Revision of the conceptual model of combustion mechanism in a liquid-propellant rocket on the basis of the results of highly informative experiments. II. Updating of the model

On the basis of the accumulated experimental data, it is established that gas recirculation in the combustion chamber of a liquid-propellant rocket is due not to a single factor (ejection by a fuel injection) but two factors; the second factor is the nonequilibrium (over the chamber cross section) distribution of the sources and outflows of gases from the combustion process. The second factor, acting on recirculation, acts again on combustion with a certain delay, etc. Taking other characteristics into account, the combustion process in this case should be examined in the context of the theory of self-organization of nonequilibrium systems. A corresponding conceptual model is constructed that is consistent at a qualitative level with the expermental data on various forms of parametric instability of combustion in a liquid-propellant rocket.