Thermal Isolation of Solid Rocket Motor Exit Cone and Nozzle

Period of Performance: 09/26/2014 - 09/24/2016


Phase 2 SBIR

Recipient Firm

Plasma Processes, LLC.
4914 Moores Mill Road Array
Huntsville, AL 35811
Principal Investigator


Primary missile structures, ancillary mechanical and electrical sub-components of missile propulsion systems must be thermally isolated from hot propulsion gases. Silica-cloth phenolic and carbon-cloth phenolic are the go-to legacy insulator materials of choice. However, these materials have limited temperature use; mechanical degradation with decomposition of the matrix; and high thermal conductivity in the charred state. At present, burn durations, flame temperatures and inter-pulse delays are constrained to avoid overheating. The objective a Phase II investigation is to develop and evaluate a low cost, high payoff ceramic-based laminar composite. Results of material property studies will provide input for trade studies to investigate the benefits and payoff of this technology in multiple propulsion systems. Favorable insulator designs will be evaluated in sub-scale test motors. Approved for Public Release 14-MDA-7739 (18 March 14).