RD-0124/0124A

Four-chamber liquid-propellant rocket engine powered by kerosene and liquid oxygen.

The record holder among all oxygen-kerosene rocket engines in the world in terms of specific thrust impulse (efficiency), providing the maximum possible energy characteristics of the PH stage on these fuel components. It is distinguished by highly efficient systems of mixing in the combustion chamber, cooling of the combustion chamber, stability of start-up parameters.

Engines for the upper stages of the Soyuz-2 launch vehicle, the Angara launch vehicle.

THE MAIN PARAMETERS OF THE RD-0124A ENGINE FAMILY

four-chamber liquid-propellantLiquid rocket engine poweredwith byafterburning keroseneof andoxidizing liquidgenerator oxygengas.

Fuel: Oxygen + naphthyl

RD-0124 / RD-0124A Engine Modernization Program

In 1993, according to the Terms of Reference of the GNPRCC "TSSKB-Progress" (now RCC "Progress") and a contract with the Russian Space Agency, work began on the creation of the RD-0124 main engine of the third stage of the upgraded Soyuz-2 launch vehicle.

The peculiarity of this engine is to start without pre-cooling the structure and cavities of the cryogenic component - liquid oxygen, which is especially important for engines with reusable activation.

In 2006, the first flight tests took place as part of the Soyuz-2.1B launch vehicle.

By the end of 2015, 28 flights of the Soyuz-2.1b, Soyuz-STB and Soyuz-2.1v rocket engines with RD-0124 were carried out.

In 1998, the technical design of the RD-0124A engine for the Angara launch vehicle was developed by KBHA according to the TK of the Salyut Design Bureau.

RD-0124A is developed on the basis of the RD-0124 engine, but it has a number of technical features, for example, in terms of fuel selection to control the deviation of the CS, ensuring the pressurization of tanks, and also differs in increased operating time in flight.