Patents by Inventor Georg Lonsdorfer
Georg Lonsdorfer 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: 10232573Abstract: A system for repairing a component made out of a plastic comprises a frame, a multiaxial guide device coupled with the frame, with a tool holder arranged thereon, an optical acquisition device, a processing device, and a plastic deposition device. The frame comprises a mounting device for retaining the frame on a component surface. The optical acquisition device, the processing device and the plastic deposition device are arranged on the tool holder. The optical acquisition device is set up to optically inspect a surface area of the component lying in proximity to the frame from at least one viewing angle, so as to acquire the spatial structure of the surface area. The processing device is set up to remove material of a damaged area from the component for generating a base surface with a desired structure and boundary edges.Type: GrantFiled: January 28, 2016Date of Patent: March 19, 2019Assignee: AIRBUS OPERATIONS GMBHInventors: Axel Siegfried Herrmann, Jens Wulfsberg, Georg Lonsdorfer, Marc Fette
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Patent number: 10167583Abstract: A honeycomb structure comprising carbon-fiber non-woven, sandwich structure comprising the honeycomb structure, and process for the production of the honeycomb structure.Type: GrantFiled: September 14, 2015Date of Patent: January 1, 2019Assignee: AIRBUS OPERATIONS GMBHInventors: Tassilo Witte, Georg Lonsdorfer
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Patent number: 9764519Abstract: A device for the production of structural components from a fiber composite material, the components being three-dimensionally arched over a large surface, including a jig having a convex mounting surface having receiving channels for the insertion of structural components, wherein the loaded jig interacts with a laminating bonding device having a corresponding shape for forming the structural component under pressure, wherein the mounting surface includes a plurality of individually elastically deformable mounting shell parts arranged adjacent to each other along at least one longitudinally extending pitch line and attached to a plurality of elastically deformable supporting frame elements extending on the interior of the shell at a right angle to the pitch line, and a plurality of actuators for deforming the mounting surface between an extended position (A) and at least one retracted position (B) to move the jig from the bonding device relative to the receiving channels without undercuts.Type: GrantFiled: September 27, 2012Date of Patent: September 19, 2017Assignee: Airbus Operations GmbHInventors: Georg Lonsdorfer, Adrian Wachendorf, Remo Hinz, Niels Deschauer, Adam Andrä
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Patent number: 9751290Abstract: A device and to a method for the production of essentially two-dimensionally arched large-area structural components from a fiber composite material, including a jig having a convex mounting surface which has longitudinally extending receiving channels for the insertion of construction components and which can be loaded with auxiliary materials, wherein the loaded jig interacts with a laminating bonding device having a corresponding shape for forming the structural component under pressure, wherein the jig includes a mounting shell that at the edge can be elastically deformed inwards, which mounting shell, by way of a plurality of actuators that are articulated to the inside, can be moved between an extended position (A) and at least one retracted position (B) in which the jig can be moved relative to the longitudinally extending receiving channels from the laminating bonding device without undercuts.Type: GrantFiled: March 28, 2011Date of Patent: September 5, 2017Assignee: Airbus Operations GmbHInventors: Georg Lonsdorfer, Remo Hinz, Adrian Wachendorf, Niels Deschauer, Adam Andrä
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Publication number: 20170050394Abstract: A method for manufacturing a component includes a) providing a first, plate-shaped semi-finished product and a second semi-finished product, the first semi-finished product including a first thermosetting reactive resin with non-directionally inserted long-stranded fibers, the second semi-finished product including an oriented network of endless fibers, the endless fibers having a mean length l of at least 80 mm, and the long-stranded fibers having a mean length k which is at least 30 mm shorter than that of the endless fibers; b) placing the second semi-finished product on top of the first semi-finished product so as to form a semi-finished product group; c) inserting the semi-finished group into a first molding part of a multi-part mold of a press, the semi-finished group covering between 70% and 95% of the first molding part after the insertion; d) extrusion forming of the semi-finished product group by the mold resulting in the component; and e) removing the component.Type: ApplicationFiled: August 11, 2016Publication date: February 23, 2017Applicant: Airbus Operations GmbHInventors: Axel Siegfried Herrmann, Georg Lonsdorfer, Hauke Seegel, Marc Fette, Jens Wulfsberg, Patrick Schiebel
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Publication number: 20160221278Abstract: A system for repairing a component made out of a plastic comprises a frame, a multiaxial guide device coupled with the frame, with a tool holder arranged thereon, an optical acquisition device, a processing device, and a plastic deposition device. The frame comprises a mounting device for retaining the frame on a component surface. The optical acquisition device, the processing device and the plastic deposition device are arranged on the tool holder. The optical acquisition device is set up to optically inspect a surface area of the component lying in proximity to the frame from at least one viewing angle, so as to acquire the spatial structure of the surface area. The processing device is set up to remove material of a damaged area from the component for generating a base surface with a desired structure and boundary edges.Type: ApplicationFiled: January 28, 2016Publication date: August 4, 2016Inventors: Axel SIEGFRIED HERRMANN, Jens WULFSBERG, Georg LONSDORFER, Marc FETTE
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Patent number: 9399325Abstract: A device for automatically laying and draping a plurality of web-form portions of a dry sheet-like formation, in particular of a multiaxial laid fiber fabric and/or a woven reinforcing fabric to create a profiled preform on a core by repeated laying and draping of the portions in order to produce a reinforcing profile with a composite material. Accordingly at least one portion, is kept in at least one cassette between two roller conveyors ready for laying on the core. As a result of the preferably simultaneous laying of preferably more than one prefabricated portion of the sheet-like formation on the core by means of at least one cassette of the cassette arrangement a profiled preform can be fully automatically laid and draped quickly and with great dimensional accuracy and at the same time with good reproducibility for the production of CRP profiles.Type: GrantFiled: March 29, 2011Date of Patent: July 26, 2016Assignee: Airbus Operations GmbHInventors: Carsten Barlag, Rolf Sundermann, Georg Lonsdorfer, Guenther Dressler, Christian Baumgartner
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Publication number: 20160076179Abstract: A honeycomb structure comprising carbon-fiber non-woven, sandwich structure comprising the said honeycomb structure, and process for the production of the said honeycomb structure.Type: ApplicationFiled: September 14, 2015Publication date: March 17, 2016Inventors: Tassilo Witte, Georg Lonsdorfer
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Patent number: 9079366Abstract: The invention relates to a production method for producing seamless, integral aircraft fuselage sections. The method comprises the following steps: a) application of a first vacuum film to a stable winding core and evacuation of the first vacuum film, b) depositing of the fuselage section in layers on the winding core by wrapping the same, c) application of an outer mold that is unstable compared to the stable winding core, to the fuselage section, wherein the winding core stabilizes the outer mold, d) application of a second vacuum film to the outer mold, e) aeration of the first vacuum film and evacuation of the second vacuum film in order to draw the fuselage section closer to the outer mold and detach it from the winding core at least in one region, a) curing of the entire arrangement in an autoclave to produce the finished fuselage section.Type: GrantFiled: June 12, 2008Date of Patent: July 14, 2015Assignee: Airbus Operations GmbHInventors: Carsten Van Vuegt, Christoph Meyer, Georg Lonsdorfer, Thomas Meyn, Helmut Felderhoff
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Patent number: 8919696Abstract: A method for stiffening a skin field of an aircraft fuselage includes providing a skin field for an aircraft fuselage, manufacturing an integral lattice-shaped stiffening structure including a plurality of longitudinal stiffeners and connecting the stiffening structure to the skin field. The manufacturing can include the use of a tool mold having a plurality of longitudinal recesses configured to form longitudinal stiffeners and a plurality of sunken areas disposed between the longitudinal recess. The sunken areas are configured for forming respective mounts that are configured for connection to circumferential stiffeners.Type: GrantFiled: December 29, 2010Date of Patent: December 30, 2014Assignee: Airbus Operations GmbHInventors: Georg Lonsdorfer, Hauke Seegel, Klaus Rode, Andreas Pau, Hartmut Herter, Kevin Danke
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Patent number: 8845946Abstract: A method for manufacturing a fiber composite component having an integral structural design includes positioning a sheet-like fibrous semi-finished product in a mold that defines an outer contour of the fiber composite component. Dimensionally stable fibrous semi-finished products, each having dimensions corresponding to a respective portion of the manufactured fiber composite component, are arranged on the sheet-like fibrous semi-finished product. The dimensionally stable fibrous semi-finished products are stabilized and fixed in place using mold cores. The semi-finished products are resin infiltrated using one of a first or a second gating process so as to form a construct. The first gating process includes gating via the mold cores at a head of each dimensionally stable fibrous semi-finished product and performing extraction in an area of the mold.Type: GrantFiled: December 28, 2010Date of Patent: September 30, 2014Assignee: Airbus Operations GmbHInventors: Georg Lonsdorfer, Hauke Seegel, Klaus Rode, Andreas Pau
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Patent number: 8741208Abstract: Manufacturing of a composite component, such as a composite component of an aircraft, is provided with a molding tool that includes, but is not limited to a first mold, a second mold and a pressure generator. Between the first mold and the second mold, a membrane is arranged so that between the first mold and the membrane a first region is formed, and between the second mold and the membrane a second region is formed. In the first region, a fibrous mat is arranged. In the second region with the use of the pressure generator 116 counter-pressure can be produced so that the membrane is pressed in the direction of the fibrous mat.Type: GrantFiled: October 17, 2011Date of Patent: June 3, 2014Assignee: Airbus Operations GmbHInventors: Matthias Nothdurft, Günther Dressler, Rolf-Georg Sundermann, Georg Lonsdorfer
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Patent number: 8512620Abstract: A method of manufacturing a component from a composite-fiber-material semifinished product includes providing a forming support having a contour including at least one section corresponding to a surface of the manufactured component. The semifinished product is placed onto the forming support and the semifinished product is formed such that the semifinished product contacts the forming support. Further, a device form manufacturing component includes the forming support having the contour including at least one section corresponding to the surface of the manufacture component.Type: GrantFiled: December 29, 2010Date of Patent: August 20, 2013Assignee: Airbus Operations GmbHInventors: Georg Lonsdorfer, Hauke Seegel, Klaus Rode
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Publication number: 20120267824Abstract: Manufacturing of a composite component, such as a composite component of an aircraft, is provided with a molding tool that includes, but is not limited to a first mold, a second mold and a pressure generator. Between the first mold and the second mold, a membrane is arranged so that between the first mold and the membrane a first region is formed, and between the second mold and the membrane a second region is formed. In the first region, a fibrous mat is arranged. In the second region with the use of the pressure generator 116 counter-pressure can be produced so that the membrane is pressed in the direction of the fibrous mat.Type: ApplicationFiled: October 17, 2011Publication date: October 25, 2012Applicant: AIRBUS OPERATIONS GMBHInventors: Matthias NOTHDURFT, Günther DRESSLER, Rolf-Georg SUNDERMANN, Georg LONSDORFER
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Publication number: 20120055617Abstract: The invention relates to a production method for producing seamless, integral aircraft fuselage sections. The method comprises the following steps: a) application of a first vacuum film to a stable winding core and evacuation of the first vacuum film, b) depositing of the fuselage section in layers on the winding core by wrapping the same, c) application of an outer mould that is unstable compared to the stable winding core, to the fuselage section, wherein the winding core stabilises the outer mould, d) application of a second vacuum film to the outer mould, e) aeration of the first vacuum film and evacuation of the second vacuum film in order to draw the fuselage section closer to the outer mould and detach it from the winding core at least in one region, a) curing of the entire arrangement in an autoclave to produce the finished fuselage section.Type: ApplicationFiled: June 12, 2008Publication date: March 8, 2012Applicant: AIRBUS OPERATIONS GMBHInventors: Carsten Van Vuegt, Christoph Meyer, Georg Lonsdorfer, Thomas Meyn, Helmut Felderhoff
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Publication number: 20110240213Abstract: A device for automatically laying and draping a plurality of web-form portions of a dry sheet-like formation, in particular of a multiaxial laid fiber fabric and/or a woven reinforcing fabric to create a profiled preform on a core by repeated laying and draping of the portions in order to produce a reinforcing profile with a composite material. Accordingly at least one portion, is kept in at least one cassette between two roller conveyors ready for laying on the core. As a result of the preferably simultaneous laying of preferably more than one prefabricated portion of the sheet-like formation on the core by means of at least one cassette of the cassette arrangement a profiled preform can be fully automatically laid and draped quickly and with great dimensional accuracy and at the same time with good reproducibility for the production of CRP profiles.Type: ApplicationFiled: March 29, 2011Publication date: October 6, 2011Inventors: Carsten Barlag, Rolf Sundermann, Georg Lonsdorfer, Guenther Dressler, Christian Baumgartner
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Publication number: 20110186683Abstract: A method for stiffening a skin field of an aircraft fuselage includes providing a skin field for an aircraft fuselage, manufacturing an integral lattice-shaped stiffening structure including a plurality of longitudinal stiffeners and connecting the stiffening structure to the skin field. The manufacturing can include the use of a tool mold having a plurality of longitudinal recesses configured to form longitudinal stiffeners and a plurality of sunken areas disposed between the longitudinal recess. The sunken areas are configured for forming respective mounts that are configured for connection to circumferential stiffeners.Type: ApplicationFiled: December 29, 2010Publication date: August 4, 2011Applicant: AIRBUS OPERATIONS GMBHInventors: Georg Lonsdorfer, Hauke Seegel, Klaus Rode, Andreas Pau, Hartmut Herter, Kevin Danke
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Publication number: 20110156309Abstract: A method of manufacturing a component from a composite-fiber-material semifinished product includes providing a forming support having a contour including at least one section corresponding to a surface of the manufactured component. The semifinished product is placed onto the forming support and the semifinished product is formed such that the semifinished product contacts the forming support. Further, a device form manufacturing component includes the forming support having the contour including at least one section corresponding to the surface of the manufacture component.Type: ApplicationFiled: December 29, 2010Publication date: June 30, 2011Applicant: AIRBUS OPERATIONS GMBHInventors: Georg Lonsdorfer, Hauke Seegel, Klaus Rode
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Publication number: 20110156305Abstract: A method for manufacturing a fiber composite component having an integral structural design includes positioning a sheet-like fibrous semi-finished product in a mold that defines an outer contour of the fiber composite component. Dimensionally stable fibrous semi-finished products, each having dimensions corresponding to a respective portion of the manufactured fiber composite component, are arranged on the sheet-like fibrous semi-finished product. The dimensionally stable fibrous semi-finished products are stabilized and fixed in place using mold cores. The semi-finished products are resin infiltrated using one of a first or a second gating process so as to form a construct. The first gating process includes gating via the mold cores at a head of each dimensionally stable fibrous semi-finished product and performing extraction in an area of the mold.Type: ApplicationFiled: December 28, 2010Publication date: June 30, 2011Applicant: AIRBUS OPERATIONS GMBHInventors: Georg Lonsdorfer, Hauke Seegel, Klaus Rode, Andreas Pau