Patents by Inventor Cord Haack
Cord Haack 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: 11643181Abstract: A connector for connecting a frame to a transversely extending stringer of a fuselage structure of an aircraft includes a base carrier extending in a longitudinal connector direction, a first connecting portion connected to the base carrier and extending in a first transverse connector direction, the first connecting portion having a coupling structure in an end region remote from the base carrier for engaging around an end region of a cross-section of the stringer, and a second connecting portion connected to the base carrier and adapted to be connected to the frame.Type: GrantFiled: May 7, 2021Date of Patent: May 9, 2023Inventors: Cord Haack, Carsten Paul, Bernhard Hörger
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Patent number: 11634205Abstract: A frame component for a frame of a fuselage structure of an aircraft includes a central web extending along a longitudinal direction and having an inner edge region with respect to a radial direction running transversely with respect to the longitudinal direction and an outer edge region with respect to the radial direction. An inner web is bent from the inner edge region of the central web towards a first side. An outer web is bent from the outer edge region of the central web towards the first side. The central web, the outer web and the inner web are produced integrally from a metal sheet and together define a C-shaped cross section of the frame component. At least one stringer recess is formed in the outer web and in the outer edge region of the central web. The central web has, in the region of the stringer recess, a first reinforcing formation which forms a protrusion on the first side of the central web.Type: GrantFiled: July 31, 2020Date of Patent: April 25, 2023Assignee: Premium Aerotec GmbHInventors: Cord Haack, Carsten Paul, Bernhard Hörger
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Patent number: 11560242Abstract: A method of manufacturing a structural component for a vehicle, in particular an aircraft or spacecraft, includes additively manufacturing a reinforcing plate of a metal material having on a joining surface a plurality of joining arms projecting from the joining surface; and joining the reinforcing plate at the joining surface to a structural element to form the structural component by inserting the joining arms into the structural element such that the joining arms permanently hold the structural element together with the reinforcing plate.Type: GrantFiled: May 13, 2021Date of Patent: January 24, 2023Inventors: Cord Haack, Carsten Paul, Bernhard Hörger
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Publication number: 20220267012Abstract: A mounting rail for receiving and holding loads in an interior of a vehicle includes a support element with a recess extending in the longitudinal direction of the support element and a rail element. The rail element is arranged in the recess of the support element and is mechanically coupled to the support element. The rail element has a receiving space for receiving and holding loads. The mounting rail is divided into two parts so that different materials can be used for the support element and the rail element, which meet the respective individual requirements hereof.Type: ApplicationFiled: February 24, 2022Publication date: August 25, 2022Applicant: Premium Aerotec GmbHInventors: Cord Haack, Carsten Paul, Bernhard Hörger
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Patent number: 11396358Abstract: A door system for an aircraft includes a door frame defining a door opening with a first perimeter strut and a second perimeter strut spaced apart from the first perimeter strut, at least one first frame stopper attached to the first perimeter strut and at least one second frame stopper attached to the second perimeter strut. The frame stoppers each comprise a first contact portion projecting into the door opening and having a first toothing. The first toothings are each formed on an inner surface of the first abutment portion. Further, the door system comprises a door mounted movably relative to the door frame and disposed in the door opening in a closed state, and a number of door stoppers corresponding to the number of frame stoppers disposed on opposite sides of the door and connected to the door, each door stopper having a second abutment portion. The second abutment portion comprises a second toothing formed complementary to the first toothing.Type: GrantFiled: February 12, 2021Date of Patent: July 26, 2022Inventors: Cord Haack, Carsten Paul, Bernhard Höger
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Publication number: 20210362881Abstract: A method of manufacturing a structural component for a vehicle, in particular an aircraft or spacecraft, includes additively manufacturing a reinforcing plate of a metal material having on a joining surface a plurality of joining arms projecting from the joining surface; and joining the reinforcing plate at the joining surface to a structural element to form the structural component by inserting the joining arms into the structural element such that the joining arms permanently hold the structural element together with the reinforcing plate.Type: ApplicationFiled: May 13, 2021Publication date: November 25, 2021Applicant: Premium Aerotec GmbHInventors: Cord Haack, Carsten Paul, Bernhard Hörger
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Publication number: 20210347462Abstract: A connector for connecting a frame to a transversely extending stringer of a fuselage structure of an aircraft includes a base carrier extending in a longitudinal connector direction, a first connecting portion connected to the base carrier and extending in a first transverse connector direction, the first connecting portion having a coupling structure in an end region remote from the base carrier for engaging around an end region of a cross-section of the stringer, and a second connecting portion connected to the base carrier and adapted to be connected to the frame.Type: ApplicationFiled: May 7, 2021Publication date: November 11, 2021Applicant: Premium Aerotec GmbHInventors: Cord Haack, Carsten Paul, Bernhard Hörger
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Publication number: 20210253218Abstract: A door system for an aircraft includes a door frame defining a door opening with a first perimeter strut and a second perimeter strut spaced apart from the first perimeter strut, at least one first frame stopper attached to the first perimeter strut and at least one second frame stopper attached to the second perimeter strut. The frame stoppers each comprise a first contact portion projecting into the door opening and having a first toothing. The first toothings are each formed on an inner surface of the first abutment portion. Further, the door system comprises a door mounted movably relative to the door frame and disposed in the door opening in a closed state, and a number of door stoppers corresponding to the number of frame stoppers disposed on opposite sides of the door and connected to the door, each door stopper having a second abutment portion. The second abutment portion comprises a second toothing formed complementary to the first toothing.Type: ApplicationFiled: February 12, 2021Publication date: August 19, 2021Inventors: Cord Haack, Carsten Paul, Bernhard Höger
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Publication number: 20210031897Abstract: A frame component for a frame of a fuselage structure of an aircraft includes a central web extending along a longitudinal direction and having an inner edge region with respect to a radial direction running transversely with respect to the longitudinal direction and an outer edge region with respect to the radial direction. An inner web is bent from the inner edge region of the central web towards a first side. An outer web is bent from the outer edge region of the central web towards the first side. The central web, the outer web and the inner web are produced integrally from a metal sheet and together define a C-shaped cross section of the frame component. At least one stringer recess is formed in the outer web and in the outer edge region of the central web. The central web has, in the region of the stringer recess, a first reinforcing formation which forms a protrusion on the first side of the central web.Type: ApplicationFiled: July 31, 2020Publication date: February 4, 2021Inventors: Cord HAACK, Carsten PAUL, Bernhard HÖRGER
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Patent number: 10450048Abstract: An aircraft fuselage structure comprising a skin element having an inner surface, a support structure connected to the inner surface for supporting the skin element, and a door opening provided in the skin element, wherein the support structure comprises an upper longitudinal element, a lower longitudinal element, a first circumferential element and a second circumferential element provided at the door opening. The object to provide an aircraft fuselage structure, wherein the support structure around the door opening is optimized for a minimum weight, is achieved in that the support structure comprises a first upper angled element extending from an upper first corner to an upper center point, and a second upper angled element extending from an upper second corner to the upper center point, such that the upper longitudinal element, the first upper angled element, and the second upper angled element together form a central upper triangle.Type: GrantFiled: November 8, 2016Date of Patent: October 22, 2019Assignee: Airbus Operations GmbHInventors: Dirk Elbracht, Cord Haack
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Publication number: 20180016010Abstract: A monument assembly for an aircraft includes at least one component of a primary structure of the aircraft, in particular a fuselage stiffening element, and a plurality of interconnected framework elements for creating a self-carrying three-dimensional framework. The at least one fuselage stiffening element is attachable to a skin of the aircraft and includes at least one bracket, wherein the framework is mechanically supported on the at least one bracket of the at least one component of the primary structure of the aircraft and wherein the framework comprises a plurality of compartments accessible from an interior region of the aircraft. The compartments are adapted for receiving and holding cabin equipment modules.Type: ApplicationFiled: September 28, 2017Publication date: January 18, 2018Inventors: Hermann BENTHIEN, Matthias HEGENBART, Andreas POPPE, Wolfram SCHOPENHAUER, Ralf SCHLIWA, Thomas LERCHE, Cord HAACK, Ralph STURM, Matthias RADNY, Jon RUETER
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Patent number: 9764815Abstract: An aircraft fuselage structure is disclosed herein and includes an outer skin, with circumferential ribs, such that a recess is provided for receiving a wing torsion box in the outer skin, and the ribs are interrupted in the region of the recess. An object of the disclosure includes providing an aircraft fuselage structure designed such that the wing torsion box is able to extend at least partially through the upper region of the fuselage, without the stability of the fuselage being significantly reduced. This can include providing first longitudinal members which are adjacent to the recess and which extend along the longitudinal edges beyond the entire length thereof. End regions of the first longitudinal members are connected to ribs which extend circumferentially at intervals from the transverse edges of the recess along the outer skin over the vertical longitudinal central plane.Type: GrantFiled: September 16, 2014Date of Patent: September 19, 2017Assignee: Airbus Defence and Space GmbHInventors: Hermann Benthien, Cord Haack, Andreas Poppe, Michael Burrichter, Torsten Abraham, Michael Brinckmann, Christoph Dierker, Frank Werth, Wulf Bindewald
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Publication number: 20170129586Abstract: An aircraft fuselage structure comprising a skin element having an inner surface, a support structure connected to the inner surface for supporting the skin element, and a door opening provided in the skin element, wherein the support structure comprises an upper longitudinal element, a lower longitudinal element, a first circumferential element and a second circumferential element provided at the door opening. The object to provide an aircraft fuselage structure, wherein the support structure around the door opening is optimized for a minimum weight, is achieved in that the support structure comprises a first upper angled element extending from an upper first corner to an upper center point, and a second upper angled element extending from an upper second corner to the upper center point, such that the upper longitudinal element, the first upper angled element, and the second upper angled element together form a central upper triangle.Type: ApplicationFiled: November 8, 2016Publication date: May 11, 2017Inventors: Dirk Elbracht, Cord Haack
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Publication number: 20150259067Abstract: A module for an aircraft has a fuselage structure and a floor element defining a floor plane. The module includes a frame device adapted for mounting a functional element and the frame device is adapted for attachment to the floor element of the aircraft at a first location in the floor plane.Type: ApplicationFiled: March 17, 2015Publication date: September 17, 2015Applicants: Airbus S.A.S., Airbus Operations GmbHInventors: Bruno Saint-Jalmes, André Rezag, Jason Zaneboni, Markus Schumacher, Andrew Muin, Cord Haack, Michael Carr
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Patent number: 9010686Abstract: A module for an aircraft having a fuselage structure and a floor element defining a floor plane. The module includes a frame device adapted for mounting a functional element and the frame device is adapted for attachment to the floor element of the aircraft at a first location in the floor plane. The frame device is adapted for attachment to the fuselage structure of the aircraft at a second location, wherein the second location is not in the floor plane.Type: GrantFiled: December 27, 2006Date of Patent: April 21, 2015Assignee: Airbus S.A.S.Inventors: Bruno Saint-Jalmes, André Rezag, Jason Zaneboni, Markus Schumacher, Andrew Muin, Cord Haack, Michael Carr
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Publication number: 20150102168Abstract: An aircraft fuselage structure is disclosed herein and includes an outer skin, with circumferential ribs, such that a recess is provided for receiving a wing torsion box in the outer skin, and the ribs are interrupted in the region of the recess. An object of the disclosure includes providing an aircraft fuselage structure designed such that the wing torsion box is able to extend at least partially through the upper region of the fuselage, without the stability of the fuselage being significantly reduced. This can include providing first longitudinal members which are adjacent to the recess and which extend along the longitudinal edges beyond the entire length thereof. End regions of the first longitudinal members are connected to ribs which extend circumferentially at intervals from the transverse edges of the recess along the outer skin over the vertical longitudinal central plane.Type: ApplicationFiled: September 16, 2014Publication date: April 16, 2015Inventors: Hermann BENTHIEN, Cord HAACK, Andreas POPPE, Michael BURRICHTER, Torsten ABRAHAM, Michael BRINCKMANN, Christoph DIERKER, Frank WERTH, Wulf BINDEWALD
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Patent number: 8905349Abstract: The structural element of an aircraft fuselage, with stringers running in the longitudinal direction of the aircraft fuselage and ribs running transversely to the stringers in the circumferential direction of the fuselage. According to the invention, at least one of the stringers running in the longitudinal direction of the aircraft fuselage is designed as a fastening rail for elements to be installed in the aircraft fuselage.Type: GrantFiled: April 25, 2008Date of Patent: December 9, 2014Assignee: AIRBUS Operations GmbHInventors: Claus-Peter Gross, Cord Haack, Dirk Humfeldt, Oliver Thomaschewski
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Patent number: 8899523Abstract: This invention provides a fuselage of an aircraft or space vehicle with a fuselage section having an outer skin, wherein at least the outer skin of the fuselage section consists of a glass-fiber reinforced aluminum laminate to form a safety zone for passengers in the event of a fire.Type: GrantFiled: April 14, 2008Date of Patent: December 2, 2014Assignee: AIRBUS Operations GmbHInventors: Cord Haack, Thomas Beumler
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Patent number: 8651421Abstract: An aircraft fuselage structure which is constructed from a plurality of shells which are joined together is disclosed. Each shell forms part of the aircraft fuselage and comprises a support structure and a skin which is arranged on the latter and outwardly seals the aircraft fuselage in a compression-proof manner. The aircraft fuselage structure comprises an upper and side shell and a lower shell, of which the lower shell has a radius which is essentially significantly larger than the radius of the upper and side shell. The upper and side shell and the lower shell are joined together at transition regions extending in the longitudinal direction of the aircraft. The support structure of the lower shell is designed in terms of its strength in such a manner that it is capable of absorbing the internal pressure loading of the lower shell without the use of a main crossmember.Type: GrantFiled: June 5, 2007Date of Patent: February 18, 2014Assignee: Airbus Operations GmbHInventor: Cord Haack
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Patent number: 8534605Abstract: An aircraft fuselage structure is described with frames running in the circumferential direction, stringers running in the longitudinal direction and a skin which is arranged thereon and outwardly seals the aircraft fuselage in a compression-proof manner. According to the invention, it is provided that the aircraft fuselage structure contains prefabricated integral units (10) which each run in the circumferential direction of a fuselage segment and in which the frame (11) of a fuselage segment and connecting elements (17, 18) for connection to skin elements (20) comprising stringers (22) and skin (21) are formed.Type: GrantFiled: June 5, 2007Date of Patent: September 17, 2013Assignee: Airbus Operations GmbHInventor: Cord Haack