Patents by Inventor Rangasamy Elangovan
Rangasamy Elangovan 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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Patent number: 10399684Abstract: An induction heating system employs a ferromagnetic susceptor mounted proximate an exterior of flight surface of an aircraft. At least one electrically conductive coil is mounted proximate the ferromagnetic susceptor. The at least one electrically conductive coil is powered by a first power source with a first frequency. At least one compensating coil is mounted proximate the ferromagnetic susceptor having a geometry determined to provide substantially net-zero flux with respect to the at least one electrically conductive coil and positioned to induce induction heating where the first plurality of electrically conductive coils lacks induced inductive heating coverage. The at least one compensating coils is powered by a second AC power source with a second frequency.Type: GrantFiled: October 29, 2014Date of Patent: September 3, 2019Assignee: The Boeing CompanyInventors: John R. Hull, Vyacheslav Khozikov, Robert J. Miller, Stephen R. Amorosi, Rangasamy Elangovan
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Patent number: 9846199Abstract: A vehicle includes a body and at least one propulsion unit operatively coupled to the body. The vehicle also includes an electrical power system at least partially disposed within the body. The electrical power system includes a rechargeable battery and a health management unit operatively coupled to the rechargeable battery. The health management unit includes a state of health module configured to output information corresponding to battery health based on received battery-related data. The battery-related data includes data collected in real time operation of the rechargeable battery and battery relevant fault history of the vehicle.Type: GrantFiled: October 20, 2014Date of Patent: December 19, 2017Assignee: THE BOEING COMPANYInventors: John L. Vian, Ali R. Mansouri, Rangasamy Elangovan, Mori M. Borumand, Khaled Abdel-Motagaly
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Patent number: 9469408Abstract: An ice protection system and method are provided that facilitate the prevention or reduction in ice formation upon an aerodynamic surface. The ice protection system may include an aerodynamic surface that includes a susceptor formed of a ferromagnetic material that is located proximate an outer mold line of a leading edge of the aerodynamic surface. The ice protection system may also include at least one induction coil and a signal source configured to provide alternating current to the at least one induction coil to thereby generate an electromagnetic field. The electromagnetic field creates an eddy current in the susceptor so as to heat the leading edge of the aerodynamic surface. A corresponding ice protection method is also provided.Type: GrantFiled: August 20, 2013Date of Patent: October 18, 2016Assignee: The Boeing CompanyInventors: Rangasamy Elangovan, Vyacheslav Khozikov, Stephen Roger Amorosi, Marc Matsen, Morteza Safai, Robert Miller
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Patent number: 9463879Abstract: A system and method for operating an ice detection and deicing system are provided herein. The ice detection and deicing system may use changing magnetic properties of various components caused by temperature changes to detect conditions conducive to, or indicating, ice formation. The ice detection and deicing system may further use eddy currents induced in one or more layers of the system to increase the temperature of the one or more layers to reduce the amount of ice formation or reduce the probability of ice being formed.Type: GrantFiled: March 3, 2014Date of Patent: October 11, 2016Assignee: The Boeing CompanyInventors: Vyacheslav Khozikov, Robert J. Miller, Rangasamy Elangovan, Marc R. Matsen, Stephen R. Amorosi, Robert G. Albers, Michael Strasik, John R. Hull
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Publication number: 20160122025Abstract: An induction heating system employs a ferromagnetic susceptor mounted proximate an exterior of flight surface of an aircraft. At least one electrically conductive coil is mounted proximate the ferromagnetic susceptor. The at least one electrically conductive coil is powered by a first power source with a first frequency. At least one compensating coil is mounted proximate the ferromagnetic susceptor having a geometry determined to provide substantially net-zero flux with respect to the at least one electrically conductive coil and positioned to induce induction heating where the first plurality of electrically conductive coils lacks induced inductive heating coverage. The at least one compensating coils is powered by a second AC power source with a second frequency.Type: ApplicationFiled: October 29, 2014Publication date: May 5, 2016Inventors: John R. Hull, Vyacheslav Khozikov, Robert J. Miller, Stephen R. Amorosi, Rangasamy Elangovan
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Publication number: 20150246730Abstract: A system and method for operating an ice detection and deicing system are provided herein. The ice detection and deicing system may use changing magnetic properties of various components caused by temperature changes to detect conditions conducive to, or indicating, ice formation. The ice detection and deicing system may further use eddy currents induced in one or more layers of the system to increase the temperature of the one or more layers to reduce the amount of ice formation or reduce the probability of ice being formed.Type: ApplicationFiled: March 3, 2014Publication date: September 3, 2015Applicant: The Boeing CompanyInventors: Vyacheslav Khozikov, Robert J. Miller, Rangasamy Elangovan, Marc R. Matsen, Stephen R. Amorosi, Robert G. Albers, Michael Strasik, John R. Hull
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Publication number: 20150100198Abstract: A vehicle includes a body and at least one propulsion unit operatively coupled to the body. The vehicle also includes an electrical power system at least partially disposed within the body. The electrical power system includes a rechargeable battery and a health management unit operatively coupled to the rechargeable battery. The health management unit includes a state of health module configured to output information corresponding to battery health based on received battery-related data. The battery-related data includes data collected in real time operation of the rechargeable battery and battery relevant fault history of the vehicle.Type: ApplicationFiled: October 20, 2014Publication date: April 9, 2015Applicant: The Boeing CompanyInventors: John L. Vian, Ali R. Mansouri, Rangasamy Elangovan, Mori M. Borumand, Khaled Abdel-Motagaly
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Patent number: 8890480Abstract: Systems and methods for health management of rechargeable batteries are disclosed. In one embodiment, a rechargeable battery system includes a rechargeable battery, and a battery health management unit operatively coupled to the rechargeable battery and including a state of health module configured to estimate a battery health by receiving battery-related data and predicting one or more failure modes. The state of health module may further include a prognostic failure mode component configured to combine at least one flight data variable with at least one model-based prognostic. In alternate embodiments, the battery health management unit may further include a state of life module and a state of charge module.Type: GrantFiled: November 30, 2006Date of Patent: November 18, 2014Assignee: The Boeing CompanyInventors: John L. Vian, Ali R. Mansouri, Rangasamy Elangovan, Mori M. Borumand, Khaled Abdel-Motagaly
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Patent number: 8777163Abstract: An ice protection system and method are provided that facilitate the prevention or reduction in ice formation upon an aerodynamic surface. The ice protection system may include at least one induction coil spaced apart from an electrically conductive layer of an aerodynamic surface and disposed interior of an exterior surface of the aerodynamic surface. For example, the ice protection system may include a plurality of induction coils with each induction coil being spaced apart from the other induction coils such that the respective induction coils are associated with different portions of the aerodynamic surface. The ice protection system may also include a signal source configured to provide alternating current to the induction coil(s) to thereby generate an electromagnetic field that creates an eddy current in the electrically conductive layer so as to heat the electrically conductive layer.Type: GrantFiled: September 3, 2009Date of Patent: July 15, 2014Assignee: The Boeing CompanyInventors: Morteza Safai, Rangasamy Elangovan, Vyacheslav Khozikov
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Publication number: 20110049300Abstract: An ice protection system and method are provided that facilitate the prevention or reduction in ice formation upon an aerodynamic surface. The ice protection system may include at least one induction coil spaced apart from an electrically conductive layer of an aerodynamic surface and disposed interior of an exterior surface of the aerodynamic surface. For example, the ice protection system may include a plurality of induction coils with each induction coil being spaced apart from the other induction coils such that the respective induction coils are associated with different portions of the aerodynamic surface. The ice protection system may also include a signal source configured to provide alternating current to the induction coil(s) to thereby generate an electromagnetic field that creates an eddy current in the electrically conductive layer so as to heat the electrically conductive layer.Type: ApplicationFiled: September 3, 2009Publication date: March 3, 2011Applicant: The Boeing CompanyInventors: Morteza Safai, Rangasamy Elangovan, Vyacheslav Khozikov
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Publication number: 20100121587Abstract: Systems and methods for health management of rechargeable batteries are disclosed. In one embodiment, a rechargeable battery system includes a rechargeable battery, and a battery health management unit operatively coupled to the rechargeable battery and including a state of health module configured to estimate a battery health by receiving battery-related data and predicting one or more failure modes. The state of health module may further include a prognostic failure mode component configured to combine at least one flight data variable with at least one model-based prognostic. In alternate embodiments, the battery health management unit may further include a state of life module and a state of charge module.Type: ApplicationFiled: November 30, 2006Publication date: May 13, 2010Applicant: The Boeing CompanyInventors: John L. Vian, Ali R. Mansouri, Rangasamy Elangovan, Mori M. Borumand, Khaled Abdel-Motagaly
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Patent number: 7681923Abstract: A fitting and an associated grommet are provided for supporting a conduit penetrating a panel and limiting energy transfer between the conduit and panel. The fitting may include a grommet having annular first and second sections spaced apart from one another and an annular wall extending between the first and second sections such that the wall and first and second sections define a bore. A plurality of ribs protrude from the annular wall, the ribs being distributed circumferentially around the annular wall and spanning between the first and second sections. A tubular liner extends through the bore of the grommet and contacts the first and second sections. The plurality of ribs extend into the bore, and at least some of the ribs contact the liner.Type: GrantFiled: November 17, 2006Date of Patent: March 23, 2010Assignee: The Boeing CompanyInventors: Mark A. Negley, Rangasamy Elangovan, Yuri Tian, Eric H. Nelson, Paul S. Gregg, Michael A. Ross
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Publication number: 20080116319Abstract: A fitting and an associated grommet are provided for supporting a conduit penetrating a panel and limiting energy transfer between the conduit and panel. The fitting may include a grommet having annular first and second sections spaced apart from one another and an annular wall extending between the first and second sections such that the wall and first and second sections define a bore. A plurality of ribs protrude from the annular wall, the ribs being distributed circumferentially around the annular wall and spanning between the first and second sections. A tubular liner extends through the bore of the grommet and contacts the first and second sections. The plurality of ribs extend into the bore, and at least some of the ribs contact the liner.Type: ApplicationFiled: November 17, 2006Publication date: May 22, 2008Applicant: The Boeing CompanyInventors: Mark A. Negley, Rangasamy Elangovan, Yuri Tian, Eric H. Nelson, Paul S. Gregg, Michael A. Ross