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公开(公告)号：EP4086638A1
公开(公告)日：2022-11-09
申请号：EP22171382.9
申请日：2022-05-03
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： DAUP, Michael Robert , NASLUND, Brian Brent
Abstract: An aircraft pressure measurement device includes a pressure sensor (16), a pressure measurement path (14), a valve (18), and a fluid port (22). The pressure measurement path extends between an aircraft skin (12) and the pressure sensor, and the valve is positioned within the pressure measurement path between the aircraft skin and the pressure sensor. The valve is configured to regulate airflow through the pressure measurement path, and the fluid port is configured to allow a pressurized fluid into the pressure measurement path to clear the pressure measurement path of debris.
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公开(公告)号：EP3051295B1
公开(公告)日：2018-10-10
申请号：EP16152102.6
申请日：2016-01-20
Applicant: Rosemount Aerospace Inc.
Inventor： DAUP, Michael Robert , SHERMAN, Andrew
CPC classification number: G01F1/46 , G01L19/0007 , G01P5/14
Abstract: A tuned sensor system 2 is disclosed. The tuned sensor system may receive an unsteady pressure from an external environment via a pressure inlet port 6. The pressure may have a first component that is substantially static and a second component that varies at a relatively high frequency. The pressure inlet port 6 may conduct the unsteady pressure to a tuned path 8. The tuned path 8 may filter the unsteady pressure, blocking the second component and communicating the first component, such as for use by a pressure sensor. The tuned sensor system 2 may be compact and may include one or more turn in the tuned path 8 so that the distance between the pressure inlet port 6 and the sensor 10 is less than the length of the tuned path 8. The tuned path 8 may be entirely within the supporting structure of the tuned sensor system 2, easing installation, removal, and maintenance of the compact and modular system.
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公开(公告)号：EP3742146A1
公开(公告)日：2020-11-25
申请号：EP19215739.4
申请日：2019-12-12
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： DAUP, Michael Robert , POTASEK, David P.
Abstract: A micromechanical piezoresistive pressure sensor (40;340) includes a diaphragm (44) configured to mechanically deform in response to an applied load, a sensor substrate located on the diaphragm, and a number of piezoresistive resistance devices located on the sensor substrate. The piezoresistive resistance devices are arranged in a first planar array defining a grid pattern having two or more rows, each row being aligned in a first direction. The piezoresistive resistance devices are configured to be electrically connected in a number of bridge circuits (30), whereby the piezoresistive resistance devices in each row is electrically connected in an associated bridge circuit. A method of using the micromechanical piezoresistive pressure sensor is also disclosed.
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Patent Agency Ranking4.发明公开AIRCRAFT TOTAL AIR TEMPERATURE ANOMALY DETECTION 审中-公开DETEKTION VON FLUGZEUGGESAMTLUFTTEMPERATURANOMALIEN
公开(公告)号：EP3109608A1
公开(公告)日：2016-12-28
申请号：EP16175711.7
申请日：2016-06-22
Applicant: Rosemount Aerospace Inc.
Inventor： SCHWIE, Chester , DAUP, Michael Robert , NELSON, Jordan William
CPC classification number: G01K13/028 , G01K15/007
Abstract: An example method includes receiving, by a computing device (10), an indication of a measured total air temperature (TAT) (26) from a temperature probe installed on an aircraft. The method further includes determining, by the computing device (10), a theoretical temperature corresponding to conditions at which the TAT is measured, and determining, by the computing device, a measured TAT anomaly condition based on the measured TAT and the theoretical temperature corresponding to the conditions at which the TAT is measured.
Abstract translation: 示例性方法包括由计算设备（10）从安装在飞行器上的温度探测器接收测量的总空气温度（TAT）（26）的指示。 该方法还包括由计算装置（10）确定对应于测量TAT的条件的理论温度，以及由计算装置根据所测量的TAT和对应的理论温度来确定测量的TAT异常条件 到测量TAT的条件。
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公开(公告)号：EP3051295A1
公开(公告)日：2016-08-03
申请号：EP16152102.6
申请日：2016-01-20
Applicant: Rosemount Aerospace Inc.
Inventor： DAUP, Michael Robert , SHERMAN, Andrew
CPC classification number: G01F1/46 , G01L19/0007 , G01P5/14
Abstract: A tuned sensor system 2 is disclosed. The tuned sensor system may receive an unsteady pressure from an external environment via a pressure inlet port 6. The pressure may have a first component that is substantially static and a second component that varies at a relatively high frequency. The pressure inlet port 6 may conduct the unsteady pressure to a tuned path 8. The tuned path 8 may filter the unsteady pressure, blocking the second component and communicating the first component, such as for use by a pressure sensor. The tuned sensor system 2 may be compact and may include one or more turn in the tuned path 8 so that the distance between the pressure inlet port 6 and the sensor 10 is less than the length of the tuned path 8. The tuned path 8 may be entirely within the supporting structure of the tuned sensor system 2, easing installation, removal, and maintenance of the compact and modular system.
Abstract translation: 公开了一种调谐传感器系统2。 经调节的传感器系统可以经由压力入口6从外部环境接收不稳定的压力。该压力可以具有基本静态的第一分量和在较高频率下变化的第二分量。 压力入口6可以将非稳态压力传导到调谐路径8.调谐路径8可以过滤不稳定压力，阻塞第二部件并连通第一部件，例如由压力传感器使用。 调谐传感器系统2可以是紧凑的，并且可以包括调谐路径8中的一个或多个转弯，使得压力入口端口6和传感器10之间的距离小于调谐路径8的长度。调谐路径8可以 完全在调谐传感器系统2的支撑结构内，减轻了紧凑和模块化系统的安装，拆卸和维护。
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公开(公告)号：EP3822580A1
公开(公告)日：2021-05-19
申请号：EP20208432.3
申请日：2020-11-18
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： DAUP, Michael Robert , NASLUND, Brian Brent , MATHEIS, Brian Daniel
Abstract: Apparatus and associated methods relate to determining altitude of an aircraft during flight based on properties of vortex shedding. A vortex-shedding projection (14) is projected into the airstream adjacent to the exterior surface of the aircraft so as to cause vortex-shedding turbulence (36) of the airstream. One or more downstream sound-pressure detectors (16A - 16G), which are attached to the exterior surface of the aircraft downstream from the vortex-shedding projection, detect(s) a vortex-shedding frequency f of the vortex-shedding turbulence caused by the vortex-shedding projection. A processor (18) determines the altitude of the aircraft based, at least in part, on the vortex-shedding frequency f of the vortex-shedding turbulence as detected by the one or more downstream sound-pressure detectors.
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公开(公告)号：EP3715860A1
公开(公告)日：2020-09-30
申请号：EP19215206.4
申请日：2019-12-11
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： BOELKE, Joel , NASLUND, Brian Brent , LANGEMO, Benjamin John , DAUP, Michael Robert
Abstract: An air data system (100) with a digital interface (103)includes least one air data component (102a-q), a receiving system (104a-c) and at least one digital connection (106). The at least one digital connection is between the receiving system and the air data component. A method (200) for transmitting data in an air data system with a digital interface includes measuring (202) at least one air data parameter with at least one air data component. The method includes generating (204) a digital signal representative of the at least one air data parameter with the at least one air data component, sending (206) the digital signal to a receiving system, and processing (208) the at least one air data parameter with the receiving system.
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公开(公告)号：EP3428657A1
公开(公告)日：2019-01-16
申请号：EP18186554.4
申请日：2016-01-20
Applicant: Rosemount Aerospace Inc.
Inventor： DAUP, Michael Robert , SHERMAN, Andrew
Abstract: A tuned sensor system (2) is disclosed. The tuned sensor system may receive an unsteady pressure from an external environment via a pressure inlet port (6). The pressure may have a first component that is substantially static and a second component that varies at a relatively high frequency. The pressure inlet port (6) may conduct the unsteady pressure to a tuned path (8). The tuned path (8) may filter the unsteady pressure, blocking the second component and communicating the first component.
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