COMPOUND PROPULSION SYSTEM OF REUSABLE FIRST STAGE LAUNCHER Russian patent published in 2021 - IPC F02K9/78 F02K7/16 

FIELD: rocket technology.

SUBSTANCE: invention relates to rocket and space technology and may be used to create reusable rocket systems. The compound propulsion system of a reusable first stage launcher contains a ramjet consisting of an inner and outer frame installed coaxially and interconnected by pylons forming a profiled channel of an axisymmetric air intake installed in the inlet part of a profiled channel, a fuel collector with nozzles and a flame stabilizer installed in the inner cavity of the annular combustion chamber formed by the inner and outer frames, in the outlet part whereof a shortened central body of the ramjet spike nozzle is installed, and the fuel supply to the nozzles is conducted using a turbo pump unit including a centrifugal pump, inlet whereof is connected with the outlet of the fuel tank, and a turbine located on the same shaft with a centrifugal pump, the outlet of whereof is connected to the fuel collector, and a heat exchanger is located in the inner cavity of the annular combustion chamber, the inlet of said heat exchanger connected to the outlet of the centrifugal pump and the outlet to the inlet of the turbine, a liquid-propellant rocket engine (LRE) located in the inner cavity of the central body of the ramjet spike nozzle. The uncooled firing walls of the annular combustion chamber and the shortened central body of the spike nozzle are made of carbon-carbon composite material (CCCM).

EFFECT: the invention provides improvement in the mass-dimensional characteristics of the aircraft due to the use of a combined power plant and as an oxidizer -air oxygen at the initial stage of flight.

2 cl, 1 dwg