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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：EP4067911A1
公开(公告)日：2022-10-05
申请号：EP22155691.3
申请日：2022-02-08
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： ANDERSON, Kaare Josef , ESSAWY, Magdi
Abstract: Apparatus (22) and associated methods relate to predicting failure and/or estimating remaining useful life of an air-data-probe heater. Failure is predicted or useful life is estimated based on an electrical metric of the electrical operating power provided to a resistive heating element (24) of the air-data-probe heater. The electrical metric of the air data probe heater is one or more of: i) phase relation between voltage across the resistive heating element and leakage current, which is conducted from the resistive heating element to a conductive sheath surrounding the resistive heating element; ii) a time-domain profile of leakage current through the heating element insulation during a full power cycle; and/or iii) high-frequency components of the electrical current conducted by the resistive heating element and/or the voltage across the resistive heating element.
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公开(公告)号：EP4063816A1
公开(公告)日：2022-09-28
申请号：EP22163304.3
申请日：2022-03-21
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： POTASEK, David P. , PHILLIPS, Richard William
Abstract: A temperature sensor assembly for measuring a gas temperature in a gas flow stream includes a first substrate having a first surface configured to be connected to a thermally conductive structure in a gas path, a first temperature sensor mounted to the first substrate a first distance from the first surface, and a second temperature sensor mounted to the first substrate a second distance from the first surface. The second distance is less than the first distance. The first and second temperature sensors are arranged along a temperature gradient.
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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.
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公开(公告)号：EP3922318A3
公开(公告)日：2022-04-20
申请号：EP21178163.8
申请日：2021-06-08
Applicant: Rosemount Aerospace Inc.
Inventor： CHRISTENSON, John Carl
IPC: A62B7/12
Abstract: A personal protective positive pressure device includes a mask (20) with an inlet connector (34) and a tube (18) with a first connector (38) and a second connector (40). The tube (18) is connected through the first connector to the inlet connector of the mask and the tube is connected through the second connector to an air nozzle of a ventilation system onboard a transportation vehicle. The personal protective positive pressure device is configured to limit inhalation of airborne pathogens while traveling on the transportation vehicle and to inspire confidence in the safe use of public transportation.
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Patent Agency Ranking
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.
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公开(公告)号：EP3907531A2
公开(公告)日：2021-11-10
申请号：EP21168420.4
申请日：2021-04-14
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： RAY, Mark , JACKSON, Darren G.
Abstract: Apparatus and associated methods relate to a system for detecting foreign object debris ingested into an aircraft engine. The system detects such foreign object debris by projecting a beam of light over an inlet (18) of the aircraft engine (14). When foreign object debris is ingested into the aircraft engine, it intercepts the beam of light and scatters a back-scattered portion of the intercepted beam of light. An optical detector (24) is configured to detect the back-scattered portion of the intercepted beam of light. A processor is configured to determine whether foreign object debris is ingested by the aircraft engine based on a comparison of a threshold value with a signal indicative of the back-scattered portion generated by the optical detector.
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公开(公告)号：EP3885065A1
公开(公告)日：2021-09-29
申请号：EP21164414.1
申请日：2021-03-23
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： PITERA, Rudy , WIGAN, Scott , JOHNSON, Paul Robert , CHOU, Ryan Philip
IPC: B22F10/20 , B22F10/25 , B22F12/17 , B22F12/30 , B23K26/342 , B33Y10/00 , B33Y30/00 , B22F7/06 , B22F7/08
Abstract: A system used to additively manufacture an object layer-by-layer using direct energy deposition (DED) includes a base (12) where the object is formed, a depositor (14) configured to deposit material layer-by-layer on the base or a previously deposited layer of the object, an energy source (16) configured to selectively direct an energized beam (18) at the material to fuse a new layer of the material to a previously formed layer, and a heating element (20) in contact with at least a portion of the base and configured to supply heat to the base.
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公开(公告)号：EP3883337A1
公开(公告)日：2021-09-22
申请号：EP21163469.6
申请日：2021-03-18
Applicant: Rosemount Aerospace Inc.
Inventor： JACOB, Robin , MAHAPATRA, Guru Prasad
Abstract: A hybrid heater system for an aircraft air data sensor includes a voltage source (46) and a first hybrid heater set (42). The first hybrid heater set includes a carbon nanotube (CNT) heater (28), a first positive temperature coefficient (PTC) heater disposed in parallel with the CNT heater (28) to form a parallel formation, and a second PTC heater disposed in series between the voltage source (46) and the parallel formation.
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公开(公告)号：EP3872468A1
公开(公告)日：2021-09-01
申请号：EP21159756.2
申请日：2021-02-26
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： HOLL, Andy , WIGEN, Scott , SABLE, Robert E. , ISEBRAND, Scott D. , BOYD, Brian
Abstract: A sensor includes an airfoil body (104), a heater element (134), and a temperature probe (158). The airfoil body (104) defines a sensor axis, an insulating cavity (172), and extends between a leading edge and a trailing edge of the airfoil body. The heater element (134)extends axially within the airfoil body and is positioned between the leading edge and the trailing edge of the airfoil body. The temperature probe extends axially within the airfoil body, is positioned between the heater element and the trailing edge of the airfoil body, and is separated from the heater element by the insulating cavity to limit thermal communication between the temperature probe and the heater element. Gas turbine engines, methods of making sensors, and methods of thermally separating temperature probes and heater elements in sensors are also described.
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