Patents by Inventor Magdi A. Essawy
Magdi A. Essawy has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Publication number: 20210084718Abstract: A method and system for monitoring a heating arrangement includes applying a first polarity voltage to a heater of the heating arrangement, detecting a first polarity heating leakage current, applying a second polarity voltage to the heating arrangement, detecting a second polarity heating leakage current, and determining health of the heating arrangement via the first polarity heating leakage current and the second polarity heating leakage current.Type: ApplicationFiled: September 16, 2019Publication date: March 18, 2021Inventors: Magdi A. Essawy, Cuong Tho Huynh
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Patent number: 10914777Abstract: A system and method for an aircraft includes a probe, first and second current sensors, and a control circuit. The probe includes a heater that includes a resistive heating element routed through the probe, wherein an operational current is provided to the resistive heating element to provide heating for the probe. The first current sensor is configured to sense a first current through the resistive heating element, and the second current sensor is configured to sense a second current through the resistive heating element. The control circuit is configured to determine a leakage current based on the first and second currents and determine a remaining useful life the probe based on the leakage current over time.Type: GrantFiled: June 15, 2017Date of Patent: February 9, 2021Assignee: Rosemount Aerospace Inc.Inventors: Magdi A. Essawy, Ben Ping-Tao Fok, Thomas Wingert
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Patent number: 10895592Abstract: A probe system configured to receive a radio-frequency (RF) signal from a radio-frequency (RF) antenna includes a heater and a control circuit. The heater includes a resistive heating element routed through the probe system. An operational voltage is provided to the resistive heating element to provide heating for the probe system and the resistive heating element has an element capacitance. The control circuit is configured to determine an antenna response of the resistive heating element and determine a remaining useful life of the probe system based on the antenna response over time.Type: GrantFiled: March 24, 2017Date of Patent: January 19, 2021Assignee: Rosemount Aerospace Inc.Inventors: Magdi A. Essawy, James Joseph McTighe
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Publication number: 20200391871Abstract: 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.Type: ApplicationFiled: June 14, 2019Publication date: December 17, 2020Inventors: Magdi A. Essawy, Kaare Josef Anderson, Darren G. Jackson
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Publication number: 20200379027Abstract: A system and method for monitoring the health of a heater connected to a power supply by a power cable that includes a first power lead conducting an inlet current having an inlet current direction, and a second power lead conducting an outlet current having an outlet current direction opposite to the inlet current direction. The power cable passes through a center region of a toroid core one or more times, and a secondary winding on the toroid core is configured to induce a secondary voltage indicative of a difference between the inlet current and the outlet current, which defines the leakage current. The system includes a prognostic processor that is configured to calculate a heater health indication based on the secondary voltage, which is indicative of the heater health.Type: ApplicationFiled: May 29, 2019Publication date: December 3, 2020Inventors: Magdi A. Essawy, Dennis A. Quy, Cuong Tho Huynh
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Patent number: 10782406Abstract: Apparatus and associated methods relate to detecting cloud conditions from a distance by generating a polarized microwave-frequency electromagnetic pulse and evaluating various reflected wave parameters pertaining to a corresponding cloud-reflected microwave-frequency electromagnetic reflection. Various cloud metrics can be calculated using these collected wave parameters. The microwave-frequency pulses can be scanned over multiple dimensions, using a steered beam arrangement which will lead to the ability to scanning a conical sector of the space in front of the aircraft. These collected multi-dimensional wave parameters can then be used to generate multi-dimensional maps of cloud metrics. Such cloud metrics can include relative velocities of moving cloud conditions in the flight direction, particle density distributions, ice/water ratios, estimates of particle side distributions, etc.Type: GrantFiled: April 28, 2016Date of Patent: September 22, 2020Assignee: Rosemount Aerospace Inc.Inventors: Magdi A. Essawy, Darren G. Jackson
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Publication number: 20200191851Abstract: A system for an aircraft includes a heater comprising a resistive heating element and insulation surrounding the resistive heating element. A first current flows into the resistive heating element to provide heat and a second current flows out of the resistive heating element. The system further includes a leakage sensor configured to produce a leakage sensor signal representing a leakage current from the heater and a prediction processor configured to predict heater failure based on the leakage sensor signal.Type: ApplicationFiled: December 14, 2018Publication date: June 18, 2020Inventors: Magdi A. Essawy, Minh Bui, John D. Gasser
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Publication number: 20200191850Abstract: A system for an aircraft includes an aircraft component that includes a heater routed through the aircraft component, the heater including a resistive heating element and insulation surrounding the resistive heating element. A first current flows into the resistive heating element to provide heating for the aircraft component and a second current flows out of the resistive heating element. The system further includes a first sensor configured to produce a first sensor signal representing the first current, a second sensor configured to produce a second sensor signal representing the second current, a leakage sensor configured to produce a leakage sensor signal representing a leakage current, and a signal processor configured to sample and measure the first current, the second current, and a leakage current using a high frequency sampling rate to identify the presence of electric arcing. The detection of electric arcing is used to predict future heater failure and estimate heater remaining useful life.Type: ApplicationFiled: December 14, 2018Publication date: June 18, 2020Inventors: Magdi A. Essawy, Marvin Onken
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Patent number: 10620342Abstract: An aircraft system is configured to detect conditions of a cloud. The aircraft system includes a laser emitter, a fluorescent filter, optics, and an imager. The laser emitter generates a short pulse laser beam. The fluorescent filter 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 are configured to direct the short pulse light beam through a window of the aircraft into the cloud. The imager is configured to receive a reflected portion of the short pulse light beam from the cloud, and process the images to detect the cloud particles of interest.Type: GrantFiled: September 28, 2017Date of Patent: April 14, 2020Assignee: Rosemount Aerospace Inc.Inventors: Magdi A Essawy, Mark Ray
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Patent number: 10605848Abstract: A probe system configured to receive a radio-frequency (RF) signal from a radio-frequency (RF) antenna includes a heater and a control circuit. The heater includes a resistive heating element routed through the probe system. An operational voltage is provided to the resistive heating element to provide heating for the probe system and the resistive heating element has an element capacitance. The control circuit is configured to determine an antenna response of the resistive heating element and determine a remaining useful life of the probe system based on the antenna response over time.Type: GrantFiled: March 24, 2017Date of Patent: March 31, 2020Assignee: Rosemount Aerospace Inc.Inventors: Magdi A. Essawy, James Joseph McTighe
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Publication number: 20200060016Abstract: An aircraft component can include an aircraft component body, and a plasma heater disposed at least partially on or at least partially within the component body and configured to selectively heat the component body. The aircraft component can be an air data sensor, and the aircraft component body can be a sensor body. The aircraft component 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).Type: ApplicationFiled: August 16, 2018Publication date: February 20, 2020Inventors: Magdi A. Essawy, Kent A. Ramthun
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Patent number: 10564203Abstract: A probe system includes a heater and a control circuit. The heater includes a resistive heating element routed through the probe system. An operational voltage is provided to the resistive heating element to provide heating for the probe system. The control circuit is configured to provide the operational voltage and monitor a capacitance between the resistive heating element and a metallic sheath of the heater over time. The control circuit is further configured to determine a remaining useful life of the probe system based on the capacitance.Type: GrantFiled: March 24, 2017Date of Patent: February 18, 2020Assignee: Rosemount Aerospace Inc.Inventors: Magdi A. Essawy, Ben Ping-Tao Fok
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Publication number: 20190094415Abstract: An aircraft system is configured to detect conditions of a cloud. The aircraft system includes a laser emitter, a fluorescent filter, optics, and an imager. The laser emitter generates a short pulse laser beam. The fluorescent filter 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 are configured to direct the short pulse light beam through a window of the aircraft into the cloud. The imager is configured to receive a reflected portion of the short pulse light beam from the cloud, and process the images to detect the cloud particles of interest.Type: ApplicationFiled: September 28, 2017Publication date: March 28, 2019Inventors: Magdi A. Essawy, Mark Ray
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Patent number: 10197517Abstract: A probe system is configured to receive thermal images of the probe system from a thermal imager and includes a heater and a control circuit. The heater includes a resistive heating element routed through the probe. An operational voltage is provided to the resistive heating element to provide heating for the probe. The control circuit is configured to provide the operational voltage and receive the thermal images from the thermal imager. The control circuit is further configured to monitor the thermal images over time and determine a remaining useful life of the probe system based upon the thermal images over time.Type: GrantFiled: March 24, 2017Date of Patent: February 5, 2019Assignee: Rosemount Aerospace, Inc.Inventors: Magdi A. Essawy, Ben Ping-Tao Fok, Marvin Gary Onken
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Patent number: 10180449Abstract: A probe system includes a heater and a control circuit. The heater includes a resistive heating element routed through the probe. An operational current is provided to the resistive heating element to provide heating for the probe. The control circuit is configured to monitor the operational current over time and determine a half-life estimate of the resistive heating element based upon an exponential function of the operational current over time.Type: GrantFiled: March 24, 2017Date of Patent: January 15, 2019Assignee: Rosemount Aerospace Inc.Inventors: Magdi A. Essawy, Ben Ping-Tao Fok
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Patent number: 10151785Abstract: A probe system includes a heater and a control circuit. The heater includes a resistive heating element routed through the probe system. An operational voltage is provided to the resistive heating element to provide heating for the probe system. The control circuit is configured to provide the operational voltage and monitor a circuit frequency based on an element capacitance between the resistive heating element and a metallic sheath of the heater over time. The control circuit is further configured to determine remaining useful life of the probe system based on the circuit frequency.Type: GrantFiled: March 24, 2017Date of Patent: December 11, 2018Assignee: Rosemount Aerospace Inc.Inventors: Magdi A. Essawy, James Joseph McTighe, Ben Ping-Tao Fok
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Publication number: 20180275080Abstract: A probe system is configured to receive thermal images of the probe system from a thermal imager and includes a heater and a control circuit. The heater includes a resistive heating element routed through the probe. An operational voltage is provided to the resistive heating element to provide heating for the probe. The control circuit is configured to provide the operational voltage and receive the thermal images from the thermal imager. The control circuit is further configured to monitor the thermal images over time and determine a remaining useful life of the probe system based upon the thermal images over time.Type: ApplicationFiled: March 24, 2017Publication date: September 27, 2018Inventors: Magdi A. Essawy, Ben Ping-Tao Fok, Marvin Gary Onken
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Publication number: 20180275182Abstract: A probe system includes a heater and a control circuit. The heater includes a resistive heating element routed through the probe system. An operational voltage is provided to the resistive heating element to provide heating for the probe system. The control circuit is configured to provide the operational voltage and monitor a circuit frequency based on an element capacitance between the resistive heating element and a metallic sheath of the heater over time. The control circuit is further configured to determine remaining useful life of the probe system based on the circuit frequency.Type: ApplicationFiled: March 24, 2017Publication date: September 27, 2018Inventors: Magdi A. Essawy, James Joseph McTighe, Ben Ping-Tao Fok
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Publication number: 20180275185Abstract: A system and method for an aircraft includes a probe, first and second current sensors, and a control circuit. The probe includes a heater that includes a resistive heating element routed through the probe, wherein an operational current is provided to the resistive heating element to provide heating for the probe. The first current sensor is configured to sense a first current through the resistive heating element, and the second current sensor is configured to sense a second current through the resistive heating element. The control circuit is configured to determine a leakage current based on the first and second currents and determine a remaining useful life the probe based on the leakage current over time.Type: ApplicationFiled: June 15, 2017Publication date: September 27, 2018Inventors: Magdi A. Essawy, Ben Ping-Tao Fok, Thomas Wingert
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Publication number: 20180275183Abstract: A probe system configured to receive a radio-frequency (RF) signal from a radio-frequency (RF) antenna includes a heater and a control circuit. The heater includes a resistive heating element routed through the probe system. An operational voltage is provided to the resistive heating element to provide heating for the probe system and the resistive heating element has an element capacitance. The control circuit is configured to determine an antenna response of the resistive heating element and determine a remaining useful life of the probe system based on the antenna response over time.Type: ApplicationFiled: March 24, 2017Publication date: September 27, 2018Inventors: Magdi A. Essawy, James Joseph McTighe