Patents by Inventor Lionel Iraudo
Lionel Iraudo 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: 10024686Abstract: A method having a preparation stage for preparing an approach path (25) to a theoretical position (20?) of a platform (20). During a consolidation stage, a current position (20?) of said platform (20) is determined and an alert is triggered when the distance (D1) between said theoretical position (20?) and said current position (20?) is greater than a first threshold. During a security stage, entities provided with respective automatic identification systems and present in a predetermined monitoring zone (OCZ) are monitored, and a horizontal representation of said approach path (25) is displayed on a display screen (8) together with the following for each entity: a plot (41) representing its current position; an indication (42) of the travel direction of the entity; and a representation (43) relating to the danger level of the entity.Type: GrantFiled: June 3, 2014Date of Patent: July 17, 2018Assignee: Airbus HelicoptersInventors: Nicolas Canale, Lionel Iraudo
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Patent number: 9611053Abstract: A method of facilitating the approach to a platform by an aircraft. The value of the required position integrity performance (RNP) is determined for a localization system. During an approach stage, this position integrity performance (RNP) is compared with a position integrity radius (HPL) resulting from the use of a GNSS localization system, and an alert is generated if the position integrity radius (HPL) is greater than the position integrity performance (RNP).Type: GrantFiled: June 24, 2015Date of Patent: April 4, 2017Assignee: Airbus HelicoptersInventors: Nicolas Canale, Lionel Iraudo
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Patent number: 9446855Abstract: A method of facilitating the approach to a platform by an aircraft, the method comprising a step of constructing a database, including for each stored platform at least one identifier of the platform, coordinates of a geometrical center of the platform, a height of the geometrical center, and the radius (OR) of a circle in which the platform lies. During a parameter-setting step, the target platform to be reached, a course to be followed, and a height parameter relative to a minimum decision altitude are determined. During a path construction step, the positions of an initial approach fix (IAF), of a final approach fix (FAF), and of a decision point (MAP) are determined by placing them in a plane that is offset relative to the platform.Type: GrantFiled: June 24, 2015Date of Patent: September 20, 2016Assignee: Airbus HelicoptersInventors: Nicolas Canale, Lionel Iraudo
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Patent number: 9346553Abstract: The present invention relates to a method and to an associated fuel metering system for balancing the power delivered by two aircraft turboshaft engines by determining first and second limiting margins of the engines (M1, M2) which are transformed into first and second power margins. Thereafter, the values of the first and second power margins are compared in order to determine a primary difference between said first and second power margins. Finally, the engine having the greater power margin is accelerated in order to balance the first and second engines in power by minimizing the primary difference to as great as extent as possible.Type: GrantFiled: June 19, 2007Date of Patent: May 24, 2016Assignee: Airbus HelicoptersInventors: François-Xavier Gaulmin, Lionel Iraudo, Daniel Chaniot
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Publication number: 20150375872Abstract: A method of facilitating the approach to a platform by an aircraft. The value of the required position integrity performance (RNP) is determined for a localization system. During an approach stage, this position integrity performance (RNP) is compared with a position integrity radius (HPL) resulting from the use of a GNSS localization system, and an alert is generated if the position integrity radius (HPL) is greater than the position integrity performance (RNP).Type: ApplicationFiled: June 24, 2015Publication date: December 31, 2015Inventors: Nicolas CANALE, Lionel IRAUDO
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Publication number: 20150375871Abstract: A method of facilitating the approach to a platform by an aircraft, the method comprising a step of constructing a database, including for each stored platform at least one identifier of the platform, coordinates of a geometrical center of the platform, a height of the geometrical center, and the radius (OR) of a circle in which the platform lies. During a parameter-setting step, the target platform to be reached, a course to be followed, and a height parameter relative to a minimum decision altitude are determined. During a path construction step, the positions of an initial approach fix (IAF), of a final approach fix (FAF), and of a decision point (MAP) are determined by placing them in a plane that is offset relative to the platform.Type: ApplicationFiled: June 24, 2015Publication date: December 31, 2015Inventors: Nicolas CANALE, Lionel IRAUDO
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Patent number: 9189963Abstract: A procedure for facilitating the approach to a platform [PF] with an aircraft [1] including a construction stage [STP1] for a database [5] that includes, for each stored platform [PF], attributes that include at least one platform identifier, the coordinates of the platform, a landing height [HDECK] of a landing zone of the platform, and the radius (OR) of a circle within which the platform is inscribed. During a parameterization stage [STP2], the target platform to be reached is determined, along with a course (CRS) to be followed and a height parameter relative to a minimum decision altitude (MDA). During a construction stage [STP3], the position of an initial approach fix (IAF) is determined, along with the position of a final approach fix (FAF), an offset point (OIP), and a decision point (MAP), in response to the information and in response to the attributes.Type: GrantFiled: February 25, 2014Date of Patent: November 17, 2015Assignee: Airbus HelicoptersInventors: Lionel Iraudo, Nicolas Canale
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Patent number: 9151637Abstract: A method having a preparation stage for preparing an approach path (25) to a theoretical position (20?) of a platform (20). During a consolidation stage, a current position (20?) of said platform (20) is determined and an alert is triggered when the distance (D1) between said theoretical position (20?) and said current position (20?) is greater than a first threshold. During a security stage, entities provided with respective automatic identification systems and present in a predetermined monitoring zone (OCZ) are monitored, and a horizontal representation of said approach path (25) is displayed on a display screen (8) together with the following for each entity: a plot (41) representing its current position; an indication (42) of the travel direction of the entity; and a representation (43) relating to the danger level of the entity.Type: GrantFiled: June 3, 2014Date of Patent: October 6, 2015Assignee: Airbus HelicoptersInventors: Nicolas Canale, Lionel Iraudo
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Publication number: 20140365045Abstract: A method having a preparation stage for preparing an approach path (25) to a theoretical position (20?) of a platform (20). During a consolidation stage, a current position (20?) of said platform (20) is determined and an alert is triggered when the distance (D1) between said theoretical position (20?) and said current position (20?) is greater than a first threshold. During a security stage, entities provided with respective automatic identification systems and present in a predetermined monitoring zone (OCZ) are monitored, and a horizontal representation of said approach path (25) is displayed on a display screen (8) together with the following for each entity: a plot (41) representing its current position; an indication (42) of the travel direction of the entity; and a representation (43) relating to the danger level of the entity.Type: ApplicationFiled: June 3, 2014Publication date: December 11, 2014Applicant: AIRBUS HELICOPTERSInventors: Nicolas CANALE, Lionel IRAUDO
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Publication number: 20140365044Abstract: A method having a preparation stage for preparing an approach path (25) to a theoretical position (20?) of a platform (20). During a consolidation stage, a current position (20?) of said platform (20) is determined and an alert is triggered when the distance (D1) between said theoretical position (20?) and said current position (20?) is greater than a first threshold. During a security stage, entities provided with respective automatic identification systems and present in a predetermined monitoring zone (OCZ) are monitored, and a horizontal representation of said approach path (25) is displayed on a display screen (8) together with the following for each entity: a plot (41) representing its current position; an indication (42) of the travel direction of the entity; and a representation (43) relating to the danger level of the entity.Type: ApplicationFiled: June 3, 2014Publication date: December 11, 2014Applicant: AIRBUS HELICOPTERSInventors: Nicolas CANALE, Lionel IRAUDO
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Publication number: 20140244079Abstract: A procedure for facilitating the approach to a platform [PF] with an aircraft [1] including a construction stage [STP1] for a database [5] that includes, for each stored platform [PF], attributes that include at least one platform identifier, the coordinates of the platform, a landing height [HDECK] of a landing zone of the platform, and the radius (OR) of a circle within which the platform is inscribed. During a parameterization stage [STP2], the target platform to be reached is determined, along with a course (CRS) to be followed and a height parameter relative to a minimum decision altitude (MDA). During a construction stage [STP3], the position of an initial approach fix (IAF) is determined, along with the position of a final approach fix (FAF), an offset point (OIP), and a decision point (MAP), in response to the information and in response to the attributes.Type: ApplicationFiled: February 25, 2014Publication date: August 28, 2014Applicant: AIRBUS HELICOPTERSInventors: Lionel IRAUDO, Nicolas CANALE
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Patent number: 8121773Abstract: The present invention relates to a method and to an instrument for determining the limiting margin of a surveillance parameter of a turboshaft engine. During a preliminary stage, a secondary processor means (11) determines a preliminary comfort margin. Thereafter, during a main stage, it estimates a useful comfort margin from the preliminary comfort margin, and then an apparent difference between the current value and the limit value of the surveillance parameter, and finally the limiting margin by subtracting the useful comfort margin from the apparent difference.Type: GrantFiled: June 7, 2007Date of Patent: February 21, 2012Assignee: EurocopterInventors: François-Xavier Gaulmin, Lionel Iraudo
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Patent number: 8050842Abstract: The present invention relates to a method and to an apparatus (9) for controlling and regulating a rotorcraft turbine engine (1). The apparatus is provided with an electronic control and regulation computer (3) that receives signals relating to monitored parameters of the turbine engine (1). The apparatus is remarkable in that it is provided with an alarm (4) controlled by the electronic computer (3) via an analog connection (8) to operate whenever an event occurs that might diminish the safety of the rotorcraft.Type: GrantFiled: June 20, 2008Date of Patent: November 1, 2011Assignee: EurocopterInventor: Lionel Iraudo
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Patent number: 7769521Abstract: The present invention relates to a method and to a device (D) enabling a health check to be performed on at least a first turbine engine (M1) of a rotorcraft, the rotorcraft being provided with first and second turbine engines (M1 and M2) controlled respectively by first and second control means (MC1 and MC2). The device is remarkable in that it comprises check means (C) provided with main means (C1), the main means (C1) controlling the first and second control means (MC1 and MC2) so that the surveillance parameters of the first and second turbine engines (M1 and M2) respectively reach the real first and second final values (V1f and V2f) as determined in accordance with the method of the invention.Type: GrantFiled: April 4, 2007Date of Patent: August 3, 2010Assignee: EurocopterInventors: Francois-Xavier Gaulmin, Lionel Iraudo
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Patent number: 7717369Abstract: The present invention relates to a power plant (18) comprising at least one turboshaft engine (8) behind a gearbox (7) for driving a rotor (3) of a rotary wing aircraft (1), the air inlet body (20) of the engine (8) having a first end (21) opening out into the ambient atmosphere in front of the engine, and a second end (22) connected to the engine at the rearmost portion thereof.Type: GrantFiled: April 30, 2007Date of Patent: May 18, 2010Assignee: EurocopterInventors: Daniel Chaniot, François-Xavier Gaulmin, Lionel Iraudo
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Publication number: 20080319629Abstract: The present invention relates to a method and to apparatus (9) for controlling and regulating a rotorcraft turbine engine (1) provided with an electronic control and regulation computer (3) that receives signals relating to monitored parameters of said turbine engine (1). The apparatus is remarkable in that it is provided alarm means (4) controlled by said electronic computer (3) via an analog connection (8) to operate whenever an event occurs that might diminish the safety of said rotorcraft.Type: ApplicationFiled: June 20, 2008Publication date: December 25, 2008Applicant: EUROCOPTERInventor: Lionel IRAUDO
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Publication number: 20080275597Abstract: The present invention relates to a method and to an associated fuel metering system for balancing the power delivered by two aircraft turboshaft engines by determining first and second limiting margins of the engines (M1, M2) which are transformed into first and second power margins. Thereafter, the values of the first and second power margins are compared in order to determine a primary difference between said first and second power margins. Finally, the engine having the greater power margin is accelerated in order to balance the first and second engines in power by minimizing the primary difference to as great as extent as possible.Type: ApplicationFiled: June 19, 2007Publication date: November 6, 2008Applicant: EUROCOPTERInventors: Francois-Xavier GAULMIN, Lionel IRAUDO, Daniel CHANIOT
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Publication number: 20080173768Abstract: The present invention relates to a power plant (18) comprising at least one turboshaft engine (8) behind a gearbox (7) for driving a rotor (3) of a rotary wing aircraft (1), the air inlet body (20) of the engine (8) having a first end (21) opening out into the ambient atmosphere in front of the engine, and a second end (22) connected to the engine at the rearmost portion thereof.Type: ApplicationFiled: April 30, 2007Publication date: July 24, 2008Applicant: EUROCOPTERInventors: Daniel Chaniot, Francois-Xavier Gaulmin, Lionel Iraudo
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Publication number: 20080125931Abstract: The present invention relates to a method and to an instrument for determining the limiting margin of a surveillance parameter of a turboshaft engine. During a preliminary stage, a secondary processor means (11) determines a preliminary comfort margin. Thereafter, during a main stage, it estimates a useful comfort margin from the preliminary comfort margin, and then an apparent difference between the current value and the limit value of the surveillance parameter, and finally the limiting margin by subtracting the useful comfort margin from the apparent difference.Type: ApplicationFiled: June 7, 2007Publication date: May 29, 2008Applicant: EUROCOPTERInventors: Francois-Xavier Gaulmin, Lionel Iraudo
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Publication number: 20070260391Abstract: The present invention relates to a method and to a device (D) enabling a health check to be performed on at least a first turbine engine (M1) of a rotorcraft, the rotorcraft being provided with first and second turbine engines (M1 and M2) controlled respectively by first and second control means (MC1 and MC2). The device is remarkable in that it comprises check means (C) provided with main means (C1), the main means (C1) controlling the first and second control means (MC1 and MC2) so that the surveillance parameters of the first and second turbine engines (M1 and M2) respectively reach the real first and second final values (V1f and V2f) as determined in accordance with the method of the invention.Type: ApplicationFiled: April 4, 2007Publication date: November 8, 2007Applicant: EUROCOPTERInventors: Francois-Xavier Gaulmin, Lionel Iraudo