The numerical simulation of the ignition process of the monomethyl hydrazine–nitrogen tetroxide attitude-control thrusters is difficult because of the complex hypergolic gas–liquid chemical reaction between the propellants. To calculate the thruster ignition delay accurately, a 36-step gas-phase chemical kinetics model and a one-step finite-rate liquid-phase hypergolic reaction are proposed. These chemical mechanisms are integrated into the Euler–Lagrange-based transient spray combustion simulation platform. The calculated ignition pressure curve of a 2 kN thruster coincides well with that from the experiment. The numerical and experimental ignition delays are 2.4 and 3.1 ms, respectively. A parameter study shows that the liquid-phase reaction at the propellant impingement points consumes 22–44% propellant and provides energy to heat the gas mixtures, which is essential for a successful gas-phase ignition. The lower limit of ignition delay was estimated as 1.5 ms under design restrictions for most thrusters.
Numerical Simulation of Ignition Process for the Monomethyl Hydrazine–Nitrogen Tetroxide Thrusters
Journal of Propulsion and Power ; 35 , 4 ; 704-719
2019-07-01
Article (Journal)
Electronic Resource
English
Numerical Study of Hydrazine and Nitrogen Tetroxide Combustion in small Rocket Motors
British Library Conference Proceedings | 1994
|