Patents by Inventor Jeffrey F. Stulc

Jeffrey F. Stulc 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).

  • Splice Joints for Composite Aircraft Fuselages and Other Structures
    Publication number: 20120061512
    Abstract: Structures and methods for joining composite fuselage sections and other panel assemblies together are disclosed herein. In one embodiment, a shell structure configured in accordance with the present invention includes a first panel portion positioned adjacent to a second panel portion. The first panel portion can include a first stiffener attached to a first composite skin, and the second panel portion can include a second stiffener attached to a second composite skin. The shell structure can further include a fitting extending across a first edge region of the first panel portion and a second edge region of the second panel portion. A first end portion of the fitting can be attached to the first stiffener and the first composite skin, and a second end portion of the fitting can be attached to a second stiffener and a second composite skin, to join the first panel portion to the second panel portion.
    Type: Application
    Filed: November 18, 2011
    Publication date: March 15, 2012
    Applicant: THE BOEING COMPANY
    Inventors: Jeffrey F. Stulc, Wallace C. Chan, Brian C. Clapp, Neal G. Rolfes
  • Splice joints for composite aircraft fuselages and other structures
    Patent number: 8061035
    Abstract: Structures and methods for joining composite fuselage sections and other panel assemblies together are disclosed herein. In one embodiment, a shell structure configured in accordance with the present invention includes a first panel portion positioned adjacent to a second panel portion. The first panel portion can include a first stiffener attached to a first composite skin, and the second panel portion can include a second stiffener attached to a second composite skin. The shell structure can further include a fitting extending across a first edge region of the first panel portion and a second edge region of the second panel portion. A first end portion of the fitting can be attached to the first stiffener and the first composite skin, and a second end portion of the fitting can be attached to a second stiffener and a second composite skin, to join the first panel portion to the second panel portion.
    Type: Grant
    Filed: January 18, 2008
    Date of Patent: November 22, 2011
    Assignee: The Boeing Company
    Inventors: Jeffrey F. Stulc, Wallace C. Chan, Brian C. Clapp, Neal G. Rolfes
  • Splice joints for composite aircraft fuselages and other structures
    Patent number: 7325771
    Abstract: Structures and methods for joining composite fuselage sections and other panel assemblies together are disclosed herein. In one embodiment, a shell structure configured in accordance with the present invention includes a first panel portion positioned adjacent to a second panel portion. The first panel portion can include a first stiffener attached to a first composite skin, and the second panel portion can include a second stiffener attached to a second composite skin. The shell structure can further include a fitting extending across a first edge region of the first panel portion and a second edge region of the second panel portion. A first end portion of the fitting can be attached to the first stiffener and the first composite skin, and a second end portion of the fitting can be attached to a second stiffener and a second composite skin, to join the first panel portion to the second panel portion.
    Type: Grant
    Filed: September 23, 2004
    Date of Patent: February 5, 2008
    Assignee: The Boeing Company
    Inventors: Jeffrey F. Stulc, Wallace C. Chan, Brian C. Clapp, Neal G. Rolfes