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公开(公告)号：EP4027159A1
公开(公告)日：2022-07-13
申请号：EP22150027.5
申请日：2022-01-03
Applicant: Rosemount Aerospace Inc.
Inventor： ESSAWY, Magdi A. , QUY, Dennis A.
IPC: G01R31/52
Abstract: Apparatus and associated methods relate to detecting leakage current in a powered electrical system. Leakage current is detected by comparing a high-frequency response signal with a high-frequency reference signal. A high-frequency excitation signal is coupled, via an inducer (32), into the powered electrical system at a first location. The high-frequency response signal is sensed, via a signal sensor (34), at a second location of the powered electrical system. Because the electrical dynamics of the powered electrical system can change in response to system degradation that results in leakage current, changes in the high-frequency response signal can be indicative of leakage. Thus, the high-frequency response signal is compared, by a controller (36), with a high-frequency reference signal. The high-frequency reference signal can be a high-frequency response signal obtained at a reference time, at which the powered electrical system is operating without leakage.
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2.发明公开
公开(公告)号：EP3671223A1
公开(公告)日：2020-06-24
申请号：EP19216159.4
申请日：2019-12-13
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： ESSAWY, Magdi A. , BUI, Minh , GASSER, John D.
Abstract: A system for an aircraft includes a heater (14) comprising a resistive heating element (22) and insulation (24) surrounding the resistive heating element (22). A first current (I 1 ) flows into the resistive heating element (22) to provide heat and a second current (I 2 ) flows out of the resistive heating element (22). The system further includes a leakage sensor (17C) configured to produce a leakage sensor signal (V L ) representing a leakage current (I L ) from the heater (14) and a prediction processor (20) configured to predict heater failure based on the leakage sensor signal (V L ).
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3.发明公开
公开(公告)号：EP4067909A1
公开(公告)日：2022-10-05
申请号：EP22163589.9
申请日：2022-03-22
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： ANDERSON, Kaare Josef , ESSAWY, Magdi A.
Abstract: Apparatus 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 (24) and leakage current, which is conducted from the resistive heating element (24) to a conductive sheath (36) surrounding the resistive heating element (24); 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 (24) and/or the voltage across the resistive heating element (24).
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公开(公告)号：EP4109108A1
公开(公告)日：2022-12-28
申请号：EP22180108.7
申请日：2022-06-21
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： VALLAMKONDU, Aswin Kumar , ANNAMAREDDY, Ramesh , ESSAWY, Magdi A. , QUY, Dennis A.
Abstract: Apparatus and associated methods relate to monitoring health of a system for sensing rotational frequency of a rotatable member. A plurality of magnetic speed probes (20A - 20C), each of which is configured to sense the rotational frequency of the rotatable member, are arranged in transmissive proximity with one another. A transmitter-configured one of the plurality of magnetic speed probes includes a signal coupler (24A) that couples an electrical signal generated by a radio-frequency signal generator (18) into the inductive coil of the transmitter-configured magnetic speed probe, thereby radiatively transmitting an electromagnetic signal. A speed-probe monitor (22) electrically coupled to each of the plurality of magnetic speed probes determines, based on the coil current sensed by each of the plurality of magnetic speed probes in response to the electromagnetic signal radiatively transmitted, health of the system.
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公开(公告)号：EP3885777A1
公开(公告)日：2021-09-29
申请号：EP21164413.3
申请日：2021-03-23
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： ESSAWY, Magdi A. , HUYNH, Cuong Tho , ONKEN, Marvin G.
Abstract: A system and method for monitoring leakage current in a heater (20) connected to a heater power supply by a power cable (14) having a first power lead (16) conducting an inlet current defining an inlet current direction and a second power lead conducting an outlet current defining an outlet current direction that is opposite the inlet current direction. The system includes a differential current electromagnetic sensor (50) having a magnetic core (52) with a center region (54) that the power cable passes through one or more times. The magnetic core has an air gap (58) in which a magnetic flux sensing device is positioned and configured to provide a signal that is representative of magnetic flux across the air gap, which is indicative of a difference between the inlet current and the outlet current. This difference defines the leakage current.
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Patent Agency Ranking
公开(公告)号：EP3467538A1
公开(公告)日：2019-04-10
申请号：EP18197258.9
申请日：2018-09-27
Applicant: Rosemount Aerospace Inc.
Inventor： ESSAWY, Magdi A. , RAY, Mark
Abstract: An aircraft system is configured to detect conditions of a cloud (18). The aircraft system includes a laser emitter (20), a fluorescent filter (22), optics (30a-30d), and an imager (24). The laser emitter (20) generates a short pulse laser beam. The fluorescent filter (22) is configured to convert the short pulse laser beam into a short pulse light beam such that the spectral content of the short pulse light beam is greater than the spectral content of the short pulse laser beam. The optics (30a-30d) are configured to direct the short pulse light beam through a window (16) of the aircraft into the cloud (18). The imager (24) is configured to receive a reflected portion of the short pulse light beam from the cloud (18), and process the images to detect the cloud particles of interest.
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公开(公告)号：EP4467455A3
公开(公告)日：2025-02-19
申请号：EP24205221.5
申请日：2019-12-05
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： ESSAWY, Magdi A. , ANDERSON, Kaara Josef , JACKSON, Darren G.
Abstract: Apparatus and associated methods relate to determining health of an electrical heater of an air data probe based on a comparison between a calculated expected value and a measured value of an electrical property of the electrical heater. The expected value of the electrical property is calculated based in part on the electrical power provided to the electrical heater and further based in part on the aircraft flight parameters and/or environmental conditions. Such aircraft flight parameters and/or environmental conditions can include at least one of: electric power source status, airspeed, air pressure, altitude, air temperature, humidity, liquid water content, ice water content, droplet/particle size distribution, angle of attack, and angle of sideslip. These aircraft flight parameters and/or environmental conditions are received via an aircraft interface.
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公开(公告)号：EP4467455A2
公开(公告)日：2024-11-27
申请号：EP24205221.5
申请日：2019-12-05
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： ESSAWY, Magdi A. , ANDERSON, Kaara Josef , JACKSON, Darren G.
IPC: B64D15/12
Abstract: Apparatus and associated methods relate to determining health of an electrical heater of an air data probe based on a comparison between a calculated expected value and a measured value of an electrical property of the electrical heater. The expected value of the electrical property is calculated based in part on the electrical power provided to the electrical heater and further based in part on the aircraft flight parameters and/or environmental conditions. Such aircraft flight parameters and/or environmental conditions can include at least one of: electric power source status, airspeed, air pressure, altitude, air temperature, humidity, liquid water content, ice water content, droplet/particle size distribution, angle of attack, and angle of sideslip. These aircraft flight parameters and/or environmental conditions are received via an aircraft interface.
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公开(公告)号：EP4027148A1
公开(公告)日：2022-07-13
申请号：EP22150140.6
申请日：2022-01-04
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： VALLAMKONDU, Aswin Kumar , ESSAWY, Magdi A. , ANNAMAREDDY, Ramesh , QUY, Dennis A.
Abstract: Apparatus and associated methods relate to health-monitoring of a magnetic speed probe (14). An inductive coil (18) of the magnetic speed probe (14) is used for two purposes: i) to sense a changing magnetic field caused by rotation of a rotating member; and ii) to radiatively transmit radio-frequency signals for determining the health of the magnetic speed probe (14). A signal generator (20) coupled to the inductive coil (18) of the magnetic speed probe (14) generates the radio-frequency signals that, when conducted by the inductive coil (18), cause the inductive coil (18) of the speed probe to act as a radio transmitter by radiatively transmitting the radio-frequency signals. The radio-frequency signals transmitted by the inductive coil (18) are detected by a radio receiver (24). The radio-frequency signals received are indicative of health of the magnetic speed probe (14).
The analysis of the received radio signals can involve emitting of a signal having a fixed frequency and determining of the amplitude of the received signal. It can also involve a frequency sweep of the radio signals applied to the coil, evaluating the amplitudes of the received signal and determining the maximum amplitude, which may indicate the resonant frequency of the coil. The received signals may be compared with reference values indicating normal operation.-
公开(公告)号：EP3611095A1
公开(公告)日：2020-02-19
申请号：EP19191966.1
申请日：2019-08-15
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： ESSAWY, Magdi A. , RAMTHUN, Kent A.
Abstract: An aircraft component (100) can include an aircraft component body (101), and a plasma heater (103) disposed at least partially on or at least partially within the component body (101) and configured to selectively heat the component body (101). The aircraft component (100) can be an air data sensor, and the aircraft component body (101) can be a sensor body. The aircraft component (100) can be any other suitable aircraft component (e.g., a portion of the airframe and/or any other suitable type of sensor and/or traditionally heated component).
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