Patents by Inventor Jean-Luc Derouineau
Jean-Luc Derouineau 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: 9911344Abstract: A camera-based obstacle detection system includes a first camera, a second camera, and one or more processors configured to acquire a first image from the first camera, acquire a second image from the second camera, determine a depth of an object based on a location of the object in the first image relative to a location of the object in the second image, and in response to the depth exceeding a threshold depth value, generate an alert.Type: GrantFiled: July 24, 2015Date of Patent: March 6, 2018Assignee: Honeywell International Inc.Inventors: Tomas Kabrt, George Papageorgiou, Jean-Luc Derouineau, Tomas Marczi, Michal Orlita
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Publication number: 20170025024Abstract: A camera-based obstacle detection system includes a first camera, a second camera, and one or more processors configured to acquire a first image from the first camera, acquire a second image from the second camera, determine a depth of an object based on a location of the object in the first image relative to a location of the object in the second image, and in response to the depth exceeding a threshold depth value, generate an alert.Type: ApplicationFiled: July 24, 2015Publication date: January 26, 2017Inventors: Tomas Kabrt, George Papageorgiou, Jean-Luc Derouineau, Tomas Marczi, Michal Orlita
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Publication number: 20160114901Abstract: Methods and system are provided for displaying information on a display device of an aircraft as well as processing crowd sourced information from other aircraft, sensors and information systems in a ground server, and provide it back to aircraft via communication means. In one embodiment, the method includes retrieving information that indicates a current situation and that has been entered by a user, the information being from at least one of a server and another aircraft; determining current situation display data based on the information; and graphically displaying the information on the display based on the current situation display data.Type: ApplicationFiled: September 22, 2015Publication date: April 28, 2016Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Jean-Luc Derouineau, Matej Dusik
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Patent number: 8970423Abstract: A helicopter collision-avoidance system is disclosed. An exemplary system includes at least one lamp, such as a light emitting diode (LED) lamp, an incandescent lamp, a halogen lamp, an infrared lamp, or the like; a radar emitter configured to emit a radar signal; a radar detector configured to receive a radar return signal associated with reflections of the emitted radar signal that are reflected from an object; and a radio frequency (RF) system configured to wirelessly transmit radar information associated with the received radar return signal to a radar information receiver configured to receive the wirelessly transmitted radar information. The light module is located at one of a plurality of light positions on an external surface of a helicopter.Type: GrantFiled: December 6, 2012Date of Patent: March 3, 2015Assignee: Honeywell International Inc.Inventors: Tomas Kabrt, George Papageorgiou, Jean-Luc Derouineau, Michal Orlita
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Patent number: 8958942Abstract: Systems and methods are operable to present braking distance information to crew of an installation aircraft. An exemplary embodiment determines a braking distance for a braking maneuver of the installation aircraft, wherein the braking distance is based on a current ground speed of the aircraft; and generates a graphical representation that is presented on a display, wherein a location of a graphical icon on the graphical representation indicates the determined braking distance from the installation aircraft.Type: GrantFiled: March 14, 2013Date of Patent: February 17, 2015Assignee: Honeywell International Inc.Inventors: Pavel Kolcarek, Jiri Vasek, Tomas Svoboda, Olukayode Olofinboba, Jean-Luc Derouineau
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Publication number: 20120078450Abstract: Methods and systems are provided for executing a single continuous altitude change by an aircraft to cruise altitude using an electronic flight bag via a flight management system. The method comprises the determination of an altitude change in a flight plan during the cruise phase of the flight plan. Based on the altitude change and a mathematical model of the aircraft an optimum vertical trajectory profile or the aircraft is determined from which an angle of attack (AOA) and a thrust is derived to achieve the optimum vertical trajectory. From the AOA and the thrust, the required aircraft control variables are determined that may be applied to the engines and the control surface actuators of the aircraft.Type: ApplicationFiled: September 27, 2010Publication date: March 29, 2012Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Stephane Marche, Petr Krupansky, Tomas Neuzil, George Papageorgiou, Jean-Luc Derouineau
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Patent number: 8093747Abstract: An electrical power system architecture uses an auxiliary power unit as an electrical power source during taxi (ground idle) and approach idle (if required). Using the APU as a power source enables a low pressure spool driven electrical generator to be off-line when its speed is too low for it to operate effectively.Type: GrantFiled: December 3, 2009Date of Patent: January 10, 2012Assignee: Honeywell International, Inc.Inventors: Wayne Pearson, Jean-Luc Derouineau
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Patent number: 7970497Abstract: An aircraft architecture may be designed to create an optimal balance between electric power and bleed power in order to match or improve current more electric architecture (MEA) performance while simplifying power extraction from the engines as well as simplifying the electrical system. Conventional aircraft architectures may use electric only ECS and cabin pressurization systems (so-called “no bleed” systems). Alternatively, older conventional aircraft may use strictly engine bleed air to provide power for ECS and cabin pressurization systems. The present invention, on the other hand, provides an architecture which may optimize the use of both engine bleed air and MEA designs to provide a system that may be simpler and potentially more reliable and available as compared to conventional aircraft architectures.Type: GrantFiled: March 2, 2007Date of Patent: June 28, 2011Assignee: Honeywell International Inc.Inventors: Jean-Luc Derouineau, Wayne T. Pearson, Michel A. Jonqueres
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Publication number: 20110133545Abstract: An electrical power system architecture uses an auxiliary power unit as an electrical power source during taxi (ground idle) and approach idle (if required). Using the APU as a power source enables a low pressure spool driven electrical generator to be off-line when its speed is too low for it to operate effectively.Type: ApplicationFiled: December 3, 2009Publication date: June 9, 2011Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Wayne PEARSON, Jean-Luc DEROUINEAU
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Patent number: 7936086Abstract: A power generation and distribution system utilizes two or more AC generators each of which may be driven by a separate prime mover such as a turbine. The generators may be driven at different rotational speeds. AC power from the generators may be rectified and applied to a common DC bus. Electrical loads may be applied to the common bus and may establish an electrical power requirement. Allocation of electrical power requirement may be made among the generators based on power available from the turbines.Type: GrantFiled: March 6, 2008Date of Patent: May 3, 2011Assignee: Honeywell International, Inc.Inventors: Edwin Yue, Jean-Luc Derouineau, Wayne T. Pearson
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Publication number: 20090326737Abstract: An aircraft architecture may be designed to create an optimal balance between electric power and bleed power in order to match or improve current more electric architecture (MEA) performance while simplifying power extraction from the engines as well as simplifying the electrical system. Conventional aircraft architectures may use electric only ECS and cabin pressurization systems (so-called “no bleed” systems). Alternatively, older conventional aircraft may use strictly engine bleed air to provide power for ECS and cabin pressurization systems. The present invention, on the other hand, provides an architecture which may optimize the use of both engine bleed air and MEA designs to provide a system that may be simpler and potentially more reliable and available as compared to conventional aircraft architectures.Type: ApplicationFiled: March 2, 2007Publication date: December 31, 2009Applicant: HONEYWELL INTERNATIONAL INC.Inventors: JEAN-LUC DEROUINEAU, WAYNE T. PEARSON, MICHEL A. JONQUERES
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Patent number: 7607318Abstract: An integrated environmental control system for an aircraft compartment and aircraft power system comprises first and second air compressors, an auxiliary power unit, and first and second environmental control systems. The first and second compressors receive and compress airflow from the aircraft exterior. The auxiliary power unit comprises a first shaft rotatably mounting a power turbine, a third air compressor to compress airflow from the aircraft exterior, and a first cooling turbine to cool the airflow. Each environmental control system comprises a first heat exchanger, a recycling heat exchanger, and a second shaft rotatably mounting a fourth compressor and a second cooling turbine for compressing and cooling the airflow. The first heat exchanger receives airflow from the first, second, and third air compressors and forwards airflow to the aircraft compartment. The recycling heat exchanger receives airflow from the aircraft compartment and recirculates airflow back to the aircraft compartment.Type: GrantFiled: May 25, 2006Date of Patent: October 27, 2009Assignee: Honeywell International Inc.Inventors: Clarence W. T. Lui, Jean-Luc Derouineau, Henry M. Claeys
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Publication number: 20090224599Abstract: A power generation and distribution system utilizes two or more AC generators each of which may be driven by a separate prime mover such as a turbine. The generators may be driven at different rotational speeds. AC power from the generators may be rectified and applied to a common DC bus. Electrical loads may be applied to the common bus and may establish an electrical power requirement. Allocation of electrical power requirement may be made among the generators based on power available from the turbines.Type: ApplicationFiled: March 6, 2008Publication date: September 10, 2009Inventors: EDWIN YUE, JEAN-LUC DEROUINEAU, Wayne T. Pearson
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Patent number: 7578136Abstract: An integrated power and pressurization management system supplies electrical power and cabin pressurization and cooling air during both airborne and ground operations. The system includes an integral auxiliary power unit (APU) that has a compressor, a motor-generator, and a power turbine all mounted on one shaft. The integral APU can supply compressed air for cabin pressurization and environmental cooling functions, and can generate electrical power for various electrical loads. The system further includes one or more electrically driven compressors.Type: GrantFiled: June 23, 2005Date of Patent: August 25, 2009Assignee: Honeywell International Inc.Inventors: Jean-Luc Derouineau, Bjoern Schenk, Clarence Lui
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Publication number: 20080264084Abstract: An aircraft air conditioning system includes an air supply system (engine bleed or cabin air compressor taking ambient air and pressurizing it at or above cabin pressure) and a cooling system (air cycle or vapor cycle cooling packs to reject heat outside the vessel). These systems can exist as independent systems or combined into a single unit. Air supply and cooling are powered from either engine bleed air or electric power. In order to increase the airflow through the cabin, some cabin air is re-circulated and mixed with fresh air from the air supply system.Type: ApplicationFiled: April 25, 2007Publication date: October 30, 2008Applicant: HONEYWELL INTERNATIONAL INC.Inventors: JEAN-LUC DEROUINEAU, MICHEL A. JONQUERES
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Publication number: 20070271952Abstract: An integrated environmental control system for an aircraft compartment and aircraft power system comprises first and second air compressors, an auxiliary power unit, and first and second environmental control systems. The first and second compressors receive and compress airflow from the aircraft exterior. The auxiliary power unit comprises a first shaft rotatably mounting a power turbine, a third air compressor to compress airflow from the aircraft exterior, and a first cooling turbine to cool the airflow. Each environmental control system comprises a first heat exchanger, a recycling heat exchanger, and a second shaft rotatably mounting a fourth compressor and a second cooling turbine for compressing and cooling the airflow. The first heat exchanger receives airflow from the first, second, and third air compressors and forwards airflow to the aircraft compartment. The recycling heat exchanger receives airflow from the aircraft compartment and recirculates airflow back to the aircraft compartment.Type: ApplicationFiled: May 25, 2006Publication date: November 29, 2007Inventors: Clarence W.T. Lui, Jean-Luc Derouineau, Henry M. Claeys
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Patent number: 7285871Abstract: An engine power extraction control system controls the main propulsion engines and the electrical machines that are coupled thereto to supply an appropriate amount of aircraft thrust and electrical energy to the aircraft. The engines and electrical machines are also controlled so that the propulsion thrust that is generated is split between the various turbines in the main propulsion engines to maintain an adequate surge margin and to minimize residual thrust generation.Type: GrantFiled: July 15, 2005Date of Patent: October 23, 2007Assignee: Honeywell International, Inc.Inventor: Jean-Luc Derouineau
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Patent number: 7124983Abstract: A hybrid electrical ice protection system implements three ice protection methods in various combinations. The ice protection methods include the fully-evaporative anti-ice protection method, the wet running anti-ice protection method, and the de-ice method. The particular methods that are implemented vary, depending on the particular aircraft structure for which ice protection is being provided and on the power condition of the aircraft.Type: GrantFiled: January 24, 2005Date of Patent: October 24, 2006Assignee: Honeywell International, Inc.Inventors: Philip S. Chow, Jean-Luc Derouineau
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Publication number: 20060231680Abstract: An integrated power and pressurization management system supplies electrical power and cabin pressurization and cooling air during both airborne and ground operations. The system includes an integral auxiliary power unit (APU) that has a compressor, a motor-generator, and a power turbine all mounted on one shaft. The integral APU can supply compressed air for cabin pressurization and environmental cooling functions, and can generate electrical power for various electrical loads. The system further includes one or more electrically driven compressors.Type: ApplicationFiled: June 23, 2005Publication date: October 19, 2006Applicant: Honeywell International, Inc.Inventors: Jean-Luc Derouineau, Bjoern Schenk, Clarence Lui
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Publication number: 20060196994Abstract: A hybrid electrical ice protection system implements three ice protection methods in various combinations. The ice protection methods include the fully-evaporative anti-ice protection method, the wet running anti-ice protection method, and the de-ice method. The particular methods that are implemented vary, depending on the particular aircraft structure for which ice protection is being provided and on the power condition of the aircraft.Type: ApplicationFiled: January 24, 2005Publication date: September 7, 2006Inventors: Philip Chow, Jean-Luc Derouineau