Accession Number : ADP006817

Title :   CFRP Stiffened Panels Under Compression,

Corporate Author : BRITISH AEROSPACE PLC WARTON (UNITED KINGDOM)

Personal Author(s) : Bucciz, A. ; Mercurio, U.

Report Date : APR 1992

Pagination or Media Count : 14

Abstract : The purpose was to experimentally demonstrate the validity of the conceptual design of a CFRP stiffened panel suitable for application in the unpressurised after fuselage of a middle size aircraft. Both the theoretical and experimental behaviour has been analysed taking into account the effect of: - Different Materials - Curvature - Barely Visible Impact Damage - Static and Fatigue Loads Composite materials with stiff fibers of last generation coupled with toughened thermosetting resin system were used.

Descriptors :   *PANELS, *STIFFNESS, *TRANSPORT AIRCRAFT, *FIBER REINFORCED COMPOSITES, AIRCRAFT, COMPOSITE MATERIALS, CURVATURE, DAMAGE, FIBERS, FUSELAGES, IMPACT, MATERIALS, PLASTICS, STATICS, THERMOSETTING PLASTICS, FATIGUE(MECHANICS), THERMOPLASTIC RESINS, MILITARY AIRCRAFT, BUCKLING, STRAIN(MECHANICS), REPRINTS, NATO.

Subject Categories : Laminates and Composite Materials
      Transport Aircraft
      Plastics

Distribution Statement : APPROVED FOR PUBLIC RELEASE