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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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2.发明公开
公开(公告)号：EP3581943A2
公开(公告)日：2019-12-18
申请号：EP19180014.3
申请日：2019-06-13
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： BOELKE, Joel , NASLUND, Brian Brent , LANGEMO, Benjamin John
Abstract: A system and method of augmenting an existing air data system includes a multi-function probe (MFP) (30; 58) having a portion extending into an oncoming airflow about an exterior of an aircraft (10). A plurality of pressure sensing ports in the portion includes at least first and second static pressure ports (P S1 ). A first electronics channel (34) of the MFP (30; 58) includes pressure sensors (46, 48, 50) communicating with the first and second static pressure ports (P S1 ) and is configured to determine first and second altitude values based on sensed static pressures at the first and second static pressure ports (P S1 ), respectively, that are independent of the existing air data system.
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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：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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Patent Agency Ranking
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：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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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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8.发明公开
公开(公告)号：EP3581943A3
公开(公告)日：2019-12-25
申请号：EP19180014.3
申请日：2019-06-13
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： BOELKE, Joel , NASLUND, Brian Brent , LANGEMO, Benjamin John
Abstract: A system and method of augmenting an existing air data system includes a multi-function probe (MFP) (30; 58) having a portion extending into an oncoming airflow about an exterior of an aircraft (10). A plurality of pressure sensing ports in the portion includes at least first and second static pressure ports (P S1 ). A first electronics channel (34) of the MFP (30; 58) includes pressure sensors (46, 48, 50) communicating with the first and second static pressure ports (P S1 ) and is configured to determine first and second altitude values based on sensed static pressures at the first and second static pressure ports (P S1 ), respectively, that are independent of the existing air data system.
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9.发明公开
公开(公告)号：EP3581938A1
公开(公告)日：2019-12-18
申请号：EP19175352.4
申请日：2019-05-20
Applicant: Rosemount Aerospace Inc.
Inventor： NASLUND, Brian Brent , BOELKE, Joel , LANGEMO, Benjamin John , BENNING, Kevin
Abstract: A system includes an air data computer (ADC) (48, 70, 88) having a single pneumatic port for receiving a pneumatic input, a plurality of electrical inputs for receiving one or more electrical signals, and an output. The ADC (48, 70, 88) can transmit, via the output, air data parameters based on the received pneumatic input and the received one or more electrical signals. In a further example embodiment, the system includes a first pressure sensing probe discrete from the ADC (48, 70, 88) and a pneumatic connection (52, 74, 92) joining a pressure sensing port of the first probe to the pneumatic input of the ADC (48, 70, 88). Second and third pressure sensing probes pneumatically coupled to respective pressure modules, which output electrical signals to the ADC (48, 70, 88), the electrical signals being representative of pressures sensed by the second and third pressure sensing probes, respectively.
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