Low Toxicity, Non-cryogenic Liquid Propellant Upper Stage Engine

Our vision for the next generation missile and space propulsion engine is a flexible and non-toxic propulsion technology using HAN/kerosene, offering variable thrust with a high degree of mission tailoring. Additionally, high bulk density of HAN/kerosene bi-propellant improves stage mass fraction and delivers performance metrics that exceed current toxic storable propellants. We propose an innovative injector capable of delivering fine atomization for rapid vaporization and capable of rapid transients to enable pulsed propulsion for tactical missions. We have teamed with UAH for test capabilities assessment in Phase I and test operations support in Phase II. In phase I, we will perform initial design trades through modeling and simulation to demonstrate engine performance capabilities to meet MDA requirements. We will assess test facility requirements for development testing in Phase II. At the end of Phase I, we will have a detailed engine concept and facility requirements, including costs, for development testing in Phase II. Approved for Public Release | 19-MDA-9932 (21 Feb 19)