Patents by Inventor Mark T. Manfred
Mark T. Manfred 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: 9037318Abstract: Systems and methods for providing aircraft heading information are provided. In one embodiment, an attitude heading reference device comprises: at least one interface for receiving heading information from one or more IRUs; at least one set of gyroscopes and accelerometers; a memory device for storing data representing heading information received via the at least one interface; and a heading calculator coupled to the at least one interface, the at least one set of gyroscopes and accelerometers, and the memory device. The heading calculator generating a heading output signal based on heading information when reliable heading information is received over the at least one interface; the heading calculator generating the heading output signal based on data from the memory device regarding previously reliable heading information and an output of the at least one set of gyroscopes and accelerometers when reliable heading information is not received over the at least one interface.Type: GrantFiled: May 8, 2013Date of Patent: May 19, 2015Assignee: Honeywell International Inc.Inventors: Mark T. Manfred, Thomas A. Ryno
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Patent number: 8538607Abstract: Systems and methods for providing aircraft heading information are provided. In one embodiment, an attitude heading reference device comprises: at least one interface for receiving heading information from one or more IRUs; at least one set of gyroscopes and accelerometers; a memory device for storing data representing heading information received via the at least one interface; and a heading calculator coupled to the at least one interface, the at least one set of gyroscopes and accelerometers, and the memory device. The heading calculator generating a heading output signal based on heading information when reliable heading information is received over the at least one interface; the heading calculator generating the heading output signal based on data from the memory device regarding previously reliable heading information and an output of the at least one set of gyroscopes and accelerometers when reliable heading information is not received over the at least one interface.Type: GrantFiled: January 28, 2010Date of Patent: September 17, 2013Assignee: Honeywell International Inc.Inventors: Mark T. Manfred, Thomas A. Ryno
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Publication number: 20130238172Abstract: Systems and methods for providing aircraft heading information are provided. In one embodiment, an attitude heading reference device comprises: at least one interface for receiving heading information from one or more IRUs; at least one set of gyroscopes and accelerometers; a memory device for storing data representing heading information received via the at least one interface; and a heading calculator coupled to the at least one interface, the at least one set of gyroscopes and accelerometers, and the memory device. The heading calculator generating a heading output signal based on heading information when reliable heading information is received over the at least one interface; the heading calculator generating the heading output signal based on data from the memory device regarding previously reliable heading information and an output of the at least one set of gyroscopes and accelerometers when reliable heading information is not received over the at least one interface.Type: ApplicationFiled: May 8, 2013Publication date: September 12, 2013Applicant: Honeywell International Inc.Inventors: Mark T. Manfred, Thomas A. Ryno
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Patent number: 8204635Abstract: An aircraft inertial system comprises at least two inertial reference units (IRU) that provide a first set of inertial signal data for an aircraft and at least two attitude heading reference systems (AHRS) that provide a second set of the inertial signal data for the aircraft. At least one primary flight display receives the first and the second sets of the inertial signal data, and a standby flight display receives at least the second set of the inertial signal data from at least one of the AHRS. When a single fault condition occurs, the primary flight display continues to operate with fail-operational redundancy from at least three independent sources of the inertial signal data comprising one or more IRU and AHRS combinations. The standby flight display will operate using a different source of the inertial signal data than the source of the inertial signal data for the primary flight display.Type: GrantFiled: December 16, 2008Date of Patent: June 19, 2012Assignee: Honeywell International Inc.Inventors: Mark T. Manfred, Thomas A. Ryno
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Publication number: 20110184594Abstract: Systems and methods for providing aircraft heading information are provided. In one embodiment, an attitude heading reference device comprises: at least one interface for receiving heading information from one or more IRUs; at least one set of gyroscopes and accelerometers; a memory device for storing data representing heading information received via the at least one interface; and a heading calculator coupled to the at least one interface, the at least one set of gyroscopes and accelerometers, and the memory device. The heading calculator generating a heading output signal based on heading information when reliable heading information is received over the at least one interface; the heading calculator generating the heading output signal based on data from the memory device regarding previously reliable heading information and an output of the at least one set of gyroscopes and accelerometers when reliable heading information is not received over the at least one interface.Type: ApplicationFiled: January 28, 2010Publication date: July 28, 2011Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Mark T. Manfred, Thomas A. Ryno
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Publication number: 20100152929Abstract: An aircraft inertial system comprises at least two inertial reference units (IRU) that provide a first set of inertial signal data for an aircraft and at least two attitude heading reference systems (AHRS) that provide a second set of the inertial signal data for the aircraft. At least one primary flight display receives the first and the second sets of the inertial signal data, and a standby flight display receives at least the second set of the inertial signal data from at least one of the AHRS. When a single fault condition occurs, the primary flight display continues to operate with fail-operational redundancy from at least three independent sources of the inertial signal data comprising one or more IRU and AHRS combinations. The standby flight display will operate using a different source of the inertial signal data than the source of the inertial signal data for the primary flight display.Type: ApplicationFiled: December 16, 2008Publication date: June 17, 2010Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Mark T. Manfred, Thomas A. Ryno
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Patent number: 7146740Abstract: A method for characterizing distortions in the earth's magnetic field caused by a vehicle having a magnetometer affixed therein is described. The method includes repeatedly measuring the distorted magnetic field utilizing the magnetometer and obtaining a three-dimensional orientation of the vehicle axes with respect to the earth at a time of each magnetometer measurement. The method also includes receiving undistorted earth magnetic field data for the vicinity of the vehicle relative to the earth at the time of each magnetometer measurement and characterizing distortions caused by one or more of the vehicle and magnetometer errors utilizing the magnetic field measurements, the orientations of the vehicle, and the undistorted earth magnetic field data.Type: GrantFiled: February 23, 2005Date of Patent: December 12, 2006Assignee: Honeywell International Inc.Inventor: Mark T. Manfred
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Patent number: 7145501Abstract: An altitude measuring system is described that includes a radar altimeter configured to measure altitude and a digital terrain map database. The database includes data relating to terrain elevation and at least one data parameter relating to an accuracy of the terrain elevation data and the altitude measured by the radar altimeter. The system is configured to weigh an altitude derived from the terrain elevation data and the radar altimeter measurements according to the at least one data parameter.Type: GrantFiled: September 26, 2005Date of Patent: December 5, 2006Assignee: Honeywell International Inc.Inventors: Mark T. Manfred, Curtis J. Call
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Patent number: 6860023Abstract: A method for characterizing distortions in the earth's magnetic field caused by a vehicle having a magnetometer affixed therein is described. The method includes repeatedly measuring the distorted magnetic field utilizing the magnetometer and obtaining a three-dimensional orientation of the vehicle axes with respect to the earth at a time of each magnetometer measurement. The method also includes receiving undistorted earth magnetic field data for the vicinity of the vehicle relative to the earth at the time of each magnetometer measurement and characterizing distortions caused by one or more of the vehicle and magnetometer errors utilizing the magnetic field measurements, the orientations of the vehicle, and the undistorted earth magnetic field data.Type: GrantFiled: December 1, 2003Date of Patent: March 1, 2005Assignee: Honeywell International Inc.Inventors: Mark T. Manfred, Randolph G. Hartman, James E. Lenz, Kevin D. Vanderwerf, Lawrence C. Vallot
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Publication number: 20040186635Abstract: A method for detecting an inaccurate barometric pressure adjustment setting on a barometric altimeter is described. The method includes receiving a barometric corrected altitude from the altimeter, receiving an altitude from a global positioning satellite (GPS) system, comparing the barometric corrected altitude with the altitude received from the GPS system, actuating an alarm if the altitudes differ by an amount larger than a threshold value, the threshold value being dependent upon one or more of the received altitudes.Type: ApplicationFiled: March 21, 2003Publication date: September 23, 2004Inventor: Mark T. Manfred
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Publication number: 20040123474Abstract: A method for characterizing distortions in the earth's magnetic field caused by a vehicle having a magnetometer affixed therein is described. The method includes repeatedly measuring the distorted magnetic field utilizing the magnetometer and obtaining a three-dimensional orientation of the vehicle axes with respect to the earth at a time of each magnetometer measurement. The method also includes receiving undistorted earth magnetic field data for the vicinity of the vehicle relative to the earth at the time of each magnetometer measurement and characterizing distortions caused by one or more of the vehicle and magnetometer errors utilizing the magnetic field measurements, the orientations of the vehicle, and the undistorted earth magnetic field data.Type: ApplicationFiled: December 1, 2003Publication date: July 1, 2004Inventors: Mark T. Manfred, Randolph G. Hartman, James E. Lenz, Kevin D. Vanderwerf, Lawrence C. Vallot
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Patent number: 4164713Abstract: A detector circuit is shown for detecting off-hook and dial pulse signals in a telephone system which, under the control of a ringing relay, reconfigures itself to provide ring-trip detection. The detection circuit includes a bridge which is responsive to circulating loop currents, while at the same time unresponsive to longitudinally balanced currents, and a two-stage voltage level detector circuit. An RC timing circuit is included between the two stages to insure that the detector is unresponsive to short duration pulses and, at the same time, once energized, will bridge over short duration interruptions of detected pulses.Type: GrantFiled: October 25, 1977Date of Patent: August 14, 1979Assignee: Bell Telephone Laboratories, IncorporatedInventors: Stephen J. Brolin, Richard J. Lisco, Mark T. Manfred