Accession Number : ADA301599

Title :   Design and Analysis of a Stiffened Composite Fuselage Panel,

Corporate Author : LOCKHEED-GEORGIA CO MARIETTA

Personal Author(s) : Dickson, J. N. ; Biggers, S. B.

PDF Url : ADA301599

Report Date : AUG 1980

Pagination or Media Count : 52

Abstract : A stiffened composite panel has been designed that is representative of the fuselage structure of existing wide bodied aircraft. The panel is a minimum weight design, based on the current level of technology and realistic loads and criteria. Several different stiffener configurations were investigated in the optimization process. The final configuration is an all graphite epoxy J-stiffened design in which the skin between adjacent stiffeners is permitted to buckle under design loads. Fail-safe concepts typically employed in metallic fuselage structure have been incorporated in the design. A conservative approach has been used with regard to structural details such as skin frame and stringer frame attachments and other areas where sufficient design data was not available.

Descriptors :   *COMMERCIAL AIRCRAFT, *COMPOSITE MATERIALS, *COMPOSITE STRUCTURES, *FUSELAGES, *AIRCRAFT PANELS, METALS, OPTIMIZATION, STRUCTURAL ANALYSIS, STIFFNESS, CONFIGURATIONS, BUCKLING, WEIGHT, FATIGUE, ATTACHMENT, FRAMES, DESIGN CRITERIA, SKIN(STRUCTURAL), FLIGHT LOADS, GRAPHITE EPOXY COMPOSITES, FAIL SAFE.

Subject Categories : Transport Aircraft
      Commercial and General Aviation
      Laminates and Composite Materials

Distribution Statement : APPROVED FOR PUBLIC RELEASE