-
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.
-
公开(公告)号：EP3971586A2
公开(公告)日：2022-03-23
申请号：EP21197741.8
申请日：2021-09-20
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： NASLUND, Brian Brent , KANE, Brian D. , SCHAUB, Steven
Abstract: An angle of attack sensor includes a rotatable vane (12) away and support from a mounting plate (68), a housing (36) extending way from an opposite side of the mounting plate, and a sensor (10) coupled to the vane. The angle of attack sensor communicates with an electronics module enclosed within the housing or mounted remotely with respect to the angle of attack sensor. The electronics module (72) includes a processor (88), computer-readable memory (90), and a communication device (92). The computer-readable memory is encoded with instructions that, when executed by the processor, cause the electronics module to perform steps of a damage detection method.
-
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).
-
公开(公告)号：EP4495013A3
公开(公告)日：2025-03-12
申请号：EP24209542.0
申请日：2021-09-20
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： NASLUND, Brian Brent , KANE, Brian D. , SCHAUB, Steven , MATHEIS, Brian Daniel
Abstract: An angle of attack sensor includes a mounting plate (68); a vane (12) supported from the mounting plate and extending from a first side of the mounting plate, wherein the vane is rotatable about a vane axis; a housing (36) extending from a second side of the mounting plate in a direction opposite to the vane; a resolver (64) coupled to the vane; and an electronics module (72) mounted within the housing, the electronics module comprising: at least one processor (88); a communication device (92); and computer-readable memory (90), encoded with instructions that, when executed by the at least one processor, cause the electronics module to: receive, from the resolver, a signal indicative of an angular position of the vane about the vane axis; compare the signal to a first damage criterion; and output, using the communication device, a first fault signal to a consuming system of an aircraft that is indicative of a damage event based on a comparison of the signal to the first damage criterion..
-
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.
-
Patent Agency Ranking
公开(公告)号：EP3971586A3
公开(公告)日：2022-06-08
申请号：EP21197741.8
申请日：2021-09-20
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： NASLUND, Brian Brent , KANE, Brian D. , SCHAUB, Steven
Abstract: An angle of attack sensor includes a rotatable vane (12) away and support from a mounting plate (68), a housing (36) extending way from an opposite side of the mounting plate, and a sensor (10) coupled to the vane. The angle of attack sensor communicates with an electronics module enclosed within the housing or mounted remotely with respect to the angle of attack sensor. The electronics module (72) includes a processor (88), computer-readable memory (90), and a communication device (92). The computer-readable memory is encoded with instructions that, when executed by the processor, cause the electronics module to perform steps of a damage detection method.
-
公开(公告)号：EP3926346A1
公开(公告)日：2021-12-22
申请号：EP21180693.0
申请日：2021-06-21
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： ROESKE, Cal , KUNIK, William , NASLUND, Brian Brent , BALASUBRAMANIAN, Rameshkumar
Abstract: A method of inspecting an air data (10) probe for damage or misalignment on a mounting surface includes retrieving reference data for the air data probe from a database, capturing images of the air data probe via a camera (30) and generating dimensions from the captured images of the air data probe via a feature extractor (50). An alignment calculator (52) analyzes the generated dimensions from the captured images of the air data probe and the reference data for the air data probe from the database to identify misalignment of the air data probe, and analyzes the generated dimensions from the captured images of the air data probe and the reference data for the air data probe from the database to identify damage of the air data probe. A maintenance recommendation for the air data probe is generated and outputted, based on the identified misalignment or damage of the air data probe.
-
公开(公告)号：EP3677922A1
公开(公告)日：2020-07-08
申请号：EP19218977.7
申请日：2019-12-20
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： KUNIK, William , NASLUND, Brian Brent , BRAUN, Scott J.
IPC: G01P5/165 , G01P21/02 , G06K9/78 , G06T7/00 , G01N21/956
Abstract: Inspecting an air data probe for physical degradation includes generating a silhouette (64) of the air data probe (12) based on an identification of the air data probe to be inspected. The silhouette is simultaneously displayed with an image (66) of the air data probe produced by a camera (18), and the displayed image of the air data probe is caused to conform to the silhouette on the display (20). An image of the air data probe is captured while the displayed image of the air data probe conforms to the silhouette on the display. The captured image is analyzed to identify physical degradation of the air data probe. A maintenance recommendation for the air data probe is generated based on the identified physical degradation.
-
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.
-
公开(公告)号：EP3594696A1
公开(公告)日：2020-01-15
申请号：EP19186094.9
申请日：2019-07-12
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： SLY, Jaime , NASLUND, Brian Brent
Abstract: A system and method for an aircraft (50) includes a low profile pneumatic sensing system and an acoustic sensing system. The low profile pneumatic sensing system includes a pneumatic sensor (30; 52a, 52b) positioned to sense first sensed data of an airflow about an exterior of the aircraft (50) and does not extend beyond a boundary layer of the aircraft (50). The first sensed data is used to determine first air data parameters. The acoustic sensing system is configured to emit acoustic signals about the exterior of the aircraft (50) and sense the acoustic signals as second sensed data. The second sensed data is used to determine second air data parameters.
-
-
-
-
-
-
-
-
-
Search Results
31
records
(took 0.027 seconds)
