FIELD: rocketry.
SUBSTANCE: the device for combustion of rocket propellant has a source of rocket propellant based on ionic salt, for example, hydroxylammoniumonitrate, combustion chamber, and a reactor. The reactor serves for dissociation of the main part of ionic salt contained in the rocket propellant and is installed for supply of the products of dissociation together with and additional propellant component contained in the rocket propellant to the combustion chamber. The method for propellant combustion in the device for combustion of rocket propellant baaed an hydroxylammoniumnitrate consists in dissociation of hydroxylammoniumnitrate and combustion of the dissociation products of the mentioned hydroxylammoniumnitrate together with not reacting propellant components contained in the rocket propellant. According to the mentioned method, the rocket propellant is introduced in the reactor, and decomposed in the reactor with dissociation at least of the greatest part of hydroxylammoniumnitrate contained in the rocket propellant. Then the output products of the reactor are directed to the combustion chamber.
EFFECT: enhanced reliability of ignition, as well as enhanced number of the cycles of use of the catalyst.
20 cl, 6 dwg
