Patents by Inventor Paul Joern
Paul Joern 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: 11021226Abstract: A method for producing a fuselage portion, in particular for an aircraft or spacecraft, has the following method steps: welding a skin portion containing a thermoplastic material with a former containing a thermoplastic material in the region of a predetermined welding zone; and connecting an attachment element, configured as a crack stopper, to the skin portion and to the former in the region of the welding zone.Type: GrantFiled: June 6, 2017Date of Patent: June 1, 2021Assignee: AIRBUS OPERATIONS GMBHInventor: Paul Joern
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Patent number: 10486372Abstract: A method for integrating a backing-structure assembly in a structure of an aircraft or spacecraft is described. In this case, a plurality of individual elements is joined to form the backing-structure assembly. The individual elements for the backing-structure assembly and a skin portion for the structure are provided. The elements are arranged on a pre-assembly device which comprises retaining devices, which are each configured to hold one of the elements so as to be adjustable with respect to the position and/or location thereof. Some or all of the elements are connected to the skin portion. In the method, by adjusting the retaining devices for tolerance compensation, gaps between joint regions of the elements and the skin portion are eliminated or adjusted.Type: GrantFiled: June 5, 2017Date of Patent: November 26, 2019Assignee: Airbus Operations GmbHInventor: Paul Joern
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Patent number: 10450052Abstract: A sandwich structure with an outer cover layer, inner cover layer, core layer, and pins extending through the core layer. The sandwich structure has a large core thickness resistant to crack formation and to detachment of the cover layers from the core layer. An anchor layer is between the outer and inner cover layers and divides the core layer, at least in areas, into an outer core layer section and inner core layer section. An outer group of pins extends through the outer core layer section and an inner group of pins extends through the inner core layer section. The outer group pins are connected to the anchor layer with their first end and to the outer cover layer with their opposite second end, and the inner group pins are connected to the anchor layer with their first end and to the inner cover layer with their opposite second end.Type: GrantFiled: July 22, 2016Date of Patent: October 22, 2019Assignee: Airbus Operations GmbHInventors: Paul Joern, Karim Grase
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Patent number: 9937996Abstract: A passenger aircraft with a passenger cabin is described, wherein the passenger aircraft comprises a fully functional door, which is openable and closable and which is adapted for an entrance and an exit of passengers, and en emergency exit door, which is exclusively adapted for an emergency exit of passengers from the passenger cabin. Therein, the emergency exit door is arranged in an area of a fuselage of the passenger aircraft, which is arranged ahead of and/or behind of wings of the passenger aircraft.Type: GrantFiled: May 14, 2015Date of Patent: April 10, 2018Assignee: AIRBUS OPERATIONS GMBHInventors: Paul Joern, Claus Hanske, Arne Roth
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Publication number: 20170355434Abstract: A method for producing a fuselage portion, in particular for an aircraft or spacecraft, has the following method steps: welding a skin portion containing a thermoplastic material with a former containing a thermoplastic material in the region of a predetermined welding zone; and connecting an attachment element, configured as a crack stopper, to the skin portion and to the former in the region of the welding zone.Type: ApplicationFiled: June 6, 2017Publication date: December 14, 2017Inventor: Paul Joern
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Publication number: 20170355152Abstract: A method for integrating a backing-structure assembly in a structure of an aircraft or spacecraft is described. In this case, a plurality of individual elements is joined to form the backing-structure assembly. The individual elements for the backing-structure assembly and a skin portion for the structure are provided. The elements are arranged on a pre-assembly device which comprises retaining devices, which are each configured to hold one of the elements so as to be adjustable with respect to the position and/or location thereof. Some or all of the elements are connected to the skin portion. In the method, by adjusting the retaining devices for tolerance compensation, gaps between joint regions of the elements and the skin portion are eliminated or adjusted.Type: ApplicationFiled: June 5, 2017Publication date: December 14, 2017Applicant: Airbus Operations GmbHInventor: Paul Joern
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Publication number: 20170355471Abstract: A method for joining skin portions of a closed fuselage, in particular for an aircraft or spacecraft, has the following method steps: providing at least a first skin portion and a second skin portion, at least one of the skin portions being fitted with components to remain in the fuselage; positioning at least the first skin portion and the second skin portion relative to one another in a first joint such that the skin portions form a circumferentially closed fuselage arrangement; guiding a first joining head along the first joint on an outer surface of the fuselage arrangement; and guiding a second joining head along the first joint on an inner surface of the fuselage arrangement, the second joining head being guided along longitudinal guide means which are arranged inside the circumferentially closed fuselage arrangement and are formed at least in part by the components to remain in the fuselage.Type: ApplicationFiled: June 5, 2017Publication date: December 14, 2017Applicant: Airbus Operations GmbHInventor: Paul Joern
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Patent number: 9694516Abstract: The invention relates to a fixing thread 1, 5, 10, 16 for sewing together reinforcing fibers, in particular to form a fiber preform, for the production of a fiber-reinforced composite component by means of impregnation with a curable polymer material. According to the invention, the fixing thread 1, 5, 10, 16 has an interface 4, 9, 15, 19 for locally increasing the ductility of a matrix formed by the curable polymer material and has at least one core thread 2, 6, 11, 12, 17, so as in particular to reduce the tendency for microcracks to form in the matrix of the finished composite component in the regions where the fixing threads 1, 5, 10, 16 penetrate. The interface 4 may be formed, for example, by an enclosure of the core thread 1 by a thermoplastic polymer material, for example by polyethylene, polypropylene or the like.Type: GrantFiled: July 24, 2006Date of Patent: July 4, 2017Assignee: Airbus Operations GmbHInventors: Paul Joern, Ulrich Eberth
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Publication number: 20170151729Abstract: A method for reinforcing a cellular material includes producing a through-hole in the cellular material that extends from a first surface of the cellular material to a second surface of the cellular material; reaching through the through-hole from the first surface of the cellular material to the second surface of the cellular material; taking hold of at least one fiber bundle at the second surface of the cellular material; and pulling the at least one fiber bundle into the through-hole in the cellular material. Producing the through-hole in the cellular material includes perforating the cellular material with a rotating and/or oscillating needle.Type: ApplicationFiled: November 18, 2016Publication date: June 1, 2017Applicant: Airbus Operations GmbHInventors: Paul Joern, Markus Mueller
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Patent number: 9637213Abstract: A segment and a method for producing such a segment, in particular for an aircraft, having a skin field and a skin field stiffening structure. The skin field and stiffening structure are made from fiber-reinforced plastic materials. The stiffening structure is bonded to an inner surface of the skin field and comprises a multiplicity of first stiffeners and mounts which are formed integrally with the first stiffeners and extend in a transverse direction of the first stiffeners for the connection of second stiffeners to form an integral lattice structure. Reinforcement elements are provided for mechanically fixing the mounts to the skin field. Each reinforcement element has a connection section and a blocking section having an extension in a direction inclined to the connection section. The connection section penetrates the skin field and the mounts, and the blocking section is in contact with an outer surface of the skin field.Type: GrantFiled: May 27, 2014Date of Patent: May 2, 2017Assignee: Airbus Operations GmbHInventors: Paul Joern, Markus Mueller
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Patent number: 9637215Abstract: A pressure bulkhead made of fiber composite material for an aircraft fuselage for the pressure-tight axial closure of a fuselage region configured to be put under internal pressure. The bulkhead comprises a first area element, at least one second area element and a plurality of core elements. The first area element has a plurality of receptacles. Each receptacle is configured to receive a core element. The core elements are received in the receptacles between surfaces facing one another of the first area element and of the at least one second area element. The surfaces facing one another of the first area element and of the at least one second area element are connected to one another in regions without core elements.Type: GrantFiled: November 24, 2014Date of Patent: May 2, 2017Assignee: AIRBUS OPERATIONS GMBHInventors: Paul Joern, Karim Grase, Ichwan Zuardy, Alexei Vichniakov, Bernd Schwing
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Patent number: 9586668Abstract: A fuselage cell structure for an aircraft includes at least two skin panels including at least one double shell skin panel and at least one monolithic skin panel. At least one longitudinal brace or a transverse brace is disposed so as to form at least one of longitudinal seam or a transverse seam between the double shell skin panel and the monolithic skin panel. The fuselage cell structure includes at least one of a longitudinal bracket and a load transfer point. The longitudinal bracket is disposed in a region of the longitudinal seam and includes a first and a second longitudinal flanges disposed offset with respect to one another and connected by a web. The load transfer point is disposed in a region of the transverse seam so as to connect the longitudinal brace disposed on the monolithic skin panel to the double shell skin panel.Type: GrantFiled: March 16, 2010Date of Patent: March 7, 2017Assignee: Airbus Operations GmbHInventors: Wolf-Dietrich Dolzinski, Norbert Heltsch, Arne Hartwig, Markus Mueller, Markus Joerg Weber, Jens-Ulrich Prowe, Paul Joern
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Publication number: 20170021910Abstract: A sandwich structure with an outer cover layer, inner cover layer, core layer, and pins extending through the core layer. The sandwich structure has a large core thickness resistant to crack formation and to detachment of the cover layers from the core layer. An anchor layer is between the outer and inner cover layers and divides the core layer, at least in areas, into an outer core layer section and inner core layer section. An outer group of pins extends through the outer core layer section and an inner group of pins extends through the inner core layer section. The outer group pins are connected to the anchor layer with their first end and to the outer cover layer with their opposite second end, and the inner group pins are connected to the anchor layer with their first end and to the inner cover layer with their opposite second end.Type: ApplicationFiled: July 22, 2016Publication date: January 26, 2017Inventors: Paul Joern, Karim Grase
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Publication number: 20160375535Abstract: A drilling method for structural parts, in particular for carbon fiber composite structural parts, comprising the following method steps: providing a structural part and a collecting element; attaching the collecting element to a first side of the structural part opposite a drill point provided on a second side of the structural part, wherein a collecting portion of the collecting element is sealed off in a dust-tight manner from surroundings; drilling through the structural part from the second side of the structural part, at the drill point, using a drill, wherein the drill emerges from the structural part on the first side and enters the collecting portion of the collecting element, wherein drilling dust accumulating on the first side is collected by the collecting portion. A collecting element for a drilling method of this kind is disclosed.Type: ApplicationFiled: June 24, 2016Publication date: December 29, 2016Inventors: Paul Joern, Markus Mueller
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Publication number: 20160375978Abstract: A stiffened fuselage component made of a fiber reinforced composite material, in particular for use in an aircraft, comprises a skin element and a plurality of elongated stiffening elements forming a stiffening element pattern comprising a plurality of node points and being attached to an inner surface of the skin element. At least some of the node points are defined by an intersection of at least two stiffening elements at an acute angle or an obtuse angle. At least some of the elongated stiffening elements are shaped so as to define an internal cavity delimited by an inner surface of the stiffening elements and covered by the skin element.Type: ApplicationFiled: June 23, 2016Publication date: December 29, 2016Inventor: Paul Joern
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Patent number: 9365279Abstract: The present invention relates to a fuselage of an aircraft or spacecraft, with at least one shell element and a structural element. An interspace to which air can be admitted by an air stream is provided between the at least one shell element and the structural element. The fuselage is distinguished by the fact that, to form the air-admitting air stream as an outgoing/incoming air stream of a pressurized interior space of the fuselage, the interspace is connected to a corresponding outgoing/incoming air connection of the interior space. The invention also relates to a corresponding aircraft or spacecraft and to a method of actively insulating such a fuselage.Type: GrantFiled: February 21, 2008Date of Patent: June 14, 2016Assignee: Airbus Operations GmbHInventor: Paul Joern
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Publication number: 20160101576Abstract: A method for manufacturing a fibre composite component is disclosed. A single-piece foam body or the parts of a multi-part foam body having at least one recess which is open towards a first side of the foam body are prepared and positioned. A rigidifying element for the backing structure or a preform or first semi-finished product for forming the rigidifying element is arranged in the recess at least in portions. A skin portion or a second semi-finished product for forming the skin portion is provided, and brought into contact, in regions, with the foam body on the first side thereof and with the rigidifying element. The skin portion or second semi-finished product and the rigidifying element or preform or first semi-finished product in contact therewith are processed further in such a way that a fibre composite component is obtained in which the skin portion and the rigidifying element are interconnected.Type: ApplicationFiled: September 12, 2014Publication date: April 14, 2016Inventor: Paul Joern
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Publication number: 20150329194Abstract: A passenger aircraft with a passenger cabin is described, wherein the passenger aircraft comprises a fully functional door, which is openable and closable and which is adapted for an entrance and an exit of passengers, and en emergency exit door, which is exclusively adapted for an emergency exit of passengers from the passenger cabin. Therein, the emergency exit door is arranged in an area of a fuselage of the passenger aircraft, which is arranged ahead of and/or behind of wings of the passenger aircraft.Type: ApplicationFiled: May 14, 2015Publication date: November 19, 2015Inventors: Paul JOERN, Claus HANSKE, Arne ROTH
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Publication number: 20150144736Abstract: A pressure bulkhead made of fiber composite material for an aircraft fuselage for the pressure-tight axial closure of a fuselage region configured to be put under internal pressure. The bulkhead comprises a first area element, at least one second area element and a plurality of core elements. The first area element has a plurality of receptacles. Each receptacle is configured to receive a core element. The core elements are received in the receptacles between surfaces facing one another of the first area element and of the at least one second area element. The surfaces facing one another of the first area element and of the at least one second area element are connected to one another in regions without core elements.Type: ApplicationFiled: November 24, 2014Publication date: May 28, 2015Inventors: Paul Joern, Karim Grase, Ichwan Zuardy, Alexei Vichniakov, Bernd Schwing
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Publication number: 20140377501Abstract: A segment and a method for producing such a segment, in particular for an aircraft, having a skin field and a skin field stiffening structure. The skin field and stiffening structure are made from fiber-reinforced plastic materials. The stiffening structure is bonded to an inner surface of the skin field and comprises a multiplicity of first stiffeners and mounts which are formed integrally with the first stiffeners and extend in a transverse direction of the first stiffeners for the connection of second stiffeners to form an integral lattice structure. Reinforcement elements are provided for mechanically fixing the mounts to the skin field. Each reinforcement element has a connection section and a blocking section having an extension in a direction inclined to the connection section. The connection section penetrates the skin field and the mounts, and the blocking section is in contact with an outer surface of the skin field.Type: ApplicationFiled: May 27, 2014Publication date: December 25, 2014Inventors: Paul Joern, Markus Mueller