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).
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Patent number: 11739771Abstract: 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: GrantFiled: April 18, 2022Date of Patent: August 29, 2023Assignees: AIRBUS HELICOPTERS DEUTSCHLAND GMBH, AIRBUS HELICOPTERSInventors: Gregor Paulmann, Genevieve Mkadara
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Publication number: 20220389943Abstract: 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: ApplicationFiled: April 18, 2022Publication date: December 8, 2022Applicants: AIRBUS HELICOPTERS DEUTSCHLAND GmbH, AIRBUS HELICOPTERSInventors: Gregor PAULMANN, Genevieve MKADARA
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Patent number: 9470248Abstract: 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: GrantFiled: August 20, 2014Date of Patent: October 18, 2016Assignee: Airbus Helicopters Deutschland GmbHInventor: Gregor Paulmann
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Publication number: 20150075149Abstract: 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: ApplicationFiled: August 20, 2014Publication date: March 19, 2015Inventor: Gregor PAULMANN
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Patent number: 8628046Abstract: 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: GrantFiled: May 26, 2011Date of Patent: January 14, 2014Assignee: EurocopterInventors: Boris Grohmann, Gregor Paulmann
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Publication number: 20120032031Abstract: 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: ApplicationFiled: May 26, 2011Publication date: February 9, 2012Applicant: EUROCOPTER DEUTSCHLAND GMBHInventors: Boris Grohmann, Gregor Paulmann
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Patent number: 7698990Abstract: 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: GrantFiled: December 18, 2006Date of Patent: April 20, 2010Assignee: Eurocopter Deutschland GmbHInventor: Gregor Paulmann
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Publication number: 20070144342Abstract: 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: ApplicationFiled: December 18, 2006Publication date: June 28, 2007Applicant: Eurocopter Deutschland GmbHInventor: Gregor Paulmann