Patents by Inventor Stephane Dattler
Stephane Dattler 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: 9014961Abstract: A method and device for aiding the navigation of an aircraft flying at low altitude as described. The device (1) includes positioning means (2) generating the current position of the aircraft, and calculation means (4) for detecting when the budgets allocated to a position error of the aircraft are exceeded by protection ranges.Type: GrantFiled: September 15, 2010Date of Patent: April 21, 2015Assignee: Airbus Operations (SAS)Inventor: Stéphane Dattler
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Patent number: 8755995Abstract: The device (1) comprises a first system (3) which comprises means (14) for calculating the vector difference between a position generated by this first system (3) and a realignment position received from a second system (4), for one and the same date-stamping, and means (16) for adding this difference to any new position of the aircraft, generated by said first system (3), so as to obtain each time a realigned position.Type: GrantFiled: October 20, 2008Date of Patent: June 17, 2014Assignee: Airbus Operations SASInventors: Philippe Haas, Stephane Dattler, Julien Nico
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Patent number: 8275495Abstract: Disclosed is a method and device, which provide an enhanced ability to monitor the navigation of an aircraft during a phase of flight in which the aircraft is close to the ground in which the aircraft uses positional information supplied by a satellite positioning system for the navigation. A display screen is used to display a first characteristic sign representing a selected setpoint value for a height parameter of the aircraft. The display screen also displays a second characteristic sign representing a current auxiliary value expressed in the form of an achievable height parameter. An alert is emitted when the second characteristic sign is determined to be within a predetermined height value of the first characteristic sign, and the alert is shown in visual format on the display screen. An alarm is also emitted following a predetermined time after the alert is emitted, if the setpoint value is not replaced by a new setpoint value.Type: GrantFiled: October 7, 2009Date of Patent: September 25, 2012Assignees: Airbus Operations SAS, AirbusInventors: Fabien Joyeux, Adrien Ott, Melanie Morel, Romain Merat, Stephane Dattler, Francois Barre, Armelle Seillier
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Patent number: 8244467Abstract: The invention relates to a method and device for determining a reliable position of an aircraft. The device (1) includes means (3, 10) for determining different aircraft position values and means (8, 16, 18) for deducing a reliable position therefrom, using coherence tests and a consolidation method.Type: GrantFiled: June 16, 2008Date of Patent: August 14, 2012Assignee: Airbus Operations SASInventors: Jean-Philippe Huynh, Alain Guillet, Stéphane Dattler, Grégory Ortet
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Patent number: 8005614Abstract: A method for monitoring the integrity of an aircraft position computed on board including on-board means for monitoring the aircraft position that are able to detect common-mode failures. Dissimilar computing channels of the aircraft position are utilized, the dissimilar channels being on-board in the aircraft. Each aircraft position primary computing channel is supplemented by a dissimilar computing channel, which allows the coherence of the primary aircraft position, the position computed by the primary computing channels, to be verified. Mechanisms for verifying the reliability of the results from dissimilar computing channels are implemented to limit a loss of performance from the utilization of dissimilar computing channels, which are less performing than primary computing channels.Type: GrantFiled: August 20, 2007Date of Patent: August 23, 2011Assignee: Airbus FranceInventors: Stéphane Dattler, Vincent Markiton
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Publication number: 20110066370Abstract: A method and device for aiding the navigation of an aircraft flying at low altitude as described. The device (1) includes positioning means (2) generating the current position of the aircraft, and calculation means (4) for detecting when the budgets allocated to a position error of the aircraft are exceeded by protection ranges.Type: ApplicationFiled: September 15, 2010Publication date: March 17, 2011Applicant: AIRBUS OPERATIONS (SAS)Inventor: Stephane Dattler
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Patent number: 7908046Abstract: A device and method calculate a global error relating to a position indication of an aircraft and compare the global error with a threshold value, which depends on flight constraints.Type: GrantFiled: May 19, 2008Date of Patent: March 15, 2011Assignee: Airbus FranceInventors: Jean-Philippe Huynh, Alain Guillet, Stephane Dattler, Gregory Ortet
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Patent number: 7764198Abstract: An aircraft standby display device includes a set of data sources, a data processing unit, and a display. The display presents altitude control indicators representing speed, altitude, attitude, and a heading scale that includes a characteristic symbol indicating a next route point of an aircraft flight plan. The heading scale is independent of the altitude control indicators. The display also presents a quantitative value that: (1) indicates the remaining distance of flight of the aircraft to reach the next route point and (2) is associated with the characteristic symbol.Type: GrantFiled: July 27, 2005Date of Patent: July 27, 2010Assignee: Airbus FranceInventors: Didier Brehin, Stephane Dattler
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Publication number: 20100169014Abstract: The invention relates to a method and device for determining a reliable position of an aircraft. The device (1) includes means (3, 10) for determining different aircraft position values and means (8, 16, 18) for deducing a reliable position therefrom, using coherence tests and a consolidation method.Type: ApplicationFiled: June 16, 2008Publication date: July 1, 2010Applicant: Airbus Operations (SAS)Inventors: Jean-Philippe Huynh, Alain Guillet, Stéphane Dattler, Grégory Ortet
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Publication number: 20100094486Abstract: The device (1) comprises a screen (13) which simultaneously displays a sign representing a selected setpoint value relating to a height parameter which is used during the phase of flight, and a sign illustrating a corresponding value which is representative of an estimated positional error.Type: ApplicationFiled: October 7, 2009Publication date: April 15, 2010Applicants: AIRBUS OPERATIONS (SAS), AIRBUSInventors: Fabien Joyeux, Adrien Ott, Melanie Morel, Romain Merat, Stephane Dattler, François Barre, Armelle Seillier
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Publication number: 20090224945Abstract: The invention concerns a device comprising a set of data sources, a data processing unit, and a display which presents on a display unit (8) altitude control indicators (9, 10, 11) representing at least speed, altitude and altitude data of the aircraft and a heading scale (12) including a characteristic symbol (13) indicating at least one next route point of the aircraft flight plan, said heading scale (12) being independent of said altitude control indicators (9, 10, 11), as well as a quantitative value (14) which indicates the remaining distance of flight of the aircraft to reach said next route point and which is associated with said characteristic symbol (13).Type: ApplicationFiled: July 27, 2005Publication date: September 10, 2009Applicant: AIRBUS FRANCEInventors: Didier Brehin, Stephane Dattler
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Patent number: 7554483Abstract: The subject of the invention is a method of aiding the piloting of an aircraft (3), which is intended to aid the piloting of the aircraft during an autonomous approach to a landing runway (P) for the purpose of landing, said aircraft comprising at least one locating means (10, 12), wherein: a) an estimated instant of arrival of the aircraft on the runway is determined; b) a prediction of the performance of said locating means of the aircraft at least at this instant of arrival is determined; and c) on the basis of said performance of the locating means and of characteristics of said approach, at least one minimum decision height (Hmin) corresponding to this instant of arrival is determined, above which the aircraft is protected from the risks of collision with the environment when it is guided automatically onto an approach axis (A) corresponding to said approach. The invention also relates to a device for implementing this method.Type: GrantFiled: July 31, 2007Date of Patent: June 30, 2009Assignee: Airbus FranceInventors: Vincent Markiton, Stéphane Dattler
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Publication number: 20090105951Abstract: The device (1) comprises a first system (3) which comprises means (14) for calculating the vector difference between a position generated by this first system (3) and a realignment position received from a second system (4), for one and the same date-stamping, and means (16) for adding this difference to any new position of the aircraft, generated by said first system (3), so as to obtain each time a realigned position.Type: ApplicationFiled: October 20, 2008Publication date: April 23, 2009Applicant: AIRBUS FranceInventors: Philippe Haas, Stephane Dattler, Julien Nico
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Publication number: 20080294306Abstract: The device (1) comprises means (8, 9, 10) for calculating a global error relating to a position indication of the aircraft, means (13) for comparing this global error with a threshold value which depends on the flight constraints, and alarm means (15).Type: ApplicationFiled: May 19, 2008Publication date: November 27, 2008Applicant: AIRBUS FranceInventors: Jean-Philippe Huynh, Alain Guillet, Stephane Dattler, Gregory Ortet
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Publication number: 20080150785Abstract: The subject of the invention is a method of aiding the piloting of an aircraft (3), which is intended to aid the piloting of the aircraft during an autonomous approach to a landing runway (P) for the purpose of landing, said aircraft comprising at least one locating means (10, 12), wherein: a) an estimated instant of arrival of the aircraft on the runway is determined; b) a prediction of the performance of said locating means of the aircraft at least at this instant of arrival is determined; and c) on the basis of said performance of the locating means and of characteristics of said approach, at least one minimum decision height (Hmin) corresponding to this instant of arrival is determined, above which the aircraft is protected from the risks of collision with the environment when it is guided automatically onto an approach axis (A) corresponding to said approach. The invention also relates to a device for implementing this method.Type: ApplicationFiled: July 31, 2007Publication date: June 26, 2008Applicant: AIRBUS FRANCEInventors: Vincent Markiton, Stephane Dattler
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Publication number: 20080046141Abstract: A method for monitoring the integrity of an aircraft position computed on board including on-board means for monitoring the aircraft position that are able to detect common-mode failures. Dissimilar computing channels of the aircraft position are utilized, the dissimilar channels being on-board in the aircraft. Each aircraft position primary computing channel is supplemented by a dissimilar computing channel, which allows the coherence of the primary aircraft position, the position computed by the primary computing channels, to be verified. Mechanisms for verifying the reliability of the results from dissimilar computing channels are implemented to limit a loss of performance from the utilization of dissimilar computing channels, which are less performing than primary computing channels.Type: ApplicationFiled: August 20, 2007Publication date: February 21, 2008Applicant: AIRBUS FRANCEInventors: Stephane Dattler, Vincent Markiton