Patents by Inventor Hartmut Brenneis

Hartmut Brenneis 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).

  • Lightweight structural component in particular for aircraft and method for its production
    Patent number: 7494092
    Abstract: Lightweight structural component including at least one panel and at least one stiffening element oriented one of lengthwise and crosswise. The at least one stiffening element includes two side pieces. Each of the two side pieces is at least partially connected to the panel in a material-locking manner. The two side pieces are connected to the panel at two separate joint zones. A method of producing the lightweight structural component includes milling the at least one panel to form at least one thickened region and joining the two side pieces to the at least one panel at the two separate joint zones. This Abstract is not intended to define the invention disclosed in the specification, nor intended to limit the scope of the invention in any way.
    Type: Grant
    Filed: January 15, 2004
    Date of Patent: February 24, 2009
    Assignees: Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V., Airbus Deutschland GmbH
    Inventors: Berndt Brenner, Bernd Winderlich, Jens Standfuβ, Jörg Schumacher, Hartmut Brenneis, Walter Zink
  • LIGHTWEIGHT STRUCTURAL COMPONENT IN PARTICULAR FOR AIRCRAFT AND METHOD FOR ITS PRODUCTION
    Publication number: 20080296433
    Abstract: Lightweight structural component including at least one panel and at least one stiffening element oriented one of lengthwise and crosswise. The at least one stiffening element includes two side pieces. Each of the two side pieces is at least partially connected to the panel in a material-locking manner. The two side pieces are connected to the panel at two separate joint zones. A method of producing the lightweight structural component includes milling the at least one panel to form at least one thickened region and joining the two side pieces to the at least one panel at the two separate joint zones. This Abstract is not intended to define the invention disclosed in the specification, nor intended to limit the scope of the invention in any way.
    Type: Application
    Filed: August 15, 2008
    Publication date: December 4, 2008
    Applicants: Fraunhofer-Gesellschaft zuer Foerderung der angewandten Forschung e.V., Airbus Deutschland GmbH
    Inventors: Berndt Brenner, Bernd Winderlich, Jens Standfub, Jorg Schumacher, Hartmut Brenneis, Walter Zink
  • Lightweight structural component in particular for aircraft and method for its production
    Publication number: 20050077427
    Abstract: Lightweight structural component including at least one panel and at least one stiffening element oriented one of lengthwise and crosswise. The at least one stiffening element includes two side pieces. Each of the two side pieces is at least partially connected to the panel in a material-locking manner. The two side pieces are connected to the panel at two separate joint zones. A method of producing the lightweight structural component includes milling the at least one panel to form at least one thickened region and joining the two side pieces to the at least one panel at the two separate joint zones. This Abstract is not intended to define the invention disclosed in the specification, nor intended to limit the scope of the invention in any way.
    Type: Application
    Filed: January 15, 2004
    Publication date: April 14, 2005
    Applicant: Fraunhofer-Gesellschaft zur Forderung der angewandten Forschung e.V.
    Inventors: Berndt Brenner, Bernd Winderlich, Jens Standfuss, Jorg Schumacher, Hartmut Brenneis, Walter Zink
  • Integral structural shell component for an aircraft and method of manufacturing the same
    Patent number: 6684593
    Abstract: A structural panel component, such as an aircraft fuselage shell component, includes a single integral part having longitudinal and crosswise stiffening elements integrally arranged on a skin sheet. This integral component has been formed by a high speed milling chip removal process applied to a solid plate-shaped semi-finished starting material. The skin sheet has areas of differing thicknesses, and the height, thickness, and spacing of the stiffening elements varies as needed, depending on the local loading conditions that will prevail on the finished structural component. The configuration of the component can be optimized to minimize the weight while satisfying all load strength requirements. The manufacturing method is very simple and economical.
    Type: Grant
    Filed: February 22, 2001
    Date of Patent: February 3, 2004
    Assignee: Airbus Deutschland GmbH
    Inventors: Hartmut Brenneis, Walter Zink
  • Integral structural shell component for an aircraft and method of manufacturing the same
    Publication number: 20010015043
    Abstract: A structural panel component, such as an aircraft fuselage shell component, includes a single integral part having longitudinal and crosswise stiffening elements integrally arranged on a skin sheet. This integral component has been formed by a high speed milling chip removal process applied to a solid plate-shaped semi-finished starting material. The skin sheet has areas of differing thicknesses, and the height, thickness, and spacing of the stiffening elements varies as needed, depending on the local loading conditions that will prevail on the finished structural component. The configuration of the component can be optimized to minimize the weight while satisfying all load strength requirements. The manufacturing method is very simple and economical.
    Type: Application
    Filed: February 22, 2001
    Publication date: August 23, 2001
    Inventors: Hartmut Brenneis, Walter Zink