Accession Number : ADP005167

Title :   Composite Repair of Cocured J-Stiffened Panels. Design and Test Verification,

Corporate Author : MESSERSCHMITT-BOELKOW-BLOHM G M B H MUNICH (GERMANY F R) HELICOPTER AND MILITARY AIRCRAFT GROUP

Personal Author(s) : Guenther,Georg ; Lemmer,Ludwig

Report Date : OCT 1986

Pagination or Media Count : 19

Abstract : An increasing percentage of military aircraft fuselage and wing structures are being replaced by cocured integrated CFC-structures. The probability of damage in day-to-day operation is increased, since most of the structure is located on the aircraft surface. The most common field of application for cocured stiffeners are thin panels critical to buckling under shear and/or compression loading and fuselage frames subject to bending. Bonded repair methods for two maintenance levels (depot and field) have been developed and tested using representative components. For the stiffened panels both repair methods (field and depot) fulfilled the structural requirements and proved their durability in the fatigue tests. Test results of the stiffened skin elements showed that cocured fuselage structures with complex geometries are repairable without reduction in strength and stiffness. Tests performed after artificial ageing of the repaired structure proved their reliability in the environment.

Descriptors :   *AIRCRAFT MAINTENANCE, *AIRCRAFT PANELS, *COMPOSITE STRUCTURES, FUSELAGES, WINGS, REPAIR, CARBON REINFORCED COMPOSITES, FIBER REINFORCED COMPOSITES, STIFFNESS, LAMINATES, SYMPOSIA

Distribution Statement : APPROVED FOR PUBLIC RELEASE