Patents by Inventor Steffen Biesek

Steffen Biesek 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).

  • Patent number: 9463865
    Abstract: A fuselage cell for an aircraft includes at least two shell segments forming a fuselage cell. The shell segments are provided with a plurality of longitudinal and/or circumferential reinforcements that are integral with a skin panel of the respective shell segment. The reinforcements at least sectionally form a closed cross-sectional geometry together with at least the skin panel of the corresponding shell segment in order to create at least one hollow space, wherein at least one system component at least sectionally extends and/or at least one system medium is at least sectionally routed in the at least one hollow space. The reinforcements also fulfill the function of accommodating at least part of the system components and system mediums of the technical equipment of the aircraft. This results in weight savings and a simplified installation because the number of required mountings and connectors for the system components is reduced.
    Type: Grant
    Filed: September 27, 2012
    Date of Patent: October 11, 2016
    Assignee: Airbus Operations GmbH
    Inventors: Holger Frauen, Robert Alexander Goehlich, Steffen Biesek
  • Patent number: 9073621
    Abstract: An aircraft includes an insulation system for thermal and acoustic insulation. The insulation system includes a cabin, an outer skin, a sound insulating unit, and a heat insulating unit. The sound insulating unit is designed to acoustically insulate the aircraft. The heat insulating unit is designed to thermally insulate the aircraft. The sound insulating unit and the heat insulating unit are arranged between the cabin and the outer skin.
    Type: Grant
    Filed: February 23, 2010
    Date of Patent: July 7, 2015
    Assignee: Airbus Operations GmbH
    Inventors: Robert Alexander Goehlich, Steffen Biesek, Cihangir Sayilgan
  • Patent number: 8766138
    Abstract: The subject matter herein discloses a method for producing a fuselage section of an aircraft via large-sized, in particular long, shell segments. The method includes joining at least two skin segments to form a large-sized skin field, welding a plurality of integral stringers onto the skin field, and welding a plurality of integral and closed ring frames to the skin field.
    Type: Grant
    Filed: April 24, 2009
    Date of Patent: July 1, 2014
    Assignee: Airbus Operations GmbH
    Inventors: Holger Frauen, Robert Alexander Goehlich, Steffen Biesek
  • Patent number: 8356772
    Abstract: A lightweight structure is disclosed, in particular a lightweight structure for an aircraft which is formed from a large number of components which can be joined together by weld joining processes. According to the invention, the lightweight structure has a component thickness which is increased corresponding to the loads in the joint region of the at least one welded joint compared to a thickness of the component outside the joint region.
    Type: Grant
    Filed: July 24, 2009
    Date of Patent: January 22, 2013
    Assignee: Airbus Operations GmbH
    Inventors: Rolf Bense, Steffen Biesek, Robert Alexander Goehlich, Karl-Hinrich Herbst, Michael Kreimeyer, Christian Kulik, Marco Pacchione
  • Publication number: 20120213955
    Abstract: In a method for manufacturing a shell, at least two shell sections are fabricated out of a composite fiber material, at least one compensation body of a plastically deformable material is secured to at least one limiting edge of at least one shell section, the shell sections are overlapped to form the shell, yielding flat seams between respectively adjacent shell sections. The at least one compensation body is arranged on at least one of the seams. In order to compensate for dimensional deviations in each overlap, the shape of the corresponding compensation bodies is changed, and the shells sections are joined together at the seams.
    Type: Application
    Filed: August 18, 2011
    Publication date: August 23, 2012
    Applicant: AIRBUS OPERATIONS GMBH
    Inventors: Steffen Biesek, Robert Alexander Goehlich, Cihangir Sayilgan
  • Patent number: 8100316
    Abstract: The invention relates to a method for joining at least two aircraft fuselage segments (2, 3) by friction stir welding with a tool (8) generating friction heat for the partial plasticisation of an edge region (6, 7) of at least one of the two aircraft fuselage segments and a counter bearing (10) for absorbing the force exerted by the tool (8) on at least one of the two aircraft fuselage segments, wherein at least one of the two aircraft fuselage segments comprises at least one rib (17) and/or one stringer (16). In order to minimise the necessary expense incurred in association with the production aids for the FSW process, it is proposed that the at least one rib (17) and/or the at least one stringer (16) of the at least one aircraft fuselage segment (2, 3) should be used as a counter bearing (10).
    Type: Grant
    Filed: May 6, 2009
    Date of Patent: January 24, 2012
    Assignee: Airbus Operations GmbH
    Inventors: Dirk Groβ, Robert Alexander Goehlich, Steffen Biesek, Rolf Bense
  • Publication number: 20120012698
    Abstract: The invention relates to an aircraft comprising an insulation system for thermal and acoustic insulation. Said insulation system includes a cabin, an outer skin, a sound insulating unit, and a heat insulating unit. The sound insulating unit is designed to acoustically insulate the aircraft. The heat insulating unit is designed to thermally insulate the aircraft. The sound insulating unit and the heat insulating unit are arranged between the cabin and the outer skin.
    Type: Application
    Filed: February 23, 2010
    Publication date: January 19, 2012
    Applicant: AIRBUS OPERATIONS GMBH
    Inventors: Robert Alexander Goehlich, Steffen Biesek, Cihangir Sayilgan
  • Publication number: 20100038489
    Abstract: A lightweight structure is disclosed, in particular a lightweight structure for an aircraft which is formed from a large number of components which can be joined together by weld joining processes. According to the invention, the lightweight structure has a component thickness which is increased corresponding to the loads in the joint region of the at least one welded joint compared to a thickness of the component outside the joint region.
    Type: Application
    Filed: July 24, 2009
    Publication date: February 18, 2010
    Inventors: Rolf Bense, Steffen Biesek, Robert Alexander Goehlich, Karl-Hinrich Herbst, Michael Kreimeyer, Chiristian Kulik, Marco Pacchione
  • Publication number: 20090294018
    Abstract: The invention relates to a method for joining at least two aircraft fuselage segments (2, 3) by friction stir welding with a tool (8) generating friction heat for the partial plasticisation of an edge region (6, 7) of at least one of the two aircraft fuselage segments and a counter bearing (10) for absorbing the force exerted by the tool (8) on at least one of the two aircraft fuselage segments, wherein at least one of the two aircraft fuselage segments comprises at least one rib (17) and/or one stringer (16). In order to minimise the necessary expense incurred in association with the production aids for the FSW process, it is proposed that the at least one rib (17) and/or the at least one stringer (16) of the at least one aircraft fuselage segment (2, 3) should be used as a counter bearing (10).
    Type: Application
    Filed: May 6, 2009
    Publication date: December 3, 2009
    Applicant: AIRBUS DEUTSCHLAND GmbH
    Inventors: Dirk Gross, Robert Alexander Goehlich, Steffen Biesek, Rolf Bense
  • Publication number: 20090283509
    Abstract: The invention relates to a method for producing shell segments with a particularly large length extend for forming a fuselage cell of an aircraft, comprising the following steps: a) Joining at least two skin segments to form a large-sized skin field, b) welding a plurality of integral stringers onto the skin field, and c) welding a plurality of integral ring frame segments to the skin field to finish the shell segment. By means of the shell segments with a large length according to the invention it is possible to reduce the number of fuselage sections that are necessary to form a fuselage cell of an aircraft and thereby reducing the number of necessary cross seams which are weight increasing due to the necessary overlaps and connection elements.
    Type: Application
    Filed: April 24, 2009
    Publication date: November 19, 2009
    Inventors: HOLGER FRAUEN, ROBERT ALEXANDER GOEHLICH, STEFFEN BIESEK