Patents by Inventor Geoffrey S. M. Hedrick
Geoffrey S. M. Hedrick 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: 20170322564Abstract: A preexisting FMS system may be upgraded to increase its functionality by optimizing the control of autopilot and auto-throttle functions and replacing other preexisting components with different components for enhancing the functionality of the FMS system. The preexisting IRU, CADC, DME receiver and DFGC in the upgraded FMS system are in communication with the legacy AFMC but, instead of employing the legacy EFIS, the EFIS is replaced by a data concentrator unit as well as the display control panel and integrated flat panel display, and a GPS receiver. The upgraded FMS system is capable of iteratively controlling the autopilot and auto-throttle during all phases of flight and of such increased functionality as increased navigation database storage capacity, RNP, VNAV, LPV and RNAV capability utilizing a GPS based navigation solution, and RTA capability, while still enabling the legacy AFMC to exploit its aircraft performance capabilities throughout the flight.Type: ApplicationFiled: May 26, 2017Publication date: November 9, 2017Inventors: Geoffrey S.M. Hedrick, Shahram Askarpour
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Publication number: 20170241783Abstract: A method and system for compensating for soft iron magnetic disturbances in multiple heading reference systems, such as aircraft heading reference systems, integrated standby units; or vehicle inertial systems, detects and provides a heading correction signal to the error prone heading reference system when a detected difference in value between a gyro heading relative to magnetic north and a magnetometer reading during a defined measurement period exceeds a predetermined acceptable threshold value of change, such as one based on the expected gyro drift over that period. Upon receipt of the heading correction signal, the gyro heading is adjusted to maintain an accurate heading relative to true magnetic north. If this threshold value is not exceeded, then the magnetometer reading is used for the heading value. This method is periodically repeated in order to continually maintain an accurate heading and may be employed for each heading measurement axis.Type: ApplicationFiled: May 10, 2017Publication date: August 24, 2017Inventors: Shahram Askarpour, Geoffrey S. M. Hedrick
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Patent number: 9709992Abstract: A preexisting FMS system may be upgraded to increase its functionality by optimizing the control of autopilot and auto-throttle functions and replacing other preexisting components with different components for enhancing the functionality of the FMS system. The preexisting IRU, CADC, DME receiver and DFGC in the upgraded FMS system are in communication with the legacy AFMC but, instead of employing the legacy EFIS, the EFIS is replaced by a data concentrator unit as well as the display control panel and integrated flat panel display, and a GPS receiver. The upgraded FMS system is capable of iteratively controlling the autopilot and auto-throttle during all phases of flight and of such increased functionality as increased navigation database storage capacity, RNP, VNAV, LPV and RNAV capability utilizing a GPS based navigation solution, and RTA capability, while still enabling the legacy AFMC to exploit its aircraft performance capabilities throughout the flight.Type: GrantFiled: June 8, 2016Date of Patent: July 18, 2017Assignee: Innovative Solutions & Support, Inc.Inventors: Geoffrey S. M. Hedrick, Shahram Askarpour
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Patent number: 9677889Abstract: A method and system for compensating for soft iron magnetic disturbances in multiple heading reference systems, such as aircraft heading reference systems, integrated standby units; or vehicle inertial systems, detects and provides a heading correction signal to the error prone heading reference system when a detected difference in value between a gyro heading relative to magnetic north and a magnetometer reading during a defined measurement period exceeds a predetermined acceptable threshold value of change, such as one based on the expected gyro drift over that period. Upon receipt of the heading correction signal, the gyro heading is adjusted to maintain an accurate heading relative to true magnetic north. If this threshold value is not exceeded, then the magnetometer reading is used for the heading value. This method is periodically repeated in order to continually maintain an accurate heading and may be employed for each heading measurement axis.Type: GrantFiled: July 29, 2016Date of Patent: June 13, 2017Inventors: Shahram Askarpour, Geoffrey S. M. Hedrick
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Publication number: 20170106994Abstract: A composite normalized angle of attack indicating system provides a simultaneous display of both body angle of attack, such as in digital form, and normalized angle of attack for an aircraft. The display may be visually enhanced as stall is approached such as by zooming the body angle of attack digital display and/or by changing the color of the display. The normalized display also selectively displays an approach reference band when the flap setting is equal to or greater than 20 degrees.Type: ApplicationFiled: December 30, 2016Publication date: April 20, 2017Inventors: Geoffrey S.M. Hedrick, Shahram Askarpour
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Patent number: 9595199Abstract: A preexisting FMS system may be upgraded to increase its functionality while still taking advantage of certain components of the legacy system previously provided on the aircraft and replacing other preexisting components with different components for enhancing the functionality of the FMS system. The preexisting IRU, CADC, DME receiver and DFGC in the upgraded FMS system are in communication with the legacy AFMC but, instead of employing the legacy EFIS which existed in the preexisting FMS system, the EFIS is replaced by a data concentrator unit as well as the display control panel and integrated flat panel display, and a GPS receiver. The upgraded FMS system is capable of such increased functionality as increased navigation database storage capacity, RNP, VNAV and RNAV capability utilizing a GPS based navigation solution, and RTA capability, while still enabling the legacy AFMC to exploit its aircraft performance capabilities throughout the flight.Type: GrantFiled: June 10, 2015Date of Patent: March 14, 2017Assignee: Innovative Solutions & Support, Inc.Inventors: Geoffrey S. M. Hedrick, Shahram Askarpour, Markus Knopf
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Patent number: 9593593Abstract: A composite normalized angle of attack indicating system provides a simultaneous display of both body angle of attack, such as in digital form, and normalized angle of attack for an aircraft. The display may be visually enhanced as stall is approached such as by zooming the body angle of attack digital display and/or by changing the color of the display. The normalized display also selectively displays an approach reference band when the flap setting is equal to or greater than 20 degrees.Type: GrantFiled: November 20, 2015Date of Patent: March 14, 2017Assignee: Innovative Solutions & Support, Inc.Inventors: Geoffrey S. M. Hedrick, Shahram Askarpour
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Publication number: 20170068253Abstract: A preexisting FMS system may be upgraded to increase its functionality by optimizing the control of autopilot and auto-throttle functions and replacing other preexisting components with different components for enhancing the functionality of the FMS system. The preexisting IRU, CADC, DME receiver and DFGC in the upgraded FMS system are in communication with the legacy AFMC but, instead of employing the legacy EFIS, the EFIS is replaced by a data concentrator unit as well as the display control panel and integrated flat panel display, and a GPS receiver. The upgraded FMS system is capable of iteratively controlling the autopilot and auto-throttle during all phases of flight and of such increased functionality as increased navigation database storage capacity, RNP, VNAV, LPV and RNAV capability utilizing a GPS based navigation solution, and RTA capability, while still enabling the legacy AFMC to exploit its aircraft performance capabilities throughout the flight.Type: ApplicationFiled: June 8, 2016Publication date: March 9, 2017Inventors: Geoffrey S.M. Hedrick, Shahram Askarpour
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Publication number: 20160334219Abstract: A method and system for compensating for soft iron magnetic disturbances in multiple heading reference systems, such as aircraft heading reference systems, integrated standby units; or vehicle inertial systems, detects and provides a heading correction signal to the error prone heading reference system when a detected difference in value between a gyro heading relative to magnetic north and a magnetometer reading during a defined measurement period exceeds a predetermined acceptable threshold value of change, such as one based on the expected gyro drift over that period. Upon receipt of the heading correction signal, the gyro heading is adjusted to maintain an accurate heading relative to true magnetic north. If this threshold value is not exceeded, then the magnetometer reading is used for the heading value. This method is periodically repeated in order to continually maintain an accurate heading and may be employed for each heading measurement axis.Type: ApplicationFiled: July 29, 2016Publication date: November 17, 2016Inventors: Shahram Askarpour, Geoffrey S. M. Hedrick
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Publication number: 20160123181Abstract: A composite normalized angle of attack indicating system provides a simultaneous display of both body angle of attack, such as in digital form, and normalized angle of attack for an aircraft. The display may be visually enhanced as stall is approached such as by zooming the body angle of attack digital display and/or by changing the color of the display. The normalized display also selectively displays an approach reference band when the flap setting is equal to or greater than 20 degrees.Type: ApplicationFiled: November 20, 2015Publication date: May 5, 2016Inventors: Geoffrey S.M. Hedrick, Shahram Askarpour
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Patent number: 9221550Abstract: A composite normalized angle of attack indicating system provides a simultaneous display of both body angle of attack, such as in digital form, and normalized angle of attack for an aircraft. The display may be visually enhanced as stall is approached such as by zooming the body angle of attack digital display and/or by changing the color of the display. The normalized display also selectively displays an approach reference band when the flap setting is equal to or greater than 20 degrees.Type: GrantFiled: March 12, 2013Date of Patent: December 29, 2015Inventors: Geoffrey S. M. Hedrick, Shahram Askarpour
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Publication number: 20150339929Abstract: A preexisting FMS system may be upgraded to increase its functionality while still taking advantage of certain components of the legacy system previously provided on the aircraft and replacing other preexisting components with different components for enhancing the functionality of the FMS system. The preexisting IRU, CADC, DME receiver and DFGC in the upgraded FMS system are in communication with the legacy AFMC but, instead of employing the legacy EFIS which existed in the preexisting FMS system, the EFIS is replaced by a data concentrator unit as well as the display control panel and integrated flat panel display, and a GPS receiver. The upgraded FMS system is capable of such increased functionality as increased navigation database storage capacity, RNP, VNAV and RNAV capability utilizing a GPS based navigation solution, and RTA capability, while still enabling the legacy AFMC to exploit its aircraft performance capabilities throughout the flight.Type: ApplicationFiled: June 10, 2015Publication date: November 26, 2015Inventors: Geoffrey S.M. Hedrick, Shahram Askarpour, Markus Knopf
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Patent number: 9087450Abstract: A preexisting FMS system may be upgraded to increase its functionality while still taking advantage of certain components of the legacy system previously provided on the aircraft and replacing other preexisting components with different components for enhancing the functionality of the FMS system. The preexisting IRU, CADC, DME receiver and DFGC in the upgraded FMS system are in communication with the legacy AFMC but, instead of employing the legacy EFIS which existed in the prrexisting FMS system, the EFIS is replaced by a data concentrator unit as well as the display control panel and integrated flat panel display, and a GPS receiver. The upgraded FMS system is capable of such increased functionality as increased navigation database storage capacity, RNP, VNAV and RNAV capability utilizing a GPS based navigation solution, and RTA capability, while still enabling the legacy AFMC to exploit its aircraft performance capabilities throughout the flight.Type: GrantFiled: May 17, 2011Date of Patent: July 21, 2015Assignee: Innovative Solutions and Support, Inc.Inventors: Geoffrey S. M. Hedrick, Shahram Askarpour, Markus Knopf
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Publication number: 20140266808Abstract: A composite normalized angle of attack indicating system provides a simultaneous display of both body angle of attack, such as in digital form, and normalized angle of attack for an aircraft. The display may be visually enhanced as stall is approached such as by zooming the body angle of attack digital display and/or by changing the color of the display. The normalized display also selectively displays an approach reference band when the flap setting is equal to or greater than 20 degrees.Type: ApplicationFiled: March 12, 2013Publication date: September 18, 2014Inventors: Geoffrey S.M. Hedrick, Shahram Askarpour
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Publication number: 20130218373Abstract: A method and system for highlighting a flight path deviation of an aircraft to a user in a multi-parameter aircraft instrument display, such as a flat panel display. A visibility attribute is configured to toggle between a standard state when the actual aircraft position is within a predetermined range of the target aircraft position, and an enhanced state when the actual aircraft position is outside the predetermined range. The electronic display is configured to highlight a flight path deviation when in the enhanced state, such as by displaying deviation scales having an actual aircraft position indicator relative to the target position, and increasing the size or changing the color of certain displayed elements, or displaying/concealing new elements. Such display features aid in focusing the pilot's attention to deviations from optimal flight paths and ensuring navigation accuracy and, therefore, safety.Type: ApplicationFiled: March 1, 2013Publication date: August 22, 2013Inventors: Geoffrey S.M. Hedrick, Michael Edward Glover
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Patent number: 8364328Abstract: Methods, systems, and apparatuses for the use of a wireless portable avionics device in conjunction with on-board flight systems and/or off-board service providers. The device may be used by aircraft personnel such as pilots and may act as a command/data entry and/or display tool to augment cockpit display systems. The device can receive flight data (e.g., a flight plan) from an off-board provider and automatically transfer it, as well as any previously prepared commands or data, to a flight management system and/or cockpit display systems. Commands and/or data (including pre-existing ones and ones entered in real-time) can be wirelessly transferred to the on-board flight systems which are not in direct physical contact with the device. Thus, the device can be easily manipulated during turbulence or under poor readability conditions. The device can be used to manipulate items shown on cockpit display systems in a timely and accurate manner.Type: GrantFiled: April 14, 2011Date of Patent: January 29, 2013Inventor: Geoffrey S. M. Hedrick
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Patent number: 8352168Abstract: The present invention relates to a system and method for minimizing or preventing runway incursion at airports by utilizing data packets of information transmitted over the voice communication channel used by pilots at the airport. The data packets of information contain the latitudinal and longitudinal position of the aircraft provided by an on board GPS receiver and a unique identifier for the aircraft, such as the tail number, which is then received by other aircraft on the same ground frequency, and the tower, and displayed on a geo-referenced map display of the airport provided to the pilots and the tower ground controller. The information may be updated by polling the various aircraft In this manner, information received from all active aircraft within an airport can be displayed on an electronic map of the airport which can be viewable by the pilots on the ground as well as the ground controller.Type: GrantFiled: October 24, 2011Date of Patent: January 8, 2013Assignee: Innovative Solutions & Support, Inc.Inventor: Geoffrey S. M. Hedrick
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Publication number: 20120296496Abstract: A preexisting FMS system may be upgraded to increase its functionality while still taking advantage of certain components of the legacy system previously provided on the aircraft and replacing other preexisting components with different components for enhancing the functionality of the FMS system. The preexisting IRU, CADC, DME receiver and DFGC in the upgraded FMS system are in communication with the legacy AFMC but, instead of employing the legacy EFIS which existed in the preexisting FMS system, the EFIS is replaced by a data concentrator unit as well as the display control panel and integrated flat panel display, and a GPS receiver. The upgraded FMS system is capable of such increased functionality as increased navigation database storage capacity, RNP, VNAV and RNAV capability utilizing a GPS based navigation solution, and RTA capability, while still enabling the legacy AFMC to exploit its aircraft performance capabilities throughout the flight.Type: ApplicationFiled: May 17, 2011Publication date: November 22, 2012Applicant: Innovative Solutions & Support, Inc.Inventors: Geoffrey S.M. Hedrick, Shahram Askarpour, Markus Knopf
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Publication number: 20120265372Abstract: Methods, systems, and apparatuses for the use of a wireless portable avionics device in conjunction with on-board flight systems and/or off-board service providers. The device may be used by aircraft personnel such as pilots and may act as a command/data entry and/or display tool to augment cockpit display systems. The device can receive flight data (e.g., a flight plan) from an off-board provider and automatically transfer it, as well as any previously prepared commands or data, to a flight management system and/or cockpit display systems. Commands and/or data (including pre-existing ones and ones entered in real-time) can be wirelessly transferred to the on-board flight systems which are not in direct physical contact with the device. Thus, the device can be easily manipulated during turbulence or under poor readability conditions. The device can be used to manipulate items shown on cockpit display systems in a timely and accurate manner.Type: ApplicationFiled: April 14, 2011Publication date: October 18, 2012Inventor: Geoffrey S.M. Hedrick
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Patent number: RE43732Abstract: Dynamic monitoring of the amount of fuel remaining in an aircraft fuel tank is effected by delivering a constant volume flow of an inert gas into the fuel through the respective open distal ends of a sensor conduit tube and a reference conduit tube, each of which extends from a proximal end exterior of the tank to its respective distal open end located within the fuel tank. The sensor conduit tube distal end is fixed closely proximate the bottom of the tank, and the reference conduit tube distal end is fixed proximate but at a vertical spacing h from the sensor conduit tube distal end. The pressure at which the gas is delivered into the fuel at the constant volumetric rate through each of the sensor and reference conduit tubes is monitored. The pressure difference between the monitored pressure in the sensor conduit tube and the pressure in the free space in the fuel tank above the surface of the remaining fuel is directly proportional to the weight of the fuel lying above the sensor conduit tube distal end.Type: GrantFiled: March 9, 2011Date of Patent: October 16, 2012Assignee: Innovative Solutions and Support, Inc.Inventor: Geoffrey S. M. Hedrick