Patents by Inventor Alain Sagansan

Alain Sagansan 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).

  • Device for mechanical connection of a control surface to a fixed structural element of an aircraft and aircraft wing element equipped with said device
    Patent number: 9376203
    Abstract: A device for mechanically connecting a control surface to a fixed structural element of an aircraft, including a rotary actuator for driving an element that is securely connected to the control surface in rotation in relation to an element securely connected to the fixed structural element, around an articulation axis, as well as articulation elements for articulating this control surface around this axis. These articulation elements are able to support the control surface independently of the rotary actuator. This arrangement permits taking benefit from the advantageous properties of rotary actuators while allowing removal of the rotary actuator without having first to remove the control surface.
    Type: Grant
    Filed: June 25, 2013
    Date of Patent: June 28, 2016
    Assignee: AIRBUS OPERATIONS SAS
    Inventors: Pierre Tieys, Alain Sagansan, Laurent Andrieu
  • DEVICE FOR MECHANICAL CONNECTION OF A CONTROL SURFACE TO A FIXED STRUCTURAL ELEMENT OF AN AIRCRAFT AND AIRCRAFT WING ELEMENT EQUIPPED WITH SAID DEVICE
    Publication number: 20140001309
    Abstract: A device for mechanically connecting a control surface to a fixed structural element of an aircraft, including a rotary actuator for driving an element that is securely connected to the control surface in rotation in relation to an element securely connected to the fixed structural element, around an articulation axis, as well as articulation elements for articulating this control surface around this axis. These articulation elements are able to support the control surface independently of the rotary actuator. This arrangement permits taking benefit from the advantageous properties of rotary actuators while allowing removal of the rotary actuator without having first to remove the control surface.
    Type: Application
    Filed: June 25, 2013
    Publication date: January 2, 2014
    Inventors: Pierre Tieys, Alain Sagansan, Laurent Andrieu
  • Fly-by-wire control system for an aircraft comprising detection of pilot induced oscillations and a control for such a system
    Patent number: 8473121
    Abstract: A fly-by-wire control system for an aircraft including detection of pilot induced oscillations and a mobile control unit for such a system. According to the invention, provision is made for the pivotings of the mobile control unit to be damped by a controllable damper controlled by a detector that detects oscillations corresponding to pilot induced oscillations.
    Type: Grant
    Filed: April 22, 2010
    Date of Patent: June 25, 2013
    Assignee: Airbus Operations SAS
    Inventors: Nathalie Raimbault, Jean-Pierre Gautier, Alain Sagansan, Pierre Fabre
  • FLY-BY-WIRE CONTROL SYSTEM FOR AN AIRCRAFT COMPRISING DETECTION OF PILOT INDUCED OSCILLATIONS AND A CONTROL FOR SUCH A SYSTEM
    Publication number: 20100200701
    Abstract: A fly-by-wire control system for an aircraft including detection of pilot induced oscillations and a mobile control unit for such a system, According to the invention, provision is made for the pivotings of the mobile control unit to be damped by a controllable damper controlled by a detector that detects oscillations corresponding to pilot induced oscillations.
    Type: Application
    Filed: April 22, 2010
    Publication date: August 12, 2010
    Applicant: AIRBUS FRANCE
    Inventors: Nathalie RAIMBAULT, Jean-Pierre Gautier, Alain Sagansan, Pierre Fabre
  • Fly-by-wire control system for an aircraft comprising detection of pilot induced oscillations and a control for such a system
    Publication number: 20050021193
    Abstract: Fly-by-wire control system for an aircraft comprising detection of pilot induced oscillations and a control for such a system. According to the invention, provision is made for the pivotings of said control (2) to be damped by controllable damping means (15, 16) controlled by means (7) detecting oscillations corresponding to pilot induced oscillations.
    Type: Application
    Filed: November 10, 2003
    Publication date: January 27, 2005
    Inventors: Nathalie Raimbault, Jean-Pierre Gautier, Alain Sagansan, Pierre Fabre