上层蚀刻的步骤。 此外，包括其中将导电材料安装在每个探针中的步骤。 版权所有（C）2004，JPO＆NCIPI

公开(公告)号：WO2021236191A2

公开(公告)日：2021-11-25

申请号：PCT/US2021/019633

申请日：2021-02-25

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： SCHWARTZ, Richard, Alan ,  ANDERSON, Kaleb

IPC: G01P13/02 ,  B64D15/00 ,  B64D15/12 ,  B64D43/00 ,  B64D43/02 ,  B64D45/00 ,  G01C21/00

Abstract: An angle of attack sensor includes a housing having an open end and a closed end. A faceplate is positioned on the open end of the housing. The faceplate comprises an integral bearing support cage that extends into the housing and is configured to accept a first bearing and a second bearing, a periphery at an outer edge of the faceplate, a central opening, and an exterior surface extending from the periphery to the central opening. A vane assembly extends through the central opening of the faceplate. A vane shaft extends into the housing and is connected to the vane assembly, and a rotational position sensor is connected to the vane shaft.

公开(公告)号：WO2021236190A2

公开(公告)日：2021-11-25

申请号：PCT/US2021/019630

申请日：2021-02-25

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： WHALEN, Mackenzie ,  CUSHER, Aaron, A. ,  VALDES CHAVEZ, Armando ,  HANSON, Daniel ,  SCHWARTZ, Richard, Alan ,  JOHNSON, Wallace ,  KRUEGER, William, B. ,  ANDERSON, Kaleb

IPC: G01P13/02 ,  B64D15/00 ,  B64D43/00 ,  B64D43/02 ,  B64D45/00 ,  G01C21/00

Abstract: An angle of attack sensor includes a housing having an open end and a closed end, a faceplate positioned on the open end of the housing, the faceplate comprising a periphery at an outer edge of the faceplate, a central opening, and an exterior surface extending from the periphery to the central opening, and a vane assembly extending through the central opening of the faceplate. The exterior surface of the faceplate has a sloped profile from the periphery to the central opening.

公开(公告)号：WO2021173816A1

公开(公告)日：2021-09-02

申请号：PCT/US2021/019638

申请日：2021-02-25

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： VALDES CHAVEZ, Armando ,  ANDERSON, Luke ,  ANDERSON, Kaleb

IPC: G01P13/02 ,  B64D15/12 ,  B64D15/14 ,  B64D43/02 ,  B64D45/00 ,  G01C21/00

Abstract: An angle of attack sensor includes a housing and a faceplate. A vane assembly extends through a central opening of the faceplate and includes a vane. The vane comprises a root, a tip, a leading edge, a trailing edge, a first lateral face, and a second lateral face. The first lateral face and the second lateral face are symmetric about a chord of the vane and each have a forward section with an outer surface profile that is nonlinear and geometrically convex from the leading edge to a transition point at a tangent to the widest point of the geometrically convex outer surface profile and each have an aft section with an outer surface profile that extends out to form a diverging wedge shape from the transition point to the trailing edge.

公开(公告)号：WO2009009732A1

公开(公告)日：2009-01-15

申请号：PCT/US2008/069787

申请日：2008-07-11

Applicant: ROSEMOUNT AEROSPACE INC. ,  GRICHENER, Alexander ,  LIN, Chuang-Chia

Inventor： GRICHENER, Alexander ,  LIN, Chuang-Chia

IPC: B64D29/06 ,  E05B39/04

CPC classification number: E05B39/04 ,  B64D29/06 ,  E05C19/145 ,  Y10T292/0948

Abstract: The invention provides a sensor (100, 200) for determining when a latch (104) for securing an engine cowl (102) on an aircraft is secured by detecting the proximity of a latch hook (106) and a latch pin (108). The sensor includes a resonant circuit configured and adapted to transmit a status signal when the latch is in, a secured state. The sensor also includes a means for conveying status information of the latch to a location remote from the latch based on the status signal, the conveying means being operably connected to the resonant circuit. The invention also provides a method of determining when a latch is open or secured by detecting the proximity of a latch hook and a latch pin.

Abstract translation: 本发明提供一种传感器（100,200），用于确定何时通过检测闩锁钩（106）和闩锁销（108）的接近来确保用于固定飞机上的发动机罩（102）的闩锁（104）。 所述传感器包括谐振电路，所述谐振电路经配置并适于在所述锁存器处于稳定状态时发送状态信号。 传感器还包括用于基于状态信号将闩锁的状态信息传送到远离闩锁的位置的装置，该传送装置可操作地连接到谐振电路。 本发明还提供了一种通过检测闩锁钩和闩锁销的接近来确定闩锁何时打开或固定的方法。

公开(公告)号：WO2008077131A2

公开(公告)日：2008-06-26

申请号：PCT/US2007088226

申请日：2007-12-19

Applicant: ROSEMOUNT AEROSPACE INC ,  SANDNAS MATHEW L ,  AUSTIN GLENN ,  BUENZ MARK J ,  TEIGEN DANIEL ,  WILLIAMS WADE

Inventor： SANDNAS MATHEW L ,  AUSTIN GLENN ,  BUENZ MARK J ,  TEIGEN DANIEL ,  WILLIAMS WADE

IPC: G01K13/02

CPC classification number: G01K13/02 ,  G01K13/028

Abstract: A total air temperature sensor includes a probe secured to a first side of a vehicle surface. The probe includes an air inlet and a temperature sensing element. Air flows into the air inlet and passes by the temperature sensing element. The temperature sensing element produces a temperature sensing element electrical signal as a function of a temperature of the air. The total air temperature sensor also includes an electronics package secured to a second side of the vehicle surface. Electronics in the electronics package receive the temperature sensing element electrical signal from the temperature sensing element and determine a total air temperature as a function of the temperature sensing element electrical signal.

Abstract translation: 总空气温度传感器包括固定到车辆表面的第一侧的探针。 探头包括一个进气口和一个感温元件。 空气流入进气口并通过温度感测元件。 温度感测元件根据空气的温度产生温度感测元件电信号。 总空气温度传感器还包括固定到车辆表面的第二侧的电子组件。 电子组件中的电子装置接收来自温度感测元件的温度感测元件电信号并根据温度感测元件电信号确定总空气温度。

公开(公告)号：WO2008036701A3

公开(公告)日：2008-03-27

申请号：PCT/US2007/078831

申请日：2007-09-19

Applicant: ROSEMOUNT AEROSPACE INC. ,  GUO, Shuwen ,  ERIKSEN, Odd Harald, Steen ,  POTASEK, David, P. ,  CHILDRESS, Kimiko J.

Inventor： GUO, Shuwen ,  ERIKSEN, Odd Harald, Steen ,  POTASEK, David, P. ,  CHILDRESS, Kimiko J.

IPC: G01L9/00

Abstract: A harsh environment transducer including: - a substrate (14) having a first surface and a second surface, the latter being exposed to the environment - a device layer sensor means (12) on the substrate (14) for measuring a parameter associated with the environment, including a single crystal semiconductor material having a thickness of less than about 0.5 microns - an output (50) contact on the substrate (14) and in electrical communication with the sensor means (12) - a package having an internal space communicating with the environment and receiving the substrate (14) such that its first surface is substantially isolated from the environment and its second surface is substantially exposed to the environment - a connecting component (22) coupled to the package - a wire (24) electrically connecting the connecting component (22) and the output contact (50) such that an output of the sensor means can be communicated. The external surface of the wire (24) and at least one of the output contact (50) and the connecting component (22) is substantially platinum.

公开(公告)号：WO2007130954A3

公开(公告)日：2007-11-15

申请号：PCT/US2007/067899

申请日：2007-05-01

Applicant: ROSEMOUNT AEROSPACE INC. ,  BOVITZ, David, J.

Inventor： BOVITZ, David, J.

IPC: H02M3/335

Abstract: An aircraft device power supply is capable of connecting to either an AC or a DC power bus provided on an aircraft. When connected to an aircraft's AC power bus, an AC power signal is EMI-filtered, stepped down in voltage to the same voltage as that of the DC power bus, and then rectified. When connected to an aircraft's DC power bus, a DC power signal is EMI-filtered before it is merged with the rectified AC power signal via an AC/DC switchover subcircuit. The output of the AC/DC switchover subcircuit is input to a power factor correction subcircuit which outputs a boosted DC voltage, regardless of which of the AC or DC aircraft power buses is connected to the power supply. A step down converter reduces the boosted DC voltage to a lower, system voltage which may then be further reduced or modified, as appropriate for device to be powered.

公开(公告)号：WO2007130954A2

公开(公告)日：2007-11-15

申请号：PCT/US2007067899

申请日：2007-05-01

Applicant: ROSEMOUNT AEROSPACE INC ,  BOVITZ DAVID J

Inventor： BOVITZ DAVID J

IPC: H02H9/06

CPC classification number: H02M1/4225 ,  H02M1/10 ,  H02M2001/007 ,  Y02B70/126 ,  Y10T307/675

Abstract: An aircraft device power supply is capable of connecting to either an AC or a DC power bus provided on an aircraft. When connected to an aircraft's AC power bus, an AC power signal is EMI-filtered, stepped down in voltage to the same voltage as that of the DC power bus, and then rectified. When connected to an aircraft's DC power bus, a DC power signal is EMI-filtered before it is merged with the rectified AC power signal via an AC/DC switchover subcircuit. The output of the AC/DC switchover subcircuit is input to a power factor correction subcircuit which outputs a boosted DC voltage, regardless of which of the AC or DC aircraft power buses is connected to the power supply. A step down converter reduces the boosted DC voltage to a lower, system voltage which may then be further reduced or modified, as appropriate for device to be powered.

Abstract translation: 飞机设备电源能够连接到飞机上提供的AC或DC电源总线。 当连接到飞机的交流电源总线时，对交流电源信号进行EMI滤波，降压至与直流电源总线相同的电压，然后进行整流。 当连接到飞机的直流电源总线时，直流电源信号经过AC / DC切换子电路与整流的交流电源信号合并之前被EMI滤波。 AC / DC切换子电路的输出被输入到输出升压的DC电压的功率因数校正子电路，而不管AC或DC飞行器电源总线中哪一个连接到电源。 降压转换器将升压的直流电压降低到较低的系统电压，然后可以进一步减小或修改，以适用于要供电的设备。

公开(公告)号：WO2005043264A3

公开(公告)日：2006-03-02

申请号：PCT/US2004027443

申请日：2004-08-24

Applicant: ROSEMOUNT AEROSPACE INC ,  BUENZ MARK J ,  NORLIEN JOHN A ,  KUNIK WILLIAM G ,  WILLIAMS WADE W ,  MYHRE DOUGLAS C

Inventor： BUENZ MARK J ,  NORLIEN JOHN A ,  KUNIK WILLIAM G ,  WILLIAMS WADE W ,  MYHRE DOUGLAS C

IPC: B60C23/04

CPC classification number: G01P3/44 ,  B60C23/0428 ,  B60C23/043 ,  B60C2200/02 ,  G01P3/48

Abstract: A wireless tire pressure sensing system for an aircraft comprises: dual resonant circuits mounted to a wheel of the aircraft, each resonant circuit comprising: a variable capacitance sensor (16) and a wire loop (12) of a predetermined inductance coupled thereto, one capacitance sensor for monitoring the pressure of a tire mounted to the wheel, and the other capacitance sensor operative as a reference to the one capacitance sensor; an interrogating circuit (18) magnetically coupleable to the dual resonant circuits and operative to induce magnetically a variable frequency current in the dual resonant circuits, the one resonant circuit responding to the induced current with an E-field signal at a first resonant frequency commensurate with the capacitance of the one sensor, and the other resonant circuit responding to the induced current with an E-field signal at a second resonant frequency commensurate with the capacitance of the other sensor; a receiving circuit (20) E-field coupleable to the dual resonant circuits and operative to receive the E-field signals at the first and second resonant frequencies and to generate first and second signals representative thereof; and a processing circuit coupled to the receiving circuit for processing the first and second signals to generate a compensated pressure reading of the tire. The pressure sensing system may be modified to provide and/or include wheel speed sensing.

Abstract translation: 一种用于飞行器的无线轮胎压力感测系统，包括：安装到飞行器的车轮的双重谐振电路，每个谐振电路包括：可变电容传感器（16）和与其耦合的预定电感的线环（12），一个电容 传感器，用于监测安装在车轮上的轮胎的压力，另一个电容传感器作为参考一个电容式传感器; 一个询问电路（18），磁性地耦合到双谐振电路并且可操作以在双谐振电路中磁力地感应可变频率电流，一个谐振电路响应感应电流，其中第一谐振频率的E场信号与 一个传感器的电容和另一个谐振电路响应感应电流，其中第二谐振频率的电场信号与另一传感器的电容相称; 接收电路（20），电场耦合到所述双谐振电路并且可操作以在所述第一和第二谐振频率处接收所述电场信号并产生表示其的第一和第二信号; 以及耦合到接收电路的处理电路，用于处理第一和第二信号以产生轮胎的补偿压力读数。 压力感测系统可以被修改以提供和/或包括轮速感测。