Patents by Inventor Yohann Coraboeuf

Yohann Coraboeuf 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).

  • Patent number: 9981757
    Abstract: The invention relates to a propulsion unit for a reusable launch vehicle including a rocket engine supported by a cradle. According to the invention, the cradle includes at least three attachment elements for assembling the unit on the structure of the vehicle to which the unit is to be connected, the at least three attachment elements defining a plane for removing the unit, and in which the unit includes one or more fluid and/or electric links of the engine, each one of the links including a free end to be assembled with a corresponding circuit for supplying the vehicle, to which the unit is to be connected, the tip of at least some of the free ends being contained in the removal plane.
    Type: Grant
    Filed: July 4, 2014
    Date of Patent: May 29, 2018
    Assignee: AIRBUS DEFENCE & SPACE SAS
    Inventors: Yohann Coraboeuf, Jean-Philippe Dutheil
  • Patent number: 9938025
    Abstract: A device for mounting and supporting a generally cylindrical or tapered tank, having a main axis X, that includes a pair of first retaining rods for retaining the tank along a vertical axis Z on each of a first and second end of the tank, a second retaining rod for retaining the tank along a horizontal axis Y, perpendicular to the main axis, on the first end of the tank, and a third retaining rod for retaining in a ball-and-socket joint, the means being located around the vertical axis and connected to the second end of the tank.
    Type: Grant
    Filed: February 4, 2014
    Date of Patent: April 10, 2018
    Assignee: AIRBUS DEFENCE & SPACE SAS
    Inventors: Benjamin Faure, Jérôme Bertrand, Yohann Coraboeuf, Samuel Chevrollier, Robert Abadie-La-Haille, Pascal Mezieres, Angélique Santerre
  • Publication number: 20160257435
    Abstract: The invention relates to a propulsion unit for a reusable launch vehicle including a rocket engine supported by a cradle. According to the invention, the cradle includes at least three attachment elements for assembling the unit on the structure of the vehicle to which the unit is to be connected, the at least three attachment elements defining a plane for removing the unit, and in which the unit includes one or more fluid and/or electric links of the engine, each one of the links including a free end to be assembled with a corresponding circuit for supplying the vehicle, to which the unit is to be connected, the tip of at least some of the free ends being contained in the removal plane.
    Type: Application
    Filed: July 4, 2014
    Publication date: September 8, 2016
    Applicant: AIRBUS DEFENCE & SPACE SAS
    Inventors: Yohann CORABOEUF, Jean-Philippe DUTHEIL
  • Publication number: 20160031544
    Abstract: The invention relates to a glass panel for an aircraft suitable for a suborbital flight and an aeronautical flight, including an outer panel made of polycarbonate or aluminosilicate for temperature resistance, a main panel for pressure resistance, sized according to standard aeroplane safety factors, and an inner panel, providing redundancy for the main panel, sized with a minimum pressure margin, the outer, main and internal redundancy panels being separated from one another by spaces. The invention also relates to an aircraft including windscreen elements and portholes made using the glass panel.
    Type: Application
    Filed: April 4, 2014
    Publication date: February 4, 2016
    Inventor: Yohann CORABOEUF
  • Publication number: 20150360792
    Abstract: The present invention relates to a device for mounting and supporting a generally cylindrical or tapered tank, having a main axis X, that includes a pair of first means for retaining the tank along a vertical axis Z on each of a first and second end of the tank, a second means for retaining the tank along a horizontal axis Y, perpendicular to the main axis, on the first end of the tank, and a third means for retaining in a ball-and-socket joint, the means being located around the vertical axis and connected to the second end of the tank.
    Type: Application
    Filed: February 4, 2014
    Publication date: December 17, 2015
    Inventors: Benjamin FAURE, Jérôme BERTRAND, Yohann CORABOEUF, Samuel CHEVROLLIER, Robert ABADIE-LA-HAILLE, Pascal MEZIERES, Angélique SANTERRE
  • Publication number: 20150360791
    Abstract: The invention concerns a tank retainer for retaining a tank in the fuselage of an aircraft which includes, between the tank and a frame rigidly connected to the fuselage of the aircraft, a hinged retaining means and a fastening rod on which said hinged retaining means is mounted. Advantageously, the hinged retaining means is intended to be connected to a rear end of the tank and the fastening rod is suitable for being mounted on the frame rigidly connected to the fuselage of the aircraft and, preferably, the hinged retaining means comprises a ball joint.
    Type: Application
    Filed: February 4, 2014
    Publication date: December 17, 2015
    Inventors: Samuel CHEVROLLIER, Robert ABADIE-LAHAILLE, Pascal MEZIERES, Benjamin FAURE, Jérôme BERTRAND, Yohann CORABOEUF, Angélique SANTERRE
  • Publication number: 20150344158
    Abstract: According to the invention, said space aircraft comprises, at the front of each of the air inlets of the turbo engines, a mobile flap that can move, in both directions, between a first position for which said flap opens said air inlet and a second position for which said flap prevents air from entering said air inlet.
    Type: Application
    Filed: January 17, 2014
    Publication date: December 3, 2015
    Applicant: AIRBUS DEFENCE AND SPACE SAS
    Inventors: Eugénio Ferreira, Marco Prampolini, Yohann Coraboeuf
  • Patent number: 9079661
    Abstract: The invention concerns an ultra-rapid air vehicle together with a method of aerial locomotion by means of an ultra-rapid air vehicle, where the air vehicle is propelled by a system of motors formed of turbojets (TB1, TB2), ramjets (ST1, ST2) and a rocket motor which can be made streamlined to reduce the drag of the base during the cruise phase, and where the vehicle has a gothic delta wing (A) fitted with moving fins (a1, a2) at both outer ends of the trailing edge of the delta wing (A).
    Type: Grant
    Filed: December 20, 2010
    Date of Patent: July 14, 2015
    Assignees: ASTRIUM SAS, EUROPEAN AERONAUTIC DEFENCE AND SPACE COMPANY—EADS FRANCE
    Inventors: Marco Prampolini, Yohann Coraboeuf
  • Publication number: 20120325957
    Abstract: The invention concerns an ultra-rapid air vehicle together with a method of aerial locomotion by means of an ultra-rapid air vehicle, where the air vehicle is propelled by a system of motors formed of turbojets (TB1, TB2), ramjets (ST1, ST2) and a rocket motor which can be made streamlined to reduce the drag of the base during the cruise phase, and where the vehicle has a gothic delta wing (A) fitted with moving fins (a1, a2) at both outer ends of the trailing edge of the delta wing (A).
    Type: Application
    Filed: December 20, 2010
    Publication date: December 27, 2012
    Applicant: ASTRIUM SAS
    Inventors: Marco Prampolini, Yohann Coraboeuf