Patents by Inventor Gregor Paulmann

Gregor Paulmann 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: 11739771
    Abstract: A failure detection apparatus for a hydraulic system, to a hydraulic, failure detection-capable system, and to a method of operating a failure detection apparatus. The failure detection apparatus comprises a monitoring and failure detection unit that receives first and second pressure values from first and second pressure sensors and comprises a failure detection unit that detects a failure of at least one hydraulically operated device when a 2-tuple of a plurality of 2-tuples is within a first and outside a second predetermined tolerance range of relative pressure values, and wherein the failure detection unit 260 detects a failure of the pump when a 2-tuple of the plurality of 2-tuples is outside the first predetermined tolerance range of relative pressure values.
    Type: Grant
    Filed: April 18, 2022
    Date of Patent: August 29, 2023
    Assignees: AIRBUS HELICOPTERS DEUTSCHLAND GMBH, AIRBUS HELICOPTERS
    Inventors: Gregor Paulmann, Genevieve Mkadara
  • Publication number: 20220389943
    Abstract: A failure detection apparatus for a hydraulic system, to a hydraulic, failure detection-capable system, and to a method of operating a failure detection apparatus. The failure detection apparatus comprises a monitoring and failure detection unit that receives first and second pressure values from first and second pressure sensors and comprises a failure detection unit that detects a failure of at least one hydraulically operated device when a 2-tuple of a plurality of 2-tuples is within a first and outside a second predetermined tolerance range of relative pressure values, and wherein the failure detection unit 260 detects a failure of the pump when a 2-tuple of the plurality of 2-tuples is outside the first predetermined tolerance range of relative pressure values.
    Type: Application
    Filed: April 18, 2022
    Publication date: December 8, 2022
    Applicants: AIRBUS HELICOPTERS DEUTSCHLAND GmbH, AIRBUS HELICOPTERS
    Inventors: Gregor PAULMANN, Genevieve MKADARA
  • Patent number: 9470248
    Abstract: A flexible response secured mechanical balancing device (D) for multiple hydraulic control actuators (1-2) with a common output member (5a-b). The balancing device (D) provides flexible/continuous fluid-pressure force fight compensation. Balance valves (17-20) are commanded to balance fluid-pressure from a first fluid-pressure network (52a) of a second actuator (2). Each fluid-pressure commanded balance valve (17-20) is arranged to allow relief of differential pressure, directly into a dedicated first (52a) or second fluid-pressure network (52b). A fluid-pressure controlled locking device (21-22) is allowing inhibiting the corresponding pairs of balance valves (17-20) e.g. in case of loss of fluid-pressure. The invention typically applies to vehicles (A) including: aircrafts, rotorcrafts, drones.
    Type: Grant
    Filed: August 20, 2014
    Date of Patent: October 18, 2016
    Assignee: Airbus Helicopters Deutschland GmbH
    Inventor: Gregor Paulmann
  • Publication number: 20150075149
    Abstract: A flexible response secured mechanical balancing device (D) for multiple hydraulic control actuators (1-2) with a common output member (5a-b). The balancing device (D) provides flexible/continuous fluid-pressure force fight compensation. Balance valves (17-20) are commanded to balance fluid-pressure from a first fluid-pressure network (52a) of a second actuator (2). Each fluid-pressure commanded balance valve (17-20) is arranged to allow relief of differential pressure, directly into a dedicated first (52a) or second fluid-pressure network (52b). A fluid-pressure controlled locking device (21-22) is allowing inhibiting the corresponding pairs of balance valves (17-20) e.g. in case of loss of fluid-pressure. The invention typically applies to vehicles (A) including: aircrafts, rotorcrafts, drones.
    Type: Application
    Filed: August 20, 2014
    Publication date: March 19, 2015
    Inventor: Gregor PAULMANN
  • Patent number: 8628046
    Abstract: The invention relates to a control system and to a method of operating such a control system, particularly to a control system for pilot command inputs for a helicopter, with a mechanical input signal (2), at least one electric position sensor (21, 21?) for said input signal (2), at least one electric power supply (25, 25?) and at least one controllable, electromechanical actuator (27, 27?) fed by the at least one electric power supply (25, 25?) and controlled by the at least one electric position sensor (21, 21?). The mechanical input signal (2) is applied mechanically to the at least one controllable electromechanical actuator (27, 27?).
    Type: Grant
    Filed: May 26, 2011
    Date of Patent: January 14, 2014
    Assignee: Eurocopter
    Inventors: Boris Grohmann, Gregor Paulmann
  • Publication number: 20120032031
    Abstract: The invention relates to a control system and to a method of operating such a control system, particularly to a control system for pilot command inputs for a helicopter, with a mechanical input signal (2), at least one electric position sensor (21, 21?) for said input signal (2), at least one electric power supply (25, 25?) and at least one controllable, electromechanical actuator (27, 27?) fed by the at least one electric power supply (25, 25?) and controlled by the at least one electric position sensor (21, 21?). The mechanical input signal (2) is applied mechanically to the at least one controllable electromechanical actuator (27, 27?).
    Type: Application
    Filed: May 26, 2011
    Publication date: February 9, 2012
    Applicant: EUROCOPTER DEUTSCHLAND GMBH
    Inventors: Boris Grohmann, Gregor Paulmann
  • Patent number: 7698990
    Abstract: A hydraulic linear actuating drive includes a cylinder, a movable servo piston that can be pressure-loaded and that runs inside the cylinder, at least one piston rod attached to the servo piston, and at least one piston gasket having at least two sealing elements at a distance from each other. An intermediate sealing space is defined between the at least two sealing elements, an inner wall of the cylinder and an outer edge of the servo piston. The hydraulic linear actuating drive has at least one leakage channel that can move together with the servo piston. A first end of the channel opens into the intermediate sealing space and into a leakage fluid inlet opening located there, while the other, second end of the channel opens into a leakage fluid outlet opening arranged outside of the cylinder.
    Type: Grant
    Filed: December 18, 2006
    Date of Patent: April 20, 2010
    Assignee: Eurocopter Deutschland GmbH
    Inventor: Gregor Paulmann
  • Publication number: 20070144342
    Abstract: A hydraulic linear actuating drive includes a cylinder, a movable servo piston that can be pressure-loaded and that runs inside the cylinder, at least one piston rod attached to the servo piston, and at least one piston gasket having at least two sealing elements at a distance from each other. An intermediate sealing space is defined between the at least two sealing elements, an inner wall of the cylinder and an outer edge of the servo piston. The hydraulic linear actuating drive has at least one leakage channel that can move together with the servo piston. A first end of the channel opens into the intermediate sealing space and into a leakage fluid inlet opening located there, while the other, second end of the channel opens into a leakage fluid outlet opening arranged outside of the cylinder.
    Type: Application
    Filed: December 18, 2006
    Publication date: June 28, 2007
    Applicant: Eurocopter Deutschland GmbH
    Inventor: Gregor Paulmann