Storable propellants, such as UDMH, MMH, NTO etc. are widely used in upper stage and spacecraft propulsion systems
with long-term operation in space conditions. Nevertheless, because of their negative influence on the environment as well
as a high toxicity to leaving beings, it is necessary to use additional neutralization and personnel protection means during
ground operations that significantly increase the cost of propulsion system development and operations. But this protective
equipment is imperfect and do not fully exclude the threat to life and heals of personnel. So, there is a strong tendency
on transfer to green propellants. One of such propellants, is the hydrogen peroxide + kerosene propellant pair. The application
of this propellant pair for the considered type of propulsion systems will allow providing both a multiple in-flight
startups without a significant design complication and ay high efficiency. We present an analytical estimation of providing
multiple ignition and parameter stability of engine’s combustion chamber.