NASA FUTURE MISSIONS PLACE STRINGENT REQUIREMENTS ON HIGH TEMPERATURE AND LIGHT-WEIGHT MATERIALS.THIS PROPOSAL ADDRESSES SOME OF THE MOST CHALLENGING MATERIALS ISSUES WITH RESPECT TO HOT STRUCTURES, VERY HIGH TEMPERATURE, UP TO 4500 DEGREES F, APPLICATIONS. THE VERY SUCCESSFUL NASA LED X-43A HYPERSONIC FLIGHT PROVED THE ABILITY TO USE STATE OF THE ART (SOTA) 2D C-C WITH OXIDATION COATING SYSTEM. HOWEVER, CURRENT MATERIAL SYSTEMS CAN ONLY OFFER LIMITED TEMPERATURE CAPABILITY (<3000 F) AND MOSTLY FOR SINGLE USE APPLICATION. IN PHASE I, TWO INNOVATIVE TECHNOLOGIES, UNDERCOAT AND FGM MULTI-LAYER COATS, WERE DEVELOPED AND SCREENED. THEY WERE FURTHER INTEGRATED INTO TWO SOTA C-C COMPOSITES. OXIDATION PROTECTED C-C SAMPLES WERE TORCH TESTED AT 3500 F/ 30 MINUTES, AT 4200 F/ 2 MINUTES UP TO 10 CYCLES, AND AT 3000 F/COOL/ 4000 F CYCLES SHOWING VERY PROMISING RESULTS. THE COMBINED EFFECTS OF THE UNDERCOAT AND FGM SPRAY COATS PROVIDE REPEATABLE PERFORMANCE BY CREATING A GLASS FORMING, CONFORMING AND ADHERENT EXTERNAL COATING TO PROTECT THE C-C FROM BEING OXIDIZED. THE OVERALL OBJECTIVE OF THE PROPOSED P-II IS TO FURTHER DEVELOP AND OPTIMIZE A ROBUST, TAILORABLE, AND AFFORDABLE OXIDATION PROTECTION SYSTEM FOR C-C TPS AND C-C HOT STRUCTURE BY INTEGRATING OUR UNDERCOAT AND FGM MULTI-LAYER SPRAY COAT TECHNOLOGIES INTO AT LEAST TWO GRADES C-C COMPOSITES (T300 AND P30 2D C-C) MEETING HIGHER TEMPERATURE PERFORMANCE UP TO 4500 F AND MULTI-USE APPLICATIONS. WORK PLAN INCLUDES 12 TASKS OVER 24 MONTH GROUPED INTO 5 CATEGORIES. ONCE FURTHER OPTIMIZED AND VALIDATED UNDER PHASE II, THESE TECHNOLOGIES CAN EASILY BE INTEGRATED INTO SOTA C-C USING CURRENT MANUFACTURING FACILITIES. THE RESULTING OXIDATION PROTECTED C-C COULD BE TAILORABLE, AFFORDABLE, AND EASILY SCALED UP FOR LARGE COMPONENTS OR STRUCTURE REQUIRED IN FUTURE NASA, DOD AND COMMERCIAL SPACE APPLICATIONS.