Non Eroding High Temperature Propulsion Nozzle Materials Environments Using Advanced Refractory Ceramic Matrix Composites

Utron Kinetics’ aim in this Small Business Innovation Research (SBIR) Phase I makes a significant contribution to developing non-eroding nozzles suitable for oxidizing environments for high-temperature combustion gas environments across three objectives: Objective 1) Develop ablation resistant, non-eroding, rocket nozzle material(s) with high temperature strength and compatibility with highly oxidizing propellant combustion gases.. Objective 2) Conduct preliminary modeling with most promising material(s), with the intended use in rocket motors per target requirements, including thermo-structural materials’ behavior, ablation and erosion resistance. Further, select mechanical properties will undergo temperature performance testing. Objective 3) Demonstrate manufacturability. In order to meet all the three objectives of this Missile Defense Agency (MDA) SBIR, Utron Kinetics leverages its extensive material science, cermet based composite material development and proven manufacturing capability to develop innovative high temperature refractory carbide-based materials. The expected outcome of proposed work in Phase I includes meeting all the stated MDA SBIR objectives/requirements of advanced nozzle material development/modeling, manufacturability, and high temperature mechanical strength/ductility properties at the target operating temperature. We anticipate that the successfully completion of the Phase I efforts will provide a persuasive basis for continued development for additional materials development, hot-fire testing in oxidizing propellant environment and scaling up cost effective manufacturing in Phase II and beyond for MDA’s transition and other commercial applications. Approved for Public Release | 24-MDA-11917 (27 Sep 24)