Hypergolic Hydrocarbon Engine

Development of novel propulsion systems in the past two decades has focused almost exclusively on cryogenic boost-phase systems (LOX/LH2, LOX/LCH4, and LOX/RP-1) for launchers and uppers stage engines, and Attitude / Reaction Control Systems (A/RCS) for in-space applications using green monopropellants such AF-M315E or LMP-103S. Basic research and development of scalable, non-toxic, non-cryogenic, high-performance bi-propellants are needed for upper stage applications to meet future defense application needs. This program will develop a novel, non-cryogenic, low-cost hypergolic bi-propellant system with performance similar to conventional MMH/NTO systems and based on hydrocarbon fuels. A rigorous design and analysis of current upper stage engine needs will be used to develop a new set of scalable liquid bi-propellant rocket engines ranging in force from 44 N to 4400 N. The new engine family, the Hypergolic Hydrocarbon Engine (HHE) will use a modular test bed to develop a new scalable engine that will be tested in the initial phase of the program. An extensive hot-fire test campaign with heavy-wall hardware and an additively-manufactured flight-grade engine will be conducted to validate scale-up and provide proof-of-concept data before building a full scale 4400 N engine in Phase II. Approved for Public Release | 19-MDA-9932 (21 Feb 19)