Patents by Inventor Christian REICHENSPERGER
Christian REICHENSPERGER 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: 11827332Abstract: A vehicle with a vehicle frame and a windshield assembly that is mounted to the vehicle frame and closes an associated opening provided in the vehicle frame. The windshield assembly comprises at least one flexible element and at least one windshield. The at least one flexible element connects the at least one windshield to the vehicle frame for at least partially absorbing loads resulting from an impact on the at least one windshield. The at least one flexible element connects the at least one windshield to the vehicle frame such that the at least one windshield pivots relative to the vehicle frame by means of the at least one flexible element upon occurrence of an impact on the at least one windshield such that the at least one flexible element defines a hinge element.Type: GrantFiled: October 7, 2019Date of Patent: November 28, 2023Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBHInventors: Christian Reichensperger, Mikko Schnizer, Lars Wolters
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Publication number: 20230348048Abstract: The disclosure is related to a rotary wing aircraft with a fuselage and an at least partially non-retractable landing gear, wherein the at least partially non-retractable landing gear comprises at least three individual support legs, wherein at least one individual support leg of the at least three individual support legs is mounted pivotally to the fuselage by means of an associated pivot bearing arrangement, wherein the at least one individual support leg is further connected to the fuselage via at least one torsion element with a predetermined elastic range, and wherein the at least one torsion element is adapted to act, in the predetermined elastic range, as a torsional spring, and, outside of the predetermined elastic range, as an energy absorber.Type: ApplicationFiled: April 14, 2023Publication date: November 2, 2023Applicant: AIRBUS URBAN MOBILITY GMBHInventors: Christian REICHENSPERGER, Martin BLACHA, Justus STEGER
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Patent number: 11554862Abstract: A vertical take-off and landing multirotor aircraft with an airframe and at least eight thrust producing units, each one of the at least eight thrust producing units being provided for producing thrust in an associated predetermined thrust direction, wherein at least four thrust producing units of the at least eight trust producing units form a first thrust producing units sub-assembly, and at least four other thrust producing units of the at least eight thrust producing units form a second thrust producing units sub-assembly, the first thrust producing units sub-assembly being operable independent of the second thrust producing units sub-assembly.Type: GrantFiled: October 17, 2019Date of Patent: January 17, 2023Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBHInventors: Uwe Kiesewetter, Christian Reichensperger, Lukasz Paluszek, Klaus Kicker
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Patent number: 11465733Abstract: A multirotor aircraft with an airframe that extends in a longitudinal direction, and with at least one thrust producing unit for producing thrust in a predetermined thrust direction, wherein the at least one thrust producing unit comprises a shrouding that is associated with at least one rotor assembly comprising at least one electrical engine, wherein the shrouding defines a cylindrical air duct that is axially delimited by an air inlet region and an air outlet region, wherein a cantilever is mounted at a leading edge region of the cylindrical air duct to the shrouding such that the cantilever is arranged inside of the cylindrical air duct and oriented at least essentially in parallel to the longitudinal direction, wherein the shrouding comprises a forward beam which connects the cantilever to the airframe, the forward beam being arranged outside of the cylindrical air duct and comprising a forward flange that is rigidly attached to the airframe, wherein the at least one electrical engine is mounted to the cType: GrantFiled: December 7, 2020Date of Patent: October 11, 2022Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBHInventors: Christian Reichensperger, Uwe Kiesewetter, Petr Schejbal, Lukasz Paluszek, Klaus Kicker, Martin Blacha
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Publication number: 20220268320Abstract: An overload coupling for coupling a driving device to a driven device. The present embodiments also relate to a rotating drive system with such an overload coupling, to a rotor system with such a rotating drive system, and to a rotary-wing aircraft with such a rotor system. The overload coupling may include concentrically arranged inner connecting element coupled to the driving device and outer connecting element coupled to the driven device. At least a first and a second arm, that each include an arrangement of at least one plate may connect the inner connecting element with the outer connecting element.Type: ApplicationFiled: January 12, 2022Publication date: August 25, 2022Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBHInventors: Martin BLACHA, Christian REICHENSPERGER
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Publication number: 20210316841Abstract: A multirotor aircraft with an airframe that extends in a longitudinal direction, and with at least one thrust producing unit for producing thrust in a predetermined thrust direction, wherein the at least one thrust producing unit comprises a shrouding that is associated with at least one rotor assembly comprising at least one electrical engine, wherein the shrouding defines a cylindrical air duct that is axially delimited by an air inlet region and an air outlet region, wherein a cantilever is mounted at a leading edge region of the cylindrical air duct to the shrouding such that the cantilever is arranged inside of the cylindrical air duct and oriented at least essentially in parallel to the longitudinal direction, wherein the shrouding comprises a forward beam which connects the cantilever to the airframe, the forward beam being arranged outside of the cylindrical air duct and comprising a forward flange that is rigidly attached to the airframe, wherein the at least one electrical engine is mounted to the cType: ApplicationFiled: December 7, 2020Publication date: October 14, 2021Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBHInventors: Christian REICHENSPERGER, Uwe KIESEWETTER, Petr SCHEJBAL, Lukasz PALUSZEK, Klaus KICKER, Martin BLACHA
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Patent number: 11117674Abstract: An aircraft with an airframe and at least one thrust producing unit the at least one thrust producing unit being electrically powered by an associated electrical engine that is electrically connected to an electrical energy source via an electrical energy distribution system, wherein the airframe comprises at least one load carrying section and at least one propulsion system carrying section, wherein the at least one load carrying section and the at least one propulsion system carrying section are segregated from each other, wherein the at least one load carrying section is provided for transportation of passengers and/or cargo, and wherein the at least one propulsion system carrying section is provided for carrying at least essentially the electrical energy source and the electrical energy distribution system.Type: GrantFiled: December 5, 2017Date of Patent: September 14, 2021Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBHInventors: Sebastian Mores, Martin Blacha, Christian Reichensperger, Klaus Rittel, Marco Schneeberger, Michael Geiss, Markus Paschek, Marius Bebesel
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Patent number: 10974815Abstract: A multirotor aircraft with an airframe that extends in a longitudinal direction, and with at least one thrust producing unit for producing thrust in a predetermined thrust direction, wherein the at least one thrust producing unit comprises a shrouding that is associated with at least one rotor assembly comprising at least one electrical engine, wherein the shrouding defines a cylindrical air duct that is axially delimited by an air inlet region and an air outlet region, and wherein a carrier beam is at least mounted at a leading edge region of the cylindrical air duct to the shrouding such that the carrier beam is arranged inside of the cylindrical air duct and oriented at least essentially in parallel to the longitudinal direction, the at least one electrical engine being mounted to the carrier beam.Type: GrantFiled: June 12, 2019Date of Patent: April 13, 2021Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBHInventors: Christian Reichensperger, Uwe Kiesewetter, Petr Schejbal, Lukasz Paluszek, Klaus Kicker, Martin Blacha
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Publication number: 20200180748Abstract: A vehicle with a vehicle frame and a windshield assembly that is mounted to the vehicle frame and closes an associated opening provided in the vehicle frame. The windshield assembly comprises at least one flexible element and at least one windshield. The at least one flexible element connects the at least one windshield to the vehicle frame for at least partially absorbing loads resulting from an impact on the at least one windshield. The at least one flexible element connects the at least one windshield to the vehicle frame such that the at least one windshield pivots relative to the vehicle frame by means of the at least one flexible element upon occurrence of an impact on the at least one windshield such that the at least one flexible element defines a hinge element.Type: ApplicationFiled: October 7, 2019Publication date: June 11, 2020Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBHInventors: Christian REICHENSPERGER, Mikko SCHNIZER, Lars WOLTERS
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Publication number: 20200164972Abstract: A vertical take-off and landing multirotor aircraft with an airframe and at least eight thrust producing units, each one of the at least eight thrust producing units being provided for producing thrust in an associated predetermined thrust direction, wherein at least four thrust producing units of the at least eight thrust producing units form a first thrust producing units sub-assembly, and at least four other thrust producing units of the at least eight thrust producing units form a second thrust producing units sub-assembly, the first thrust producing units sub-assembly being operable independent of the second thrust producing units sub-assembly.Type: ApplicationFiled: October 17, 2019Publication date: May 28, 2020Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBHInventors: Uwe KIESEWETTER, Christian REICHENSPERGER, Lukasz PALUSZEK, Klaus KICKER
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Publication number: 20200062377Abstract: A multirotor aircraft with an airframe that extends in a longitudinal direction, and with at least one thrust producing unit for producing thrust in a predetermined thrust direction, wherein the at least one thrust producing unit comprises a shrouding that is associated with at least one rotor assembly comprising at least one electrical engine, wherein the shrouding defines a cylindrical air duct that is axially delimited by an air inlet region and an air outlet region, and wherein a carrier beam is at least mounted at a leading edge region of the cylindrical air duct to the shrouding such that the carrier beam is arranged inside of the cylindrical air duct and oriented at least essentially in parallel to the longitudinal direction, the at least one electrical engine being mounted to the carrier beam.Type: ApplicationFiled: June 12, 2019Publication date: February 27, 2020Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBHInventors: Christian REICHENSPERGER, Uwe KIESEWETTER, Petr SCHEJBAL, Lukasz PALUSZEK, Klaus KICKER, Martin BLACHA
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Patent number: 10399658Abstract: An aircraft structural component that is adapted for absorbing and transmitting forces in an aircraft, the aircraft structural component comprising at least one panel element and at least one reinforcing structure. The at least one reinforcing structure is rigidly attached to the at least one panel element such that at least one cavity is defined between the at least one panel element and the at least one reinforcing structure, the at least one cavity being adapted for distributing forces that are absorbed by the aircraft structural component in operation.Type: GrantFiled: June 8, 2016Date of Patent: September 3, 2019Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBHInventors: Kaspar Von-Wilmowsky, Christian Reichensperger, Andreas Rack
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Publication number: 20180170509Abstract: An aircraft with an airframe and at least one thrust producing unit the at least one thrust producing unit being electrically powered by an associated electrical engine that is electrically connected to an electrical energy source via an electrical energy distribution system, wherein the airframe comprises at least one load carrying section and at least one propulsion system carrying section, wherein the at least one load carrying section and the at least one propulsion system carrying section are segregated from each other, wherein the at least one load carrying section is provided for transportation of passengers and/or cargo, and wherein the at least one propulsion system carrying section is provided for carrying at least essentially the electrical energy source and the electrical energy distribution system.Type: ApplicationFiled: December 5, 2017Publication date: June 21, 2018Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBHInventors: Sebastian MORES, Martin BLACHA, Christian REICHENSPERGER, Klaus RITTEL, Marco SCHNEEBERGER, Michael GEISS, Markus PASCHEK, Marius BEBESEL
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Publication number: 20180170511Abstract: An aircraft with a modular airframe. The modular airframe has a load carrying framework and at least one exchangeable covering item that exhibits a first predetermined shaping. The at least one exchangeable covering item is detachably mounted to the load carrying framework. The modular airframe is customizable by exchanging the at least one exchangeable covering item with a substitute exchangeable covering item that exhibits a second predetermined shaping.Type: ApplicationFiled: December 5, 2017Publication date: June 21, 2018Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBHInventors: Sebastian MORES, Martin BLACHA, Christian REICHENSPERGER, Klaus RITTEL, Marco SCHNEEBERGER, Michael GEISS, Markus PASCHEK, Marius BEBESEL
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Publication number: 20160375979Abstract: An aircraft structural component that is adapted for absorbing and transmitting forces in an aircraft, the aircraft structural component comprising at least one panel element and at least one reinforcing structure. The at least one reinforcing structure is rigidly attached to the at least one panel element such that at least one cavity is defined between the at least one panel element and the at least one reinforcing structure, the at least one cavity being adapted for distributing forces that are absorbed by the aircraft structural component in operation.Type: ApplicationFiled: June 8, 2016Publication date: December 29, 2016Inventors: Kaspar VON-WILMOWSKY, Christian REICHENSPERGER, Andreas RACK