DEVELOPMENT OF THERMOPLASTIC MATRIX COMPOSITE FILAMENT WINDING

THERMOPLASTIC MATRIX COMPOSITE MATERIALS SUCH AS GRAPHITE/PEEK AND GLASS/ULTEM OFFER GREAT POTENTIAL AS STRUCTURAL MATERIALS FOR HELICOPTER AIRFRAMES. THROUGH THE USE OF THERMOPLASTIC MATRIX COMPOSITES IT IS POSSIBLE TO BUILD THE LIGHTWEIGHT, DURABLE, DAMAGE TOLERANT STRUCTURE REQUIRED FOR HELICOPTERS. THIS PROGRAM IS DESIGNED TO DEVELOP AN AUTOMATED FIBER-REINFORCED THERMOPLASTIC FIBER PLACEMENT SYSTEM, SPECIFICALLY A FILAMEND WINDING SYSTEM. A MANUFACTURING METHOD FOR FILAMENT WINDING AND SIMULTANEOUSLY CONSOLIDATING SELECTED GRAPHITE AND/OR GLASS THERMOPLASTIC MATRIX COMBINATIONS IS DEVELOPED. A HOT-HEAD,LAYDOWN/CONSOLIDATION SYSTEM IS DESIGNED AND FABRICATED. MECHANICAL, PHYSICAL AND NONDESTRUCTIVE TEST DATA IS GENERATED USING THE SYSTEM USING FILAMENT WOULD THERMOPLASTIC MATRIX COMPOSITES. A FINAL REPORT IS PROVIDEDWHICH SUMMARIZES THIS EFFORT AND PROVIDES GUIDELINES FOR FURTHER PHASE II DEVELOPMENT INCLUDING THE FABRICATION OF FILAMENT WOUND HELICOPTER STRUCTURES.