Patents by Inventor Andreas Wildschek

Andreas Wildschek 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: 10364018
    Abstract: A coupling device for supporting a first wing section against a second wing section of an aircraft, and configured for passive flight load alleviation includes a housing including a chamber including a first portion and a second portion and filled with a fluid, a piston device movably arranged in the chamber and separating the first portion from the second portion in a fluid tight manner, a first fluid pathway connecting the first portion to the second portion, a first pressure relief valve arranged in the first fluid pathway and blocking the first fluid pathway, if the pressure in the second portion is smaller than a first relief pressure and opening the first fluid pathway, if the pressure in the second portion is greater than the first relief pressure. In addition, the coupling device can be used to actuate the second wing section against the first wing section.
    Type: Grant
    Filed: July 19, 2016
    Date of Patent: July 30, 2019
    Assignees: Airbus Defence and Space GmbH, AIRBUS OPERATIONS LIMITED
    Inventors: Andreas Wildschek, Stefan Storm, Stephen Rolston, Martin Herring
  • Publication number: 20170021911
    Abstract: A coupling device for supporting a first wing section against a second wing section of an aircraft, and configured for passive flight load alleviation includes a housing including a chamber including a first portion and a second portion and filled with a fluid, a piston device movably arranged in the chamber and separating the first portion from the second portion in a fluid tight manner, a first fluid pathway connecting the first portion to the second portion, a first pressure relief valve arranged in the first fluid pathway and blocking the first fluid pathway, if the pressure in the second portion is smaller than a first relief pressure and opening the first fluid pathway, if the pressure in the second portion is greater than the first relief pressure. In addition, the coupling device can be used to actuate the second wing section against the first wing section.
    Type: Application
    Filed: July 19, 2016
    Publication date: January 26, 2017
    Applicants: Airbus Defence and Space GmbH, Airbus Group Limited
    Inventors: Andreas Wildschek, Stefan Storm, Stephen Rolston, Martin Herring
  • Patent number: 9446837
    Abstract: A method for dynamically alleviating loads generated on an aircraft by a disturbance of gust involves automatically detecting a disturbance due to gust on a flight of the aircraft. When a disturbance due to gust is detected, control commands for control surfaces are automatically generated and the control commands are applied to actuate the control surfaces. The method also involves dynamically actuating the control surfaces in a prescribed dynamic way in order to minimize not only a first load peak but also at least a second load peak.
    Type: Grant
    Filed: July 20, 2012
    Date of Patent: September 20, 2016
    Assignee: EADS Deutschland GmbH
    Inventors: Andreas Wildschek, Tomas Hanis
  • Patent number: 9327823
    Abstract: A device for reducing structural vibrations of airfoils in an aircraft comprises, in the region of the airfoil tips, at least one force generator acting substantially in the direction of movement of the vibrations. This arrangement has the advantage that such a force generator is considerably less susceptible to wear than conventional aerodynamic flaps and therefore effective vibration damping is possible with a reduced outlay on maintenance and greater efficiency.
    Type: Grant
    Filed: May 25, 2012
    Date of Patent: May 3, 2016
    Assignee: Airbus Defence and Space GmbH
    Inventors: Stefan Storm, Rudolf Maier, Andreas Wildschek
  • Publication number: 20160068258
    Abstract: An aircraft with C-shaped carrier surfaces wherein an axis of rotation of top surfaces is arranged in the respective aerodynamic center of the top surfaces, furthermore that each top surface can be adjusted by an adjustment device that can be controlled by a control device, wherein an angle of attack of the top surfaces can be adjusted that is optimal for a minimal induced resistance based on flight state parameters. This arrangement minimizes the adjusting moment during the adjusting of the top surfaces and is independent of the angle of attack of the top surface.
    Type: Application
    Filed: September 4, 2015
    Publication date: March 10, 2016
    Inventors: Klaus Seywald, Andreas Wildschek
  • Patent number: 9242723
    Abstract: A method of dynamically alleviating loads generated on an aircraft by a disturbance of gust and/or turbulence. The method comprises monitoring, during flight of the aircraft, to automatically detect a disturbance due to gust and/or turbulence and determining an incidence angle or angle of attack of the disturbance. When a disturbance due to gust and/or turbulence is detected, automatically generating control commands for deflecting control surfaces dependent on the incidence angle or angle of attack, and applying the control commands to deflect the control surfaces.
    Type: Grant
    Filed: May 24, 2012
    Date of Patent: January 26, 2016
    Assignee: EADS DEUTSCHLAND GmbH
    Inventor: Andreas Wildschek
  • Publication number: 20150028162
    Abstract: A method of dynamically alleviating loads generated on an aircraft by a disturbance of gust and/or turbulence. The method comprises monitoring, during flight of the aircraft, to automatically detect a disturbance due to gust and/or turbulence and determining an incidence angle or angle of attack of the disturbance. When a disturbance due to gust and/or turbulence is detected, automatically generating control commands for deflecting control surfaces dependent on the incidence angle or angle of attack, and applying the control commands to deflect the control surfaces.
    Type: Application
    Filed: May 24, 2012
    Publication date: January 29, 2015
    Applicant: EADS DEUTSCHLAND GMBH
    Inventor: Andreas Wildschek
  • Publication number: 20150021443
    Abstract: A method for dynamically alleviating loads generated on an aircraft by a disturbance of gust involves automatically detecting a disturbance due to gust on a flight of the aircraft. When a disturbance due to gust is detected, control commands for control surfaces are automatically generated and the control commands are applied to actuate the control surfaces. The method also involves dynamically actuating the control surfaces in a prescribed dynamic way in order to minimize not only a first load peak but also at least a second load peak.
    Type: Application
    Filed: July 28, 2011
    Publication date: January 22, 2015
    Applicant: EADS Deutschland GmbH
    Inventors: Andreas Wildschek, Tomas Hanis
  • Publication number: 20140341737
    Abstract: A device for reducing structural vibrations of aerofoils in an aircraft comprises, in the region of the aerfoil tips, at least one force generator (24a) acting substantially in the direction of movement of the vibrations. This arrangement has the advantage that such a force generator (24a) is considerably less susceptible to wear than conventional aerodynamic flaps and therefore effective vibration damping is possible with a reduced outlay on maintenance and greater efficiency.
    Type: Application
    Filed: May 25, 2012
    Publication date: November 20, 2014
    Applicant: EADS DEUTSCHLAND GMBH
    Inventors: Stefan Storm, Rudolf Maier, Andreas Wildschek
  • Patent number: 8255096
    Abstract: Minimizing dynamic structural loads of an aircraft, introduced by an external excitation, which, includes generating a signal (x) indicative of the external excitation; deriving signals (y) of pre-controlling for actuating control elements of the aircraft from the excitation indicating signal (x) in accordance with a pre-controlling rule, so as to reduce the dynamic structural loads introduced to the aircraft; generating an error signal (e, e*) representing performance of said pre-controlling; optimizing the pre-controlling rule by the error signal (e, e*) and/or the excitation indicating signal (x) so as to minimize the dynamic structural loads.
    Type: Grant
    Filed: January 19, 2007
    Date of Patent: August 28, 2012
    Assignee: Airbus Operations SAS
    Inventors: Andreas Wildschek, Rudolf Maier, Falk Hoffmann, Matthieu Jeanneau, Nicky Aversa
  • Publication number: 20090084908
    Abstract: Minimizing dynamic structural loads of an aircraft (2), introduced by an external excitation (1), which, comprises generating a signal (x) indicative of the external excitation (1); deriving signals (y) of pre-controlling for actuating control elements of the aircraft (2) from said excitation indicating signal (x) in accordance with a pre-controlling rule, so as to reduce the dynamic structural loads introduced to the aircraft (2); generating an error signal (e, e*) representing performance of said pre-controlling; optimizing the pre-controlling rule by said error signal (e, e*) and/or said excitation indicating signal (x) so as to minimize the dynamic structural loads.
    Type: Application
    Filed: January 19, 2007
    Publication date: April 2, 2009
    Applicant: Airbus France
    Inventors: Andreas Wildschek, Rudolf Maier, Falk Hoffmann, Matthieu Jeanneau, Nicky Aversa