Low-Erosion and Affordable Nozzles for Advanced Air-to-Air Missiles Navy SBIR FY2012.1 Sol No.: Navy SBIR FY2012.1 Topic No.: N121-014 Topic Title: Low-Erosion and Affordable Nozzles for Advanced Air-to-Air Missiles Proposal No.: N121-014-0576 Firm: Edward Pope Dr dba MATECH 31304 Via Colinas, Suite 102 Westlake Village, California 91362-3901 Contact: Steve Kirkwood Phone: (818) 991-8500 Web Site: www.matechgsm.com Abstract: In this Navy Phase I SBIR program, MATECH proposes to demonstrate its oxidative and erosion-resistant high temperature zirconium oxy-carbide (matrix) with carbon fiber (Cf-ZrOCm) ceramic matrix composite (CMC) for nozzles in multi pulse solid rocket motor, low-smoke propellant, tactical air-to-air missiles. Current graphite and carbon phenolic throat and nozzle components will not meet erosion and thermal insulation (heat soak) requirements. MATECH has developed a Cf-ZrOCm structural insulator/propulsion component material system in which the matrix has demonstrated virtually no erosion by H2 Arc Heater testing and by LHMEL laser testing with Mach 0.9 air impingement. This material also exhibits very low thermal conductivity (<1.5 W/m-�C) while maintaining very high thermal shock tolerance. Additionally, a throat/nozzle prototype will be fabricated to demonstrate the feasibility of a reduced part count through the integration of the nozzle throat and throat insulator into a single component. Following a successful Phase I demonstration, multiple hot fire static and pulsed tests are planned for a Phase II to validate the performance of a full scale nozzle/throat in multi-pulse modes, bringing this material to a TRL6. This Phase I proposal benefits from the active participation and support of Aerojet (Sacramento, CA) and Raytheon (Tuscan, AZ). Benefits: ZrOC-based ceramic matrix composites can benefit the NAVY by providing improved mission performance and capability to air-to-air pulsed motor missiles and other high temperature, erosion resistant structural insulator application including hot motor components and aerothermal components. This material system also offers relatively low weight and very low thermal conductivity with high shock resistance. In addition to the NAVY, other DOD agencies can benefit inasmuch as this material system has been successfully hot fire tested at Aerojet with applicability to aerothermal structures and DACS thruster components for strategic missiles, tactical missiles, and space launch systems, in addition to missile defense systems. Commercial space launch systems could also benefit from this technology. Return