Patents by Inventor Tanno Zantz

Tanno Zantz 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).

  • Publication number: 20250027518
    Abstract: A hydraulic actuator comprising a housing, a piston, first to third pressure chambers, and a plurality of arrangements of piezoelectric elements arranged inside one of the plurality of chambers. A computer implemented internal brake for selectively switching between a braking mode and a non-braking mode of the piston comprises the third chamber, and fluid connections between the first to third chambers with flow control elements.
    Type: Application
    Filed: July 2, 2024
    Publication date: January 23, 2025
    Inventor: Tanno ZANTZ
  • Publication number: 20190368519
    Abstract: A hydraulic actuator including a cylinder housing surrounding a cylinder cavity. A piston is in the cylinder cavity and separates the cylinder cavity into a first and a second pressure chamber. A connection between the first and the second pressure chamber for a hydraulic fluid is provided. A piston rod extends from the piston along an actuation direction. A locking device can be selectively switched between a locking mode and a non-locking mode, wherein in the locking mode the locking device prevents movement of the piston and in the non-locking mode does not prevent movement of the piston. A first arrangement of piezoelectric elements is inside the first pressure chamber which first arrangement of piezoelectric elements is adapted to selectively contract or expand to change the volume of the first pressure chamber occupied by the piezoelectric elements of the first arrangement of piezoelectric elements.
    Type: Application
    Filed: May 20, 2019
    Publication date: December 5, 2019
    Inventor: Tanno Zantz
  • Patent number: 9868511
    Abstract: A high lift system for an aircraft comprises a wing structure and a leading edge slat movably supported relative to a leading edge of the wing structure, the leading edge slat comprises a leading edge and a trailing edge, wherein the trailing edge is configured to take different positions to form a gap between the leading edge slat and the wing structure, a skin and enclosing an interior space of the leading edge slat, the skin having a flexible leading skin section facing away from the wing structure, a flexible trailing skin section facing towards the wing structure, at least one actuation arrangement arranged inside the interior space for selectively introducing a normal force onto at least one of the leading skin section and the trailing skin section.
    Type: Grant
    Filed: January 29, 2015
    Date of Patent: January 16, 2018
    Assignee: Airbus Operations GmbH
    Inventors: Frieder Henning, Tanno Zantz, Michael Brady
  • Patent number: 9701396
    Abstract: A joint arrangement includes an outer joint component, an inner joint component, a cage and at least two balls located between the outer and inner joint component and in openings of the cage. The balls run in ball recesses, while at least two are in a mechanical contact with pressing devices, which are adapted for holding the respective balls in a radially flexible position relative to one of the inner joint component, the outer joint component and the cage and for pressing the respective balls into the corresponding recesses.
    Type: Grant
    Filed: May 30, 2014
    Date of Patent: July 11, 2017
    Assignee: Airbus Operations GmbH
    Inventor: Tanno Zantz
  • Patent number: 9434469
    Abstract: A drive system for driving control surfaces of an aircraft includes at least one drive unit, at least one main shaft connectable to the at least one drive unit and at least two adjusting units for each control surface to be driven. Each adjusting unit includes a differential, two rotary actuators and an adjustment lever. The differential has at least one input means and two output means and is adapted to transfer torque from the at least one input means to the two output means. The input means is connectable to the main shaft, the two rotary actuators each have a rotation input means and a motion output means. The rotation input means is connectable to one of the output means of the differential each and the adjustment lever is connected to the motion output means of both rotary actuators.
    Type: Grant
    Filed: August 8, 2013
    Date of Patent: September 6, 2016
    Assignees: Airbus Operations GmbH, Technische Universitaet Hamburg-Harburg
    Inventors: Tanno Zantz, David Arriola, Stefan Benischke, Frank Thielecke
  • Publication number: 20160039516
    Abstract: A joint arrangement includes an outer joint component, an inner joint component, a cage and at least two balls located between the outer and inner joint component and in openings of the cage. The balls run in ball recesses, while at least two are in a mechanical contact with pressing devices, which are adapted for holding the respective balls in a radially flexible position relative to one of the inner joint component, the outer joint component and the cage and for pressing the respective balls into the corresponding recesses. Such a joint arrangement is based on a homokinetic joint and allows a homogenous transfer of torque without alternating acceleration and deceleration due to the action of the joint itself. Furthermore, a reliable and effective torque limitation may be accomplished.
    Type: Application
    Filed: May 30, 2014
    Publication date: February 11, 2016
    Applicant: AIRBUS OPERATIONS GMBH
    Inventor: Tanno Zantz
  • Publication number: 20150210379
    Abstract: A high lift system for an aircraft comprises a wing structure and a leading edge slat movably supported relative to a leading edge of the wing structure, the leading edge slat comprises a leading edge and a trailing edge, wherein the trailing edge is configured to take different positions to form a gap between the leading edge slat and the wing structure, a skin and enclosing an interior space of the leading edge slat, the skin having a flexible leading skin section facing away from the wing structure, a flexible trailing skin section facing towards the wing structure, at least one actuation arrangement arranged inside the interior space for selectively introducing a normal force onto at least one of the leading skin section and the trailing skin section.
    Type: Application
    Filed: January 29, 2015
    Publication date: July 30, 2015
    Inventors: Frieder HENNING, Tanno Zantz, Michael Brady
  • Publication number: 20140042269
    Abstract: A drive system for driving control surfaces of an aircraft includes at least one drive unit, at least one main shaft connectable to the at least one drive unit and at least two adjusting units for each control surface to be driven. Each adjusting unit includes a differential, two rotary actuators and an adjustment lever. The differential has at least one input means and two output means and is adapted to transfer torque from the at least one input means to the two output means. The input means is connectable to the main shaft, the two rotary actuators each have a rotation input means and a motion output means. The rotation input means is connectable to one of the output means of the differential each and the adjustment lever is connected to the motion output means of both rotary actuators.
    Type: Application
    Filed: August 8, 2013
    Publication date: February 13, 2014
    Applicants: TECHNISCHE UNIVERSITAET HAMBURG-HARBURG, AIRBUS OPERATIONS GMBH
    Inventors: Tanno Zantz, David Arriola, Stefan Benischke, Frank Thielecke