Patents by Inventor Franck Delaplace
Franck Delaplace 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: 9457888Abstract: According to the invention, high lift leading-edge slats (13) and high lift flaps (14) are simultaneously deployed, when the speed of the aircraft is equal to and less than an AES threshold.Type: GrantFiled: June 7, 2007Date of Patent: October 4, 2016Assignee: AIRBUS OPERATIONS SASInventors: Franck Delaplace, Martin Richter, Dieter Lang
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Patent number: 8798810Abstract: An energy protecting device for three and four-engined aircraft includes a detecting unit configured to detect failure of each engine. A control unit is configured to provide a protective function by controlling maximum thrust of each engine. A triggering unit is configured to monitor a plurality of parameters and trigger the control unit to provide maximum thrust at predetermined conditions of the monitored parameters. An inhibiting unit is linked to the triggering unit and is configured to inhibit the protective function, when at least one of the engine on the wings of the aircraft has failed. The control unit is also configured to control the engines that have not failed to minimize thrust imbalance.Type: GrantFiled: September 12, 2006Date of Patent: August 5, 2014Assignee: Airbus Operations SASInventors: Franck Delaplace, Didier Ronceray, Jean Muller
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Patent number: 8083178Abstract: In conformance with the invention, based on the incident conditions and velocity, the steering of the ailerons is weakly negative (b0) or corresponds either to the maximum sharpness of the aircraft (b1), or the optimal lift of the latter (b2).Type: GrantFiled: May 21, 2007Date of Patent: December 27, 2011Assignee: Airbus Operations SASInventors: Franck Delaplace, Sophie Lambeaux, Frédéric Sauvinet
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Patent number: 8014910Abstract: A reference value is arbitrarily selected from a range of possible aircraft rotation speeds. A position of a trimmable horizontal stabilizer is angled in accordance with a centering of the reference value. A deviation between the reference value and an accelerating speed value of the aircraft is determined. Elevators or the horizontal stabilizer are controlled, prior to rotation, in accordance with the determined deviation.Type: GrantFiled: May 4, 2006Date of Patent: September 6, 2011Assignee: Airbus FranceInventors: Gerard Mathieu, Franck Delaplace, Xavier Le Tron
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Patent number: 7850125Abstract: The invention relates to a method and device for reducing the wake vortices of an aircraft during the approach/landing phase. Spoilers are automatically ordered to deploy when lift-augmenting aerodynamic surfaces are ordered to deploy, and are automatically ordered to retract when at least one of the following three conditions holds: the angle of incidence ? of the aircraft is equal to or greater than an incidence threshold ?s; the speed Vc of the aircraft is equal to or less than a speed threshold Vs; and the aircraft is instigating a go-around maneuver.Type: GrantFiled: April 19, 2007Date of Patent: December 14, 2010Assignee: Airbus FranceInventor: Franck Delaplace
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Publication number: 20090230253Abstract: In conformance with the invention, based on the incident conditions and velocity, the steering of the ailerons is weakly negative (b0) or corresponds either to the maximum sharpness of the aircraft (b1), or the optimal lift of the latter (b2).Type: ApplicationFiled: May 21, 2007Publication date: September 17, 2009Applicant: Airbus FranceInventors: Franck Delaplace, Sophie Lambeaux, Frederic Sauvinet
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Publication number: 20090152403Abstract: According to the invention, high lift Leading-edge slats (13) and high lift flaps (14) are simultaneously deployed, when the speed of the aircraft is equal to and less than an AES threshold.Type: ApplicationFiled: June 7, 2007Publication date: June 18, 2009Applicants: AIRBUS FRANCE, AIRBUS DEUTSCHALND GMBHInventors: Franck Delaplace, Martin Richter, Dieter Lang
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Publication number: 20080208398Abstract: The invention concerns a device (1) comprising control means (3) for activating a protective function which consists in automatically controlling the engines (M1 to M4) so that they supply maximum power when the triggering conditions are fulfilled, and inhibiting means (8) for inhibiting the protective function solely when all the engines which are arranged on a common wing of the aircraft have simultaneously broken down.Type: ApplicationFiled: September 12, 2006Publication date: August 28, 2008Applicant: AIRBUS FRANCEInventors: Franck Delaplace, Didier Ronceray, Jean Muller
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Publication number: 20080188999Abstract: A reference value VRef is arbitrarily selected from the range of possible rotation speeds, the position of the trimmable horizontal stabiliser is angled at least in accordance with the centring, for said value VRef, the deviation between said reference value and the accelerating aircraft speed value VC is determined, and the elevators and/or the trimmable horizontal stabiliser of the aircraft are controlled, prior to rotation, in such a way that said deviation is taken into account.Type: ApplicationFiled: May 4, 2005Publication date: August 7, 2008Applicant: AIRBUS FRANCEInventors: Gerard Mathieu, Franck Delaplace, Xavier Le Tron
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Patent number: 7382283Abstract: Detection of the overstepping of design loads of an aircraft tailplane may include determining current bending and twisting moments applied to the aircraft. The determined bending and twisting moments are compared with a safety envelope to determine the risk of developing permanent deformations on the tailplane. A determination is made as to whether a structural inspection of the tailplane should be performed based on the comparison result.Type: GrantFiled: June 7, 2005Date of Patent: June 3, 2008Assignee: Airbus FranceInventors: Franck Delaplace, Sylvie Marquier, Gérard Mathieu, Gennaro Squeglia
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Patent number: 7366592Abstract: A control system for an aircraft includes an actuation section that moves lift-enhancing devices as a function of received control orders, a control member operable by a pilot of the aircraft, and a control unit that includes a control section that produces control orders, as a function of actuation of the control member, so as to control the actuation section to bring the lift-enhancing devices into a predetermined position. The control unit further includes a device that produces automatically auxiliary control orders which are transmitted to the actuation section to automatically retract the lift-enhancing devices when the aircraft is in a first flight condition and another device that automatically disables control orders produced by the control section following actuation of the control member to deploy the lift-enhancing devices when the aircraft is in a second flight condition.Type: GrantFiled: July 14, 2004Date of Patent: April 29, 2008Assignee: Airbus FranceInventors: Franck Delaplace, Dominique Buisson
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Publication number: 20080097728Abstract: Detection of the overstepping of design loads of an aircraft tailplane may include determining current bending and twisting moments applied to the aircraft. The determined bending and twisting moments are compared with a safety envelope to determine the risk of developing permanent deformations on the tailplane. A determination is made as to whether a structural inspection of the tailplane should be performed based on the comparison result.Type: ApplicationFiled: June 7, 2005Publication date: April 24, 2008Applicant: AIRBUS FRANCEInventors: Franck Delaplace, Sylvie Marquier, Gerard Mathieu, Gennaro Squeglia
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Patent number: 7281683Abstract: An aircraft takeoff process may include applying a pitch command deflecting an adjustable horizontal tailplane of the aircraft by a predetermined angle. Thereafter, the pitch command is corrected in accordance with the deviation between a takeoff rotation speed and a stall reference speed VRref of the aircraft.Type: GrantFiled: April 22, 2005Date of Patent: October 16, 2007Assignee: Airbus FranceInventors: Franck Delaplace, Gérard Mathieu, Nicolas Daniel
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Patent number: 7271741Abstract: A method and device for detecting an overstepping of design loads of the fin of an aircraft. The device includes a set of information sources and a section for determining, with the aid of information emanating from the set of information sources, a current bending moment. The device further includes a section for determining, with the aid of information emanating from the set of information sources, a current twisting moment, and a section for carrying out a comparison by comparing the pair formed by the current bending moment and the current twisting moment with a safety envelope representing a chart formed in a plane on the basis of pairs of values of bending and twisting moments and defined so that, for any pair which lies outside the safety envelope, there exists a risk of appearance of permanent deformation on the fin.Type: GrantFiled: June 3, 2005Date of Patent: September 18, 2007Assignee: Airbus FranceInventors: Franck Delaplace, Sylvie Marquier, Gérard Mathieu, Gennaro Squeglia
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Publication number: 20070185628Abstract: A control system for an aircraft includes an actuation section that moves lift-enhancing devices as a function of received control orders, a control member operable by a pilot of the aircraft, and a control unit that includes a control section that produces control orders, as a function of actuation of the control member, so as to control the actuation section to bring the lift-enhancing devices into a predetermined position. The control unit further includes a device that produces automatically auxiliary control orders which are transmitted to the actuation section to automatically retract the lift-enhancing devices when the aircraft is in a first flight condition and another device that automatically disables control orders produced by the control section following actuation of the control member to deploy the lift-enhancing devices when the aircraft is in a second flight condition.Type: ApplicationFiled: July 14, 2004Publication date: August 9, 2007Applicant: AIRBUS FranceInventors: Franck Delaplace, Dominique Buisson
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Publication number: 20070170313Abstract: According to the invention, the spoilers are automatically ordered to deploy when the lift-augmenting aerodynamic surfaces are themselves ordered to deploy and are automatically ordered to retract when at least one of the following three conditions holds: the angle of incidence ? of the aircraft is equal to or greater than an incidence threshold ?s; the speed Vc of the aircraft is equal to or less than a speed threshold Vs; and the aircraft is instigating a go-around maneuver.Type: ApplicationFiled: April 19, 2007Publication date: July 26, 2007Applicant: AIRBUS FRANCEInventor: Franck DELAPLACE
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Publication number: 20070136030Abstract: The device (1) comprises a set (2) of information sources, means (3) for determining, with the aid of information emanating from said set (2), a current bending moment, means (5) for determining, with the aid of information emanating from said set (2), a current twisting moment, means (7) for carrying out a comparison by comparing the pair formed by the current bending moment and the current twisting moment with a safety envelope representing a chart formed in a plane on the basis of pairs of values of bending and twisting moments and defined so that, for any pair which lies outside the safety envelope, there exists a risk of appearance of permanent deformations on the fin, and means (10) for determining whether a structural inspection of the fin has to be performed, at least on the basis of the result of said comparison.Type: ApplicationFiled: June 3, 2005Publication date: June 14, 2007Applicant: AIRBUS FranceInventors: Franck Delaplace, Sylvie Marquier, Gerard Mathieu, Gennaro Squeglia
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Patent number: 7164366Abstract: A process and device for detecting on an aircraft an overshoot of design loads at the level of a structural part of the aircraft. The detection device includes a speed measuring device for measuring an effective speed of the aircraft. A first comparator compares the measured effective speed with a maximum speed relating to the current flight configuration of the aircraft. A vertical load measuring device measures a vertical load factor of the aircraft, and a second comparator compares the measured vertical load factor with a limit value of the vertical load factor. An inspection determining device determines whether a structural inspection needs to be performed at the level of the structural part, based of the results of the first and second comparisons.Type: GrantFiled: November 30, 2004Date of Patent: January 16, 2007Assignee: Airbus FranceInventors: Franck Delaplace, Sylvie Marquier, Gérard Mathieu, Gennaro Squeglia
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Publication number: 20050242235Abstract: Process for aiding the takeoff of an aircraft. According to the invention, a reference speed VRref is chosen arbitrarily and the deviation existing between this reference value and the rotation speed value is determined and the elevators and/or the adjustable horizontal tailplane of the aircraft (1) is/are acted upon to take account of said deviation.Type: ApplicationFiled: April 22, 2005Publication date: November 3, 2005Applicant: AIRBUS FRANCEInventors: Franck Delaplace, Gerard Mathieu, Nicolas Daniel
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Publication number: 20050192718Abstract: Process and device for detecting on an aircraft an overshoot of design loads at the level of a structural part of said aircraft. The detection device (1) comprises means (2) for measuring an effective speed of the aircraft, means (3) for carrying out a first comparison, by comparing this measured effective speed with at least one maximum speed relating at least to the current flight configuration of the aircraft, means (7) for measuring a vertical load factor of the aircraft, means (8) for carrying out a second comparison, by comparing said measured vertical load factor with at least one limit value of vertical load factor, and means (5) for determining whether a structural inspection needs to be performed at the level of said structural part, at least on the basis of the results of said first and second comparisons.Type: ApplicationFiled: November 30, 2004Publication date: September 1, 2005Applicant: AIRBUS FRANCEInventors: Franck Delaplace, Sylvie Marquier, Gerard Mathieu, Gennaro Squeglia