Theoretical Modeling and Design of a Coaxial-Swirl Injector and Thruster Components for MMH/NTO-Based Upper Stage Thrusters

Abstract

Coaxial swirl injectors solve the major problem when it comes to liquid propulsion, which is the mixing of the fuel and oxidizer. It helps by mixing the fuel at an atomic level and making sure that the mixture is even. This paper focuses on the design of an engine with coaxial swirl injector faceplate using hypergolic propellant. The major problem with the hypergolic propellant is that it ignites on contact, but with the help of a coaxial swirl injector we can take it as an advantage by modifying the spray cone angle so that the contact point is at an optimal distance. The work entails the design of a modified coaxial swirl injector for hypergolic propellants which is then integrated into a faceplate with multiple injectors. Then, with the help of the dimensions of the faceplate, the combustion chamber is designed to withstand the simultaneous instant combustion from the multiple injectors, which is then focused onto the custom-designed nozzle to maximize the output thrust.