Soviet rocket's engines (NPO Energomash)

RD-107 Development of the RD-107 rocket engines spanned between 1954 and 1957. It was designed to power the first stage of the Vostok launch vehicle. The RD-107 system incorporates four main combustion chambers and two smaller steering chambers. All six chambers are fed from a single turbopump. The RD-107 system launched both Sputnik 1 and Yuri Gagarin into orbit and since 1957 has been successfully used to launch both crewed (Soyuz) and autonomous missions (Foton, Gamma). Produced at Energomash's Samara subsidiary, the RD-107 is in use on the Soyuz rocket. The engine has been upgraded approximately 15 times since its original design in 1957.

RD-108 The RD-108, based on the same four-chamber, four-nozzle design as the RD-107, powers the second stage of the Vostok launch vehicle. Where as the RD-107 has two vernier engines, located 90 degrees apart on the outside of the four nozzles, the RD-108 has four vernier engines. The RD-108, used in conjunction with the RD-107, has boosted many of Russia's earth-observing satellites, planetary probes as well as cargo and piloted space craft.

RD-111 (1962) The RD-111 engine, completed in 1962, powered the first stage of one version of the Cosmos rocket. This four gimbaled engine is no longer in production.

RD-119 (1963) The RD-119 liquid oxygen/UDMH engine was developed for the second stage of the Cosmos launch vehicle. Designed from 1958-1963, this engine is no longer used or produced, although manufacturing capability still exists. It is a single chamber engine, using four nozzles for flight control.

RD-120 The RD-120, developed for second stage of the Zenit launch vehicle, is a liquid oxygen/kerosene single chamber engine with turbopump feeding system and four vernier engines used for steering. With modification the highly reliable RD-120 can be used as a first stage engine, and the RD-120 is the predecessor of the RD-170/171 engines. The RD-120 is produced in conjunction with NPO Yuzhnoye in Ukraine, with approximately 80 to 90 percent of component materials coming from Russia.

RD-120K A modified version of the RD-120, the RD-120K, is proposed for use as a first stage engine on small to medium size launch vehicles. The RD-120K has a single chamber gimbaled in one plane.

RD-161 (1988) The RD-161 is a single chamber liquid oxygen/kerosene engine under development since 1988 for use as an universal launcher or as an upper stage for a modified Soyuz rocket. The RD-161 will utilize a stage combustion cycle and is intended to have in-flight multiple restart capability (up to seven times). Two plane gambling and use of gaseous vernier will provide flight control.

RD-161P A modified RD-161, the RD-161P is being developed as an orbital maneuvering engine. It is designed to have multistart capability (up to fifty times in one mission) and flight control by gimbaling in two planes.

RD-170/RD-171 The RD170 is a four chamber liquid oxygen/kerosene engine used on each of the four strap-on boosters of the Energia launch vehicle. The RD-171 is a slight variation of the RD-170 and is used as the first stage of the Zenit booster. The only difference between these engines is that the RD-170 has two-axis gimbal capability, whereas the RD-171 only has single axis. The engines are flight qualified, having flown on two Energia (RD-170) and twenty Zenit (RD-171) orbital flights as boosters and first-stage engines, respectively. The RD-170 is most mature Russian engine and incorporates the state-of-the-art Russian propulsion technology.

RD-180 The RD-180 is a liquid oxygen/kerosene engine under development for possible use on an upgraded medium launch vehicle. It derives from the RD-170/171 and is a closed cycle, staged combustion engine with two combustion chambers and two nozzles instead of four.

RD-214 (1957) The RD-214 liquid propellant rocket engine was completed in 1957 and was used on the first stage of the Cosmos launch vehicle prototype. It has four chambers and no verniers, but uses refractory vanes protruding into the exhaust for steering. This engine is no longer in production.

RD-216 (1960) Energomash completed development on the RD-216 in 1960. It was first used operationally in the 1964 launch of the SL-8 Cosmos first stage. The RD-216 is a cluster of two identical engine blocks with two combustion chambers. This engine is no longer in production.

RD-218 (1961) Le RD-218 est un moteur à carburant liquide pour le premier étage des fusées. Il a été développé entre 1958 et 1961 pour être utilisé sur des missiles stratégiques. Son utilisation actuel n'est pas confirmée, mais il n'est plus produit.

RD-219 The RD-219 is a two chamber engine thought to be developed for the second stage of the Tsyklon launch vehicle. Originally designed for a military system.

RD-253 (1965) The RD-253 is NPO Energomash's most powerful single-chamber engine. Fueled with nitrogen tetroxide/UDMH, it is a closed cycle, staged combustion engine. Increased thrust is achieved by after-burning the oxidizer gas which increases engine efficiency. Used on the first stage of the Proton launch vehicle since 1965, the RD-253 has operated without failure since 1969.

RD-301 The RD-301 was originally developed as an upper stage engine for launch vehicle. The engine uses an unique fluorine/ammonia liquid propellant. The RD-301 completed certification testing but was never operationally flown.

Famille RD-700 The RD-700 family of rocket engines is intended to be NPO energomash's first two-phase tripropellant engines. The launch mode operates on liquid oxygen, liquid hydrogen, and kerosene, while the trans-atmospheric mode operates on liquid hydrogen and liquid oxygen. Operation in the three propellant mode achieves increased specific impulse relative to specific impulse of the liquid oxygen-kerosene only engines. Bi-modal operation from a single engine is potentially attractive for advanced projects such as single stage to orbit launch vehicles. Two variants of the engine are under development: a two chamber version (RD-701) and single chamber version (RD-704).

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