Numerical Analysis of Different Injectors for
Kerosene/Hydrogen-Peroxide and Ethanol Amine/Hydrogen-Peroxide for Satellite
Thruster 2023-01-5180
In a satellite thruster the function of injector plays a major role in
controlling the combustion. This paper presents the numerical simulation of two
most used injectors namely, impinging doublet, and triplet using Ansys fluent.
The injectors are designed for the non-toxic, green propellants used in
satellite thrusters. The present study focuses on the design and simulation of
the injectors with 2 variant of green propellants i.e.,
Kerosene/Hydrogen-peroxide and Ethanol Amine/Hydrogen-peroxide. The objective of
the study is to investigate the performance of the two injectors in terms of
atomization, combustion efficiency and thrust generation. Theoretical design
calculations were performed for a 20 N bi-propellant satellite thruster. A
comparative study on the condensed combustion products and injector was carried
out using NASA CEA Run code and Ansys fluent, respectively. The ethanol
amine/hydrogen-peroxide injector showed better performance in terms of
combustion efficiency. The study provides valuable insights for the design of
injectors for satellite thrusters, which can help in improving the performance
of space propulsion systems.
