A ROCKET ENGINE WITH MULTI-STAGE COMBUSTION OF A MIXTURE OF PROPELLANTS

The invention relates to a rocket engine with the multi-stage combustion of a mixture of propellants, having at least one pre-combustion chamber and a main combustion chamber, a propellant mixture supply system to these chambers, including a fuel and oxidant pump, and an exhaust gas nozzle, which according to the invention has at least at least one staged detonation chamber, comprising at least two preliminary detonation chambers (1, 2), and at their outlet - a post-combustion chamber (3), where full mixing and post-combustion of detonation products from the pre-chambers (1, 2) takes place, and the exhaust gases they are directed outwards through the nozzle (4), preferably of the Aerospike type. In this engine, in an individual staged detonation chamber, the preliminary detonation chambers (1, 2) are concentric and have a tubular, annular, disc or conical structure and operate in the rotating detonation mode, with one of the two preliminary detonation chambers (1, 2) in the individual staged detonation chamber, a gaseous mixture with a composition rich in fuel is supplied, and a gaseous mixture with a composition rich in oxidant is supplied to the other chamber. [0002] The solution according to the invention allows reduction of the dimensions of the rocket engine with multi-stage combustion of a mixture of propellants, as well as the mass of the engine compared to the state of the art solutions.