THE EXCELLENT PROPERTIES OF CARBON-CARBON (C/C) COMPOSITES MAKE THESE MATERIALS PRIME CANDIDATES FOR HIGH TEMPERATURE RESISTANT STRUCTURES ON ADVANCED MISSILES.

THE EXCELLENT PROPERTIES OF CARBON-CARBON (C/C) COMPOSITES MAKE THESE MATERIALS PRIME CANDIDATES FOR HIGH TEMPERATURE RESISTANT STRUCTURES ON ADVANCED MISSILES. HOWEVER, C/C COMPONENTS MUST BE JOINED TOGETHER TO PRODUCE A FINAL STRUCTURE. THE USE OF ADHESIVE BONDING AND METALLIC FASTENERS IS NOT PRACTICAL AT HIGH TEMPERATURES. THE MOST DESIRABLE FASTENER TO JOIN C/C COMPOSITES TOGETHER WOULD BE FABRICATED FROM C/C TO MAINTAIN GOOD STRENGTH AT TEMPERATURES TO AT LEAST 2500 DEG F ALONG WITH LIGHTWEIGHT AND LOW COEFFICIENT OF THERMAL EXPANSION. FABRIC REINFORCE (2-D)C/C WILL NOT BE SUITABLE BECAUSE OF LOW SHEAR STRENGTH. A PROGRAM IS PROPOSED TO DEVELOP AND EVALUATE ECONOMICAL 3-D AND 4-D C/C COMPOSITES AS FASTENERS TO JOIN C/C COMPOSITE PANELS TOGETHER. AFTER FASTENER REQUIREMENTS DEFINITION AND DESIGN TASKS, 3D AND 4D PERFORMS WILL BE WOVEN WITH HIGH STRENGTH CARBON FIBERS. ALL WEAVING WILL BE DONE ON FULLY AUTOMATED LOOMS FOR MINIMUM COST. C/C PANELS WILL BE FULLY DENSIFIED BY A PROCESS THAT CAN BE SCALED UP TO A LOW COST MANUFACTURING PROCEDURE. THREADED RODS AND NUTS WILL BE MACHINED FROM THE 3D AND 4D C/C AND EVALUATED FOR MECHANICAL AND THERMAL EXPANSION PROPERTIES. A DEMONSTRATION C/C BOLTED JOINT WILL BE FABRICATED.