THE INCREASED USE OF COMPOSITE MATERIALS FOR STRUCTURAL APPLICATIONS IN THE AIRCRAFT INDUSTRY REQUIRES A DEEPER UNDERSTANDING OF COMPOSITE REPAIR. THIS KNOWLEDGE CAN ONLY BE PROVIDED BY IDENTIFYING THE FUNDAMENTALS THAT OUTLINE THE REPAIR PROCESS. THE INTERACTION BETWEEN DISSIMILAR MATRIX MATERIALS, WHICH WOULD ALLOW WIDER SUBSTITUTION OF COMPATIBLE MATERIALS IN STRUCTURAL REPAIRS, HAS BEEN IDENTIFIED AS THE FIRST FUNDAMENTAL STEP. ACCORDINGLY, A SERIES OF EXPERIMENTS HAS BEEN DESIGNED WHERE DISSIMILAR MATRICES REINFORCED WITH THE SAME CONTINUOUS CARBON FIBERS WERE FABRICATED BY DIRECT PROCESSING OR BONDING OF PRECURED LAMINATES. THERMAL ANALYSIS TECHNIQUES SUCH AS DMA AND DSC WERE COUPLED WITH TRADITIONAL MECHANICAL TESTS TO DETERMINE MATERIAL COMPATIBILITY.