公开(公告)号：EP1491900A2

公开(公告)日：2004-12-29

申请号：EP04253847.0

申请日：2004-06-28

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： Seidel, Greg A. ,  Cronin, Dennis J. ,  Mette, John H. ,  Koosmann, Mark R. ,  Schmitz, James A. ,  Fedele, John R. ,  Kromer, Dana A.

IPC: G01P13/02 ,  G01P5/165

CPC classification number: B64D43/02 ,  G01K13/028 ,  G01P5/165 ,  G01P13/025

Abstract: A multi-function air data sensing probe has a strut that is mounted on an aircraft and extends laterally from the aircraft skin. The strut is supported on a base plate, and has a pitot pressure sensing tube at the outer end thereof, with a pitot port facing upstream, and also includes a passageway for total air temperature sensor including a forwardly facing inlet scoop that leads to a chamber in the strut that is laterally offset from the inlet scoop so that flow changes direction as it enters the chamber. The surface defining the change of direction between the scoop and the chamber is provided with bleed holes for bleeding off boundary layer air. A vane type air data sensor is mounted on a shaft that rotates freely and is supported on the strut, and is positioned to sense the relative air flow past the strut to determine changes of relative angles of such air flow. In addition, the strut has static pressure sensing ports on lateral sides thereof leading to a separate chamber on the interior of the strut.

Abstract translation: 多功能空气数据传感探头具有安装在飞机上并从飞行器皮肤横向延伸的支柱。 支柱支撑在基板上，并且在其外端具有皮托管压力传感管，皮托口面向上游，并且还包括用于总空气温度传感器的通道，其包括朝向前方的入口勺，其通向腔室 在从入口勺侧向偏移的支柱中，使得流进入室时流动改变方向。 限定勺子和腔室之间的方向变化的表面设置有用于排出边界层空气的排放孔。 叶片型空气数据传感器安装在自由旋转并被支撑在支柱上的轴上，并且被定位成感测通过支柱的相对空气流以确定这种空气流的相对角度的变化。 此外，支柱在其横向侧上具有静态压力感测端口，其通向支柱内部的单独的室。

公开(公告)号：EP1431241A2

公开(公告)日：2004-06-23

申请号：EP03104568.5

申请日：2003-12-05

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： Koch, Daniel, J ,  Keenan, David, R ,  Gephart, Greg, L

IPC: B81B3/00 ,  G12B21/02 ,  G01R3/00 ,  G01R1/073

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

Abstract: A method for making a probe finger structure (14) including the steps of providing a wafer or wafer portion having an upper layer (32), a lower layer (30) and an insulating or etch stop layer (34) located between the upper and lower layers. The method further includes the step of etching the lower layer to form a mounting portion, and etching the upper layer to form a plurality of probe fingers. The method also includes the step of locating an electrically conductive material (40) on each of the probe fingers.

Abstract translation: 一种用于制造探针指结构（14）的方法，包括以下步骤：提供具有上层（32），下层（30）和绝缘或蚀刻停止层（34）的晶片或晶片部分，位于上和 较低层。 该方法还包括蚀刻下层以形成安装部分的步骤，并且蚀刻上层以形成多个探针。 该方法还包括将导电材料（40）定位在每个探针上的步骤。

公开(公告)号：EP1348981A3

公开(公告)日：2003-11-19

申请号：EP03251639.5

申请日：2003-03-18

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： Jamieson, James R. ,  Ray, Mark D.

IPC: G01S17/93 ,  G01S7/486

CPC classification number: G01S7/4818 ,  B64D45/08 ,  G01C23/005 ,  G01P5/26 ,  G01S7/4812 ,  G01S7/4813 ,  G01S7/4817 ,  G01S7/483 ,  G01S7/486 ,  G01S7/51 ,  G01S17/42 ,  G01S17/58 ,  G01S17/87 ,  G01S17/88 ,  G01S17/933

Abstract: A distributed laser based obstacle awareness system for use on-board an aircraft comprises: a plurality of obstacle detecting sensors disposable at a corresponding plurality of locations of the aircraft for emitting laser energy from the aircraft into a predetermined region of space and for receiving return laser energy from an obstacle in the predetermined region of space; a laser source for emitting a laser beam along an optical path; and a plurality of bistatic optical channels. Each channel comprises a plurality of transmission fiber optic cables and at least one receiver fiber optic cable and extends from the laser source to a corresponding obstacle detecting sensor of the plurality to direct the laser beam from the optical path to its corresponding obstacle detecting sensor of the plurality for emission into the corresponding predetermined region of space; and a light detector. Return laser energy from an obstacle received by any one of the obstacle detecting sensors is propagated through the receiver fiber optic cable of the corresponding optical channel to the light detector for use in detection of the obstacle in the corresponding predetermined region of space. In one embodiment, an optical switch is disposed in the optical path to redirect the laser beam in a time sequence manner from the optical path to selected optical channels of the plurality.

公开(公告)号：EP1335194A1

公开(公告)日：2003-08-13

申请号：EP03008110.3

申请日：1999-07-27

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： Boggs, Bradley J. ,  Bang, Christopher A. ,  Just, Marcus S. ,  Stark, Kevin C.

IPC: G01L1/22 ,  G01L1/18 ,  G01L9/00

CPC classification number: G01L9/0055 ,  G01L1/18 ,  G01L1/2293

Abstract: A generally flexible strain gage comprises a strain sensing element, and a generally flexible substrate supporting the strain sensing element. The strain sensing element is made of single crystal or polycrystalline semiconducting material. The invention also includes a method for forming a generally flexible strain gage comprising the step of selecting a wafer having a portion of a base material and portion of a single crystal or polycrystalline semiconducting material located thereon. The method further comprises the steps of etching a strain sensing element out of the semiconducting material and forming a generally flexible substrate onto said sensing element.

Abstract translation: 通常柔性的应变片包括应变感测元件和支撑应变感测元件的大体柔性基底。 应变传感元件由单晶或多晶半导体材料制成。 本发明还包括一种用于形成大体上柔性的应变计的方法，包括选择具有一部分基材和位于其上的单晶或多晶半导体材料的部分的晶片的步骤。 该方法还包括以下步骤：从半导体材料中蚀刻应变感测元件，并将基本上柔性的衬底形成在所述感测元件上。

公开(公告)号：EP1293784A2

公开(公告)日：2003-03-19

申请号：EP02256143.5

申请日：2002-09-04

Applicant: Rosemount Aerospace Inc.

Inventor： Alwin, Steve F. ,  Cronin, Dennis J. ,  Foster, Roger D. ,  Amerson, Thomas D. ,  Skarohlid, Mark C.

IPC: G01P13/02

CPC classification number: G01P21/025 ,  G01P13/025

Abstract: A method of detecting errors in air data sensing systems having multi-function probes being used in combinations to define probe systems includes a step (A) of, for each probe system, making a first prediction of an aircraft parameter as a function of local angles of attack at two member probes of the particular system, and making a second prediction of the aircraft parameter as a function of local pressure ratios at the two member probes of the particular system. A step (B) is performed in which, for each of the probe systems, the first and second predictions of the aircraft parameter are compared to determine whether the first and second predictions are within a predetermined threshold of each other. Then, a step (C) is performed in which, for each of the probe systems, if the first and second predictions of the aircraft parameter are not within the predetermined threshold of each other, then the particular probe system is identified as having a malfunctioning member probe.

Abstract translation: 检测具有组合定义探测系统的多功能探测器的空气数据传感系统中的错误的方法包括：对于每个探测系统，对飞机参数的第一预测作为局部角度的函数进行步骤（A） 在特定系统的两个成员探针处的攻击，以及作为特定系统的两个成员探针处的局部压力比的函数的飞机参数的第二预测。 执行步骤（B），其中对于每个探测系统，比较飞行器参数的第一和第二预测以确定第一和第二预测是否在彼此的预定阈值内。 然后，执行步骤（C），其中对于每个探测系统，如果飞行器参数的第一和第二预测不在彼此的预定阈值内，则特定探测系统被识别为具有故障 成员探针。

公开(公告)号：EP1245251A2

公开(公告)日：2002-10-02

申请号：EP02252112.4

申请日：2002-03-25

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： Bachinski, Thomas J.

IPC: A62B18/00

CPC classification number: B64D10/00 ,  A62B9/006

Abstract: A mask (11) is shown which is used for providing air or oxygen for breathing. The mask (16) has a differential pressure sensor (30) for providing a signal to control oxygen or airflow to the mask (16). In one form the sensor is in the wall of the mask or in a wall of a supply tube, to sense the differences between ambient pressure, for example in the cabin (10) of an aircraft, and pressure in the breathing space (24) on the interior of the mask (16). Reduction in the pressure on the interior of the mask (16) can indicate that a pilot (12) is not receiving adequate oxygen, or is being subjected to stresses that may result in blackouts or red outs. The signal from the differential pressure sensor (30) is used to control the flow of oxygen to the mask (16), and also can be used for controlling the pressure of pressurized suits (14) worn by the pilot (12). The pressure sensor (30) output also can be used to maintain a higher pressure on the interior of the mask (16) to insure ambient air does not contaminate the air being breathed.

Abstract translation: 示出了用于提供空气或氧气用于呼吸的面罩（11）。 掩模（16）具有差压传感器（30），用于提供信号以控制氧气或气流到掩模（16）。 在一种形式中，传感器位于掩模的壁或供应管的壁中，以感测例如在飞行器的舱室（10）中的环境压力之间的差异和呼吸空间（24）中的压力， 在面罩（16）的内部。 降低掩模（16）内部的压力可以指示飞行员（12）没有接收到足够的氧气，或者受到可能导致停电或红灯熄灭的应力。 来自差压传感器（30）的信号用于控制到面罩（16）的氧气流，并且还可用于控制由飞行员（12）佩戴的加压套管（14）的压力。 压力传感器（30）输出也可以用于在掩模（16）的内部保持更高的压力，以确保环境空气不会污染被吸入的空气。

公开(公告)号：EP1221594A2

公开(公告)日：2002-07-10

申请号：EP02250017.7

申请日：2002-01-03

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： Hongerholt, Derrick D. ,  Haugen, Eric D. ,  Huss, Charles G. ,  Seidel, Greg A.

IPC: G01F23/296

CPC classification number: G01F25/0076 ,  G01F23/2962 ,  G01F25/0061

Abstract: A built-in test system for an ultrasonic liquid level sensor that includes a transducer assembly having an ultrasonic transducer, and a switch that will be actuated when the ultrasonic transducer is in intimate contact with a surface of a tank in which level is to be determined. Once the switch is actuated to indicate that the ultrasonic transducer is properly coupled to the surface, a test sequence is initiated to determine that the level of ultrasonic transmissions are above a certain desired threshold for a selected period of time, and after which the circuit looks for echoes to determine the depth of the liquid in the tank. Thereafter, the test sequence is repeated for each cycle of level sensing.

Abstract translation: 一种用于超声波液面传感器的内置测试系统，其包括具有超声波换能器的换能器组件，以及当超声换能器与待确定等级的坦克的表面紧密接触时将被致动的开关 。 一旦开关被启动以指示超声波换能器被适当地耦合到表面，则启动测试序列以确定超声波发射的电平在所选择的时间段内高于某个期望的阈值，之后电路看起来 用于回波以确定罐中液体的深度。 此后，对于电平感测的每个周期重复测试序列。

公开(公告)号：EP0932831A1

公开(公告)日：1999-08-04

申请号：EP97911799.0

申请日：1997-10-14

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： MUEHLHAUSER, Brett, A. ,  RANUM, Brian

IPC: G01P5

CPC classification number: G01P5/165 ,  G01P5/14

Abstract: An air data probe (10) such as a pitot probe, pitot-static probe, or total air temperature probe incorporates heaters (42) within the wall (30) of the device. The heater (42) is in the wall (30) of the probe (10) and extends from the base (12) of the probe (10) to the tip (18) of the probe (10) and surrounds a sampling chamber (24) in the probe (10) in a spiral pattern.

公开(公告)号：EP0737315A1

公开(公告)日：1996-10-16

申请号：EP95940523.0

申请日：1995-10-20

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： ORTIZ, Rafael A., Caparra Hts Sta ,  DALE, Theodore, Paul

IPC: G01F1 ,  G01P5

CPC classification number: G01F1/46 ,  G01P5/165

Abstract: An air data sensor strut (16) made of a single block of material has one side (20) finished in a smooth contour, and has grooves (26, 28, 30) in an opposite side of the strut (16) for receiving pressure carrying conduits (34, 36), or other elongated members such as a heater (40). The heater (40) and conduits (34, 36) are secured in place with a filling of potting material (29) and the open sides of the grooves (26, 28, 30) are finished after filling so that the desired contour is provided for the opposite side (21) of the strut (16). The strut (16) has a thin cross section because of the elimination of hollow interior spaces formed by spaced walls.

公开(公告)号：EP4528691A1

公开(公告)日：2025-03-26

申请号：EP24191146.0

申请日：2024-07-26

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： NASLUND, Brian B. ,  SANDU, Irina R. ,  EUCKEN, Douglas ,  SEGAL, Juan Martin

IPC: G08G5/00 ,  G06V20/58

Abstract: An airborne object detection system (103) can include one or more imaging devices (110) configured to be disposed on an aircraft and to produce imaging data of one or more portions of an environment surrounding the aircraft, and an object detection system (103) operatively connected to the one or more imaging devices (110) to receive the imaging data. The object detection system (103) can be configured to determine whether there are one or more collision risk objects in the imaging data that will or are likely to collide with the aircraft based on the imaging data. The object detection system (103) can be configured to determine a collision location on the aircraft that the one or more collision risk objects will or are likely to collide with.