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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：EP3611516A1
公开(公告)日：2020-02-19
申请号：EP19190617.1
申请日：2019-08-07
Applicant: ROSEMOUNT AEROSPACE INC.
Abstract: An aircraft probe (12) includes a base (24), a strut (22) that extends from the base (24), at least one port (26, 28, 30), and an electronics assembly insertable into the strut (22) and removable from the strut (22). The electronics assembly includes at least one pressure sensor (42a, 42b, 42c) that is pneumatically connected to the at least one port (26, 28, 30) to sense a first pressure when in the inserted position.
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公开(公告)号：EP3461538B1
公开(公告)日：2020-11-11
申请号：EP18197194.6
申请日：2018-09-27
Applicant: Rosemount Aerospace Inc.
Inventor： BENNING, Kevin , WESSER, Aaron , WIGEN, Scott , SHERMAN, Andrew
IPC: A62C4/00
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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：EP4001925A1
公开(公告)日：2022-05-25
申请号：EP21209679.6
申请日：2021-11-22
Applicant: ROSEMOUNT AEROSPACE INC.
Abstract: An air data system includes a laser emitter (74), a laser receiver (75), and an electronics module (72). The electronics module includes a processor (86) and computer-readable memory (88) encoded with instructions that, when executed by the processor, cause the laser to emit a coherent light pulse into a target volume locating within an exhaust flow aft of an aircraft. The laser receiver detects backscatter produced by the coherent light pulse interacting with the aft target volume, and the electronics module determines an air data parameter based on the backscatter and at least one of an engine parameter indicative of an engine condition of the aircraft and an aircraft parameter indicative of a state of the aircraft before outputting the air data parameter to a consuming system of the aircraft.
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Patent Agency Ranking
公开(公告)号：EP3581940A1
公开(公告)日：2019-12-18
申请号：EP19180636.3
申请日：2019-06-17
Applicant: ROSEMOUNT AEROSPACE INC.
Abstract: A system includes a probe (14; 114; 214) and a transducer (16; 116; 216). The probe (14; 114; 214) is detachable and includes a mount having an outlet (28; 128; 228) of a first gas path (24; 124; 224) extending through the probe (14; 114; 214) and a protrusion (32; 132; 232) extending away from the mount. The transducer (16; 116; 216) is configured to mate with the mount and includes a sealing feature (40; 140; 240) adjacent an inlet (38; 138; 238) of the second gas path (36; 136; 236) in fluid communication with the first gas path (24; 124; 224). When the mount of the probe (14; 114; 214) is adjacent the transducer (16; 116; 216), the protrusion (32; 132; 232) interacts with the sealing feature (40; 140; 240) such that the sealing feature (40; 140; 240) is in an open position to allow air to flow from the first gas path (24; 124; 224) into the second gas path (36; 136; 236). When the mount of the probe (14; 114; 214) is distant from the transducer (16; 116; 216), the sealing feature (40; 140; 240) is in a closed position to prevent contaminants from entering the second gas path (36; 136; 236).
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公开(公告)号：EP3461538A1
公开(公告)日：2019-04-03
申请号：EP18197194.6
申请日：2018-09-27
Applicant: Rosemount Aerospace Inc.
Inventor： BENNING, Kevin , WESSER, Aaron , WIGEN, Scott , SHERMAN, Andrew
IPC: A62C4/00
Abstract: A vented module includes a housing portion having a drainage side (30) and a drainage port (32) within the drainage side (30). The module further includes a flame arrestor (10; 110) including a first surface (12; 112) having a fluid inlet (18; 118), a second surface (14; 114) having at least one fluid outlet (24; 124), a labyrinth channel extending from the fluid inlet (18; 118) to the fluid outlet (24; 124), and at least one mesh screen (22; 122) disposed within the labyrinth channel. The flame arrestor (10; 110) is attached to the housing portion such that the drainage port (32) is aligned with the fluid inlet (18; 118).
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公开(公告)号：EP3581941A1
公开(公告)日：2019-12-18
申请号：EP19180677.7
申请日：2019-06-17
Applicant: ROSEMOUNT AEROSPACE INC.
Abstract: A system includes a probe (14; 314), a transducer (16; 316), and a sealing feature (40). The probe (14) is detachable and includes a first gas path (24) extending from a head (20) to a mount. The transducer (16; 316) is configured to mate with the mount and includes a second gas path (36) with an inlet (38) configured to be in fluid communication with the outlet (28) of the first gas path (24) when the transducer (16; 316) is mated with the mount and at least one sensor disposed along the second gas path (36). The sealing feature (40) includes a first membrane (366) configured to allow pressure to be conveyed from the first gas path (24) to the second gas path (36) when the transducer (16; 316) is mated with the mount while preventing contaminants from entering the second gas path (36) when the transducer is distant from the probe (14).
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公开(公告)号：EP3581909A1
公开(公告)日：2019-12-18
申请号：EP19180664.5
申请日：2019-06-17
Applicant: ROSEMOUNT AEROSPACE INC.
Abstract: A device (10) for use in a leak check test of an air data system (12) includes a device body (14), an opening (18) extending into the device body (14) with the opening (18) being configured to allow a probe (22) to be at least partially inserted into the opening (18), and walls (16) surrounding the opening (18) with the walls (16) being situated to seal a port (24) in the probe (22) such that air is prevented from flowing into or out of the port (24) while the probe (22) is inserted into the opening (18). A method of performing a leak check test includes covering the port (24) with the device (10) to seal the port (24), heating air within a gas path in the air data system (12), measuring the change in pressure of the air resulting from an increase in temperature of the air, and determining whether the air data system (12) is sealed depending on the change in pressure of the air.
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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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