TaC/TaC CMCs for Aluminized Propellant SRMs

In this proposed MDA Phase I SBIR Program, MATECH seeks to develop woven TaC ceramic fiber reinforced TaC matrix CMCs for aluminized propellant solid rocket motors (SRMs). Aluminized propellant SRMs constitute the most eroding environment when compared to non-aluminized SRMs and liquid SRMs. Both theoretically and experimentally, it has been shown that the reaction initiation temperature of TaC is 1000oC higher than that of carbon and 400oC higher than HfC, thus making it a prime candidate for thrusters used in the next generation of higher performance, hypersonic missile defense systems. Moreover, it has been demonstrated that the erosion rate of TaC is significantly less that HfC and carbon under comparable conditions. Of all the refractory metal carbide systems, TaC holds the most promise for the unique conditions of aluminized propellant SRMs.