Computational-Theoretical Study of Resonant System of Gasdynamical Ignition for Low-Thrust Liquid-Propellant Rocket Engines

The computational-theoretical study of a gasdynamical ignition system of low-thrust liquid-propellant rocket engines is carried out. An operating principle of the system is based on implementation of the cyclic process in the "supersonic nozzle-resonator with confuser inlet" system. The optimization of the geometric and regime parameters of the ignition system is performed for achieving the maximum intensity of gas-mixture heating.