Patents by Inventor Alain Bignolais
Alain Bignolais 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: 11572187Abstract: A pivoting connection device connecting at least two components and comprising an end fitting having first and second branches, an arm positioned between the first and second branches of the end fitting, a cylindrical axle connecting the end fitting and the arm and having, at one of the ends thereof, a first portion configured to expand radially, a cylindrical rod configured to be screwed into a tapped portion of the cylindrical axle, an insert fitted on the cylindrical rod and movable between a first position, in which the first portion is not expanded, and a second position, in which the first portion is expanded radially, and a nut configured to be screwed on the cylindrical rod to urge the insert into the second position.Type: GrantFiled: May 17, 2019Date of Patent: February 7, 2023Assignee: AIRBUS OPERATIONS SASInventors: Christian Fabre, Alain Bignolais, Paolo Messina, Thomas Bourdieu
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Publication number: 20190359344Abstract: A pivoting connection device connecting at least two components and comprising an end fitting having first and second branches, an arm positioned between the first and second branches of the end fitting, a cylindrical axle connecting the end fitting and the arm and having, at one of the ends thereof, a first portion configured to expand radially, a cylindrical rod configured to be screwed into a tapped portion of the cylindrical axle, an insert fitted on the cylindrical rod and movable between a first position, in which the first portion is not expanded, and a second position, in which the first portion is expanded radially, and a nut configured to be screwed on the cylindrical rod to urge the insert into the second position.Type: ApplicationFiled: May 17, 2019Publication date: November 28, 2019Inventors: Christian FABRE, Alain BIGNOLAIS, Paolo MESSINA, Thomas BOURDIEU
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Patent number: 10408253Abstract: A method and equipment for installing a tapped insert in a cylindrical bore, the equipment including a tool body comprising a threaded end portion, the threaded end portion being adapted to a threaded inner wall portion of a cylindrical body of the tapped insert; a screw of diameter lower than a diameter of an inner bore of the tool body, the comprising at one end a thread complementary to the inner tapped aperture of the core of the tapped insert; and a positioning ring installed to slide on the tool body, the tool body and the positioning ring comprising complementary sliding means adapted to enable relative sliding of the positioning ring on the tool body in a longitudinal direction and to maintain the positioning ring on the tool body in a defined longitudinal transverse section.Type: GrantFiled: March 30, 2016Date of Patent: September 10, 2019Assignee: AIRBUS OPERATIONS (S.A.S.)Inventors: Christian Fabre, Alain Bignolais
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Patent number: 10029827Abstract: A stopper for a tank having an opening includes a body which is provided to be fixed in the opening and which has a hole, a membrane which is fixed to the body and of which a portion completely blocks the hole, a core which is fixed to the portion of the membrane which blocks the hole, and stop means which are provided to permit a movement of the core between a blocking position which corresponds to the non-broken membrane which blocks the hole, and an open position which corresponds to the broken membrane which is spaced apart from the hole, and to keep the core fixedly joined to the body in an open position. The knowledge of the characteristics of the membrane enables the force from which the stopper opens to be known.Type: GrantFiled: September 30, 2015Date of Patent: July 24, 2018Assignee: Airbus Operations S.A.S.Inventors: Christian Fabre, Alain Bignolais
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Patent number: 9624790Abstract: A locking system comprising a handle mounted such that it can rotate about an operating spindle, wherein the handle can move between a locked position and an unlocked position, a hook mounted on the handle and secured in rotation therewith, wherein the hook has a throat in which a latching point of a structure is designed to engage when the handle is in the locked position. The locking system comprises a key associated with the hook and by means of which it is possible to pass from the locked position to the unlocked position of the handle, wherein the key can be removed when the handle is in the locked position and cannot be removed when the handle is in the unlocked position.Type: GrantFiled: December 18, 2014Date of Patent: April 18, 2017Assignee: Airbus Operations SASInventors: Christian Fabre, Alain Bignolais
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Patent number: 9604728Abstract: The invention relates to an aircraft turbojet nacelle including a cowling assembly (60) made up of four covers (62, 64, 66, 68). Each cover extends in arcuate shape around part of the longitudinal axis of the nacelle, in symmetrical manner about a vertical plane (P) containing the axis. On either side of said plane, the cowling assembly comprises a top cover (62, 66) hinged at its top portion and a bottom cover (64, 68) hinged at its bottom portion. Access to the internal space (e) of the nacelle is obtained by moving the covers away from the longitudinal axis by pivoting them about their hinge axes. A top cover is less heavy for handling purposes than is a single cover of the prior art.Type: GrantFiled: May 12, 2014Date of Patent: March 28, 2017Assignee: Airbus Operations (S.A.S.)Inventors: Christian Fabre, Alain Bignolais
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Patent number: 9587516Abstract: A locking system comprising a handle mounted such that it can rotate about an operating spindle, wherein the handle can move between a locked position and an unlocked position, a hook mounted on the handle and secured in rotation therewith, wherein the hook has a throat in which a latching point of a structure is designed to engage when the handle is in the locked position. The locking system comprises a key associated with the hook and by means of which it is possible to pass from the locked position to the unlocked position of the handle, wherein the key can be removed when the handle is in the locked position and cannot be removed when the handle is in the unlocked position.Type: GrantFiled: December 18, 2014Date of Patent: March 7, 2017Assignee: Airbus Operations (SAS)Inventors: Christian Fabre, Alain Bignolais
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Publication number: 20160208843Abstract: A method and equipment for installing a tapped insert in a cylindrical bore, the equipment including a tool body comprising a threaded end portion, the threaded end portion being adapted to a threaded inner wall portion of a cylindrical body of the tapped insert; a screw of diameter lower than a diameter of an inner bore of the tool body, the comprising at one end a thread complementary to the inner tapped aperture of the core of the tapped insert; and a positioning ring installed to slide on the tool body, the tool body and the positioning ring comprising complementary sliding means adapted to enable relative sliding of the positioning ring on the tool body in a longitudinal direction and to maintain the positioning ring on the tool body in a defined longitudinal transverse section.Type: ApplicationFiled: March 30, 2016Publication date: July 21, 2016Applicant: AIRBUS OPERATIONS (S.A.S.)Inventors: Christian FABRE, Alain BIGNOLAIS
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Patent number: 9353559Abstract: A latching system for selectively securing together two components, such as the fan cowl doors of a nacelle of an aircraft, closed. The latching system generally includes an anchor and a latch. The latch has a handle movable from an open and a closed position. The handle is precluded from reaching the closed position unless the anchor and latch are secured. Also, the positioning of a keeper portion of the anchor may be adjustable.Type: GrantFiled: April 22, 2014Date of Patent: May 31, 2016Assignee: Airbus Operations (SAS)Inventors: Christian Fabre, Alain Bignolais
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Patent number: 9334895Abstract: The present invention relates to a tapped insert for cylindrical plain bore (30) of a part A1 comprising a cylindrical body (10), characterized in that said cylindrical body (10) comprises an inner bore (11) of frusto-conical shape, and at least one longitudinal slot (12, 12?) extending into the cylindrical body (10) and communicating with said frusto-conical inner bore (11) and characterized in that the tapped insert also comprises a core (20) of frusto-conical shape complementary with said frusto-conical inner bore (11) of the cylindrical body (10), said core (20) comprising a inner tapped aperture (21), said cylindrical body (10) and said core (20) being such that said tapped insert can be holded in position and locked in said cylindrical bore (30) to equip said cylindrical bore with an inner taping.Type: GrantFiled: July 6, 2010Date of Patent: May 10, 2016Assignee: AIRBUS OPERATIONS S.A.S.Inventors: Christian Fabre, Alain Bignolais
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Publication number: 20160101906Abstract: A stopper for a tank having an opening includes a body which is provided to be fixed in the opening and which has a hole, a membrane which is fixed to the body and of which a portion completely blocks the hole, a core which is fixed to the portion of the membrane which blocks the hole, and stop means which are provided to permit a movement of the core between a blocking position which corresponds to the non-broken membrane which blocks the hole, and an open position which corresponds to the broken membrane which is spaced apart from the hole, and to keep the core fixedly joined to the body in an open position. The knowledge of the characteristics of the membrane enables the force from which the stopper opens to be known.Type: ApplicationFiled: September 30, 2015Publication date: April 14, 2016Applicant: AIRBUS OPERATIONS S.A.S.Inventors: Christian Fabre, Alain Bignolais
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Publication number: 20150300061Abstract: A latching system for selectively securing together two components, such as the fan cowl doors of a nacelle of an aircraft, closed. The latching system generally includes an anchor and a latch. The latch has a handle movable from an open and a closed position. The handle is precluded from reaching the closed position unless the anchor and latch are secured. Also, the positioning of a keeper portion of the anchor may be adjustable.Type: ApplicationFiled: April 22, 2014Publication date: October 22, 2015Inventors: Christian Fabre, Alain Bignolais
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Publication number: 20150184544Abstract: A locking system comprising a handle mounted such that it can rotate about an operating spindle, wherein the handle can move between a locked position and an unlocked position, a hook mounted on the handle and secured in rotation therewith, wherein the hook has a throat in which a latching point of a structure is designed to engage when the handle is in the locked position. The locking system comprises a key associated with the hook and by means of which it is possible to pass from the locked position to the unlocked position of the handle, wherein the key can be removed when the handle is in the locked position and cannot be removed when the handle is in the unlocked position.Type: ApplicationFiled: December 18, 2014Publication date: July 2, 2015Inventors: Christian Fabre, Alain Bignolais
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Publication number: 20150184543Abstract: A locking system comprising a handle mounted such that it can rotate about an operating spindle, wherein the handle can move between a locked position and an unlocked position, a hook mounted on the handle and secured in rotation therewith, wherein the hook has a throat in which a latching point of a structure is designed to engage when the handle is in the locked position. The locking system comprises a key associated with the hook and by means of which it is possible to pass from the locked position to the unlocked position of the handle, wherein the key can be removed when the handle is in the locked position and cannot be removed when the handle is in the unlocked position.Type: ApplicationFiled: December 18, 2014Publication date: July 2, 2015Inventors: Christian Fabre, Alain Bignolais
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Patent number: 8991511Abstract: A fluid ejection device for example used as a fire extinguisher in which ejected fluid is an extinguishing agent in liquid or powdery form. The device includes: a cylinder shaped tank, split hermetically, perpendicular to its axis, into two chambers by a piston, slidable axially inside the tank; a first chamber, including a non-gaseous fluid, which communicates with an ejection port closed by a cap, which can open for a pressure greater than or equal to a defined pressure in the first chamber; a second pressurization chamber to be connected to a mechanism increasing pressure in the chamber; and a mechanism to link the piston to the tank in full fixity at a storage position, which mechanism can break and release the piston for axial translation at a pressure higher than or equal to a given pressure in the pressurization chamber, to cause the fluid to be ejected.Type: GrantFiled: December 3, 2010Date of Patent: March 31, 2015Assignee: Airbus Operations S.A.SInventors: Christian Fabre, Alain Bignolais
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Publication number: 20140334922Abstract: The invention relates to an aircraft turbojet nacelle including a cowling assembly (60) made up of four covers (62, 64, 66, 68). Each cover extends in arcuate shape around part of the longitudinal axis of the nacelle, in symmetrical manner about a vertical plane (P) containing the axis. On either side of said plane, the cowling assembly comprises a top cover (62, 66) hinged at its top portion and a bottom cover (64, 68) hinged at its bottom portion. Access to the internal space (e) of the nacelle is obtained by moving the covers away from the longitudinal axis by pivoting them about their hinge axes. A top cover is less heavy for handling purposes than is a single cover of the prior art.Type: ApplicationFiled: May 12, 2014Publication date: November 13, 2014Applicant: AIRBUS OPERATIONS (SAS)Inventors: Christian FABRE, Alain BIGNOLAIS
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Patent number: 8826799Abstract: The invention belongs to the field of single-effect hydraulic cylinders. It relates to a device that makes it possible to limit the pressure in the pressurization chamber of a single-effect cylinder when the rod thereof is in a particular range of longitudinal positions of safety, while respecting the operating safety of the device, that is, in the case that the power supply of the pilot valves of the distributors and of the hydraulic pump is cut, the rod of the cylinder remains in its position if this position does not lie within the safety position range.Type: GrantFiled: March 29, 2011Date of Patent: September 9, 2014Assignee: Airbus Operations S.A.S.Inventors: Marc Anscieau, Alain Bignolais
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Publication number: 20140231660Abstract: A device for measuring, on an aircraft, the extinguishing agent concentration of a gaseous mixture. The device includes an ultraviolet radiation detector for generating an output signal that is a function of the concentration of the agent in the gaseous mixture and an electronic circuit for determining the concentration as a function of said output signal. The device includes a unit for sampling the gaseous mixture in at least one fire zone of said aircraft, and a measurement chamber passed through by the gaseous mixture and comprising a tranquilizing chamber, the detector being arranged in such a way as to measure the concentration of the agent in the gaseous mixture passing through the tranquilizing chamber.Type: ApplicationFiled: January 21, 2014Publication date: August 21, 2014Inventors: Christian Fabre, Alain Bignolais
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Patent number: 8783372Abstract: A compact device for ejecting a fluid including two chambers separated by a separating element of piston type. One of the chambers contains the fluid intended to be ejected, the other chamber is a pressurization chamber, the pressurization of which can cause translational movement of the separating element and ejection of the fluid. The pressurization chamber includes a thimble capable of sealably separating the inside of the pressurization chamber from the side walls of the reservoir. Thus, a seal between two chambers is perfect and durable without degrading slidability of the piston.Type: GrantFiled: October 29, 2008Date of Patent: July 22, 2014Assignee: Airbus Operations S.A.S.Inventors: Christian Fabre, Alain Bignolais
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Patent number: 8727263Abstract: A device for aiding the localization of an aircraft wreck submerged in a sea is arranged inside the aircraft. The device includes at least one beacon that is able to emit remotely detectable signals. Upon immersion of the aircraft in water, an ejection device automatically ejects the beacon out of the aircraft. The ejection device includes a piston system that generates an opening in the aircraft and expels the beacon accordingly. Also after immersion of the aircraft in water, a trigger device automatically triggers the emission of signals from the beacon.Type: GrantFiled: December 5, 2011Date of Patent: May 20, 2014Assignee: Airbus Operations (SAS)Inventors: Christian Fabre, Alain Bignolais