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.

Inventor： NASLUND, Brian Brent ,  ANDERSON, Matthew Paul ,  LANGEMO, Benjamin John ,  SHERMAN, Andrew

IPC: G01P5/165 ,  G01P13/02

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：EP3581941A1

公开(公告)日：2019-12-18

申请号：EP19180677.7

申请日：2019-06-17

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： NASLUND, Brian Brent ,  LANGEMO, Benjamin John ,  ANDERSON, Matthew Paul ,  SHERMAN, Andrew

IPC: G01P5/165 ,  G01P13/02

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).

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.

Inventor： NASLUND, Brian Brent ,  LANGEMO, Benjamin John ,  ANDERSON, Matthew Paul ,  SHERMAN, Andrew

IPC: G01M3/02 ,  G01M3/28 ,  F16L55/10 ,  G01P5/16 ,  G01P13/02

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.

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.

Inventor： NASLUND, Brian Brent ,  SHERMAN, Andrew ,  LANGEMO, Benjamin John ,  ANDERSON, Matthew Paul

IPC: G01P5/26 ,  G01P13/02 ,  G01S17/58 ,  B64D43/02

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：EP3581940A1

公开(公告)日：2019-12-18

申请号：EP19180636.3

申请日：2019-06-17

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： NASLUND, Brian Brent ,  LANGEMO, Benjamin John ,  ANDERSON, Matthew Paul ,  SHERMAN, Andrew

IPC: G01P5/165 ,  G01P13/02

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).