The Kosmos-3M was a Russian space launch vehicle, member of the Kosmos rocket family. It was a liquid-fueled two-stage launch vehicle, first launched in 1967 and with over 420 successful launches to its name.
The R-14 Chusovaya was a single stage Intermediate-range ballistic missile developed by the Soviet Union during the Cold War. It was given the NATO reporting name SS-5 Skean and was known by GRAU index 8K65. It was designed by Mikhail Yangel. Chusovaya is the name of a river in Russia. Line production was undertaken by Facility No. 1001 in Krasnoyarsk.
The Kosmos rockets were a series of Soviet and subsequently Russian rockets, derived from the R-12 and R-14 missiles, the best known of which is the Kosmos-3M, which has made over 440 launches. The Kosmos family contained a number of rockets, both carrier rockets and sounding rockets, for orbital and sub-orbital spaceflight respectively. The first variant, the Kosmos, first flew on 27 October 1961. Over 700 Kosmos rockets have been launched overall.
The RD-170 is the world's most powerful and heaviest liquid-fuel rocket engine. It was designed and produced in the Soviet Union by NPO Energomash for use with the Energia launch vehicle. The engine burns kerosene fuel and LOX oxidizer in four combustion chambers, all supplied by one single-shaft, single-turbine turbopump rated at 170 MW (230,000 hp) in a staged combustion cycle.
The RD-58 is a rocket engine, developed in the 1960s by OKB-1, now RKK Energia. The project was managed by Mikhail Melnikov, and it was based on the previous S1.5400 which was the first staged combustion engine in the world. The engine was initially created to power the Block D stage of the Soviet Union's abortive N1 rocket. Derivatives of this stage are now used as upper stages on some Proton and Zenit rockets. An alternative version of the RD-58 chamber, featuring a shorter nozzle, was used as the N1's roll-control engine.
The RD-107 and its sibling, the RD-108, are a type of rocket engine used on the R-7 rocket family. RD-107 engines are used in each booster and the RD-108 is used in the central core. The engines have four main combustion chambers and either two (RD-107) or four (RD-108) vernier chambers.
The RD-253 and its later variants, the RD-275 and RD-275M, are liquid-propellant rocket engines developed in the Soviet Union by Energomash. The engines are used on the first stage of the Proton launch vehicle and use an oxidizer-rich staged combustion cycle to power the turbopumps. The engine burns a hypergolic mixture of unsymmetrical dimethylhydrazine (UDMH) fuel with dinitrogen tetroxide oxidizer, which are highly toxic, but storable at room temperature.
The RD-120 is a liquid upper stage rocket engine burning RG-1 and LOX in an oxidizer rich staged combustion cycle with an O/F ratio of 2.6. It is used in the second stage of the Zenit family of launch vehicles. It has a single, fixed combustion chamber and thus on the Zenit it is paired with the RD-8 vernier engine. The engine was developed from 1976 to 1985 by NPO Energomash with V.P. Radovsky leading the development. It is manufactured by, among others, Yuzhmash in Ukraine.
This page is an incomplete list of orbital rocket engine data and specifications.
The RD-0214 (Russian: Ракетный Двигатель-0214 [РД-0214], romanized: Raketnyy Dvigatel-0214, lit. 'Rocket Engine 0214', GRAU index: 8D811) is a vernier thruster rocket engine burning unsymmetrical dimethylhydrazine (UDMH) fuel with dinitrogen tetroxide (N2O4) oxidizer in a gas-generator cycle. It has four nozzles that can each gimbal 45 degrees in plane to provide thrust vectoring control to the RD-0212 propulsion module of Proton rocket's third stage. It is a revised version of the RD-0207 (Russian: РД-0214, GRAU index: 8D67).
The RD-0210 (Russian: Ракетный Двигатель-0210, romanized: Raketnyy Dvigatel-0210, lit. 'Rocket Engine 0210', GRAU index: 8D411K) is also known as the RD-465. It and its twin, the RD-0211, are rocket engines using unsymmetrical dimethylhydrazine (UDMH) as fuel and dinitrogen tetroxide (N2O4) as oxidizer in an oxidizer rich staged combustion cycle. They have a single nozzle, possess thrust vectoring and are the latest evolution in the RD-0203/4 lineage. They are the engines used on the Proton second stage. The RD-0213 is a fixed nozzle variation that is used on the RD-0212 module of the Proton third stage.
The RD-0216 (Russian: Ракетный Двигатель-0216, romanized: Raketnyy Dvigatel-0216, lit. 'Rocket Engine 0216') and RD-0217 are liquid rocket engines, burning N2O4 and UDMH in the oxidizer rich staged combustion cycle. The only difference between the RD-0216 and the RD-0217 is that the latter doesn't have a heat exchanger to heat the pressuring gasses for the tanks. Three RD-0216 and one RD-0217 were used on the first stage of the UR-100 ICBM. The engines were manufactured until 1974 and stayed in operational use until 1991. More than 1100 engines were produced.
The RD-0233 and RD-0234 are liquid-fueled rocket engines which burn a hypergolic mixture of unsymmetrical dimethylhydrazine (UDMH) fuel with dinitrogen tetroxide oxidizer in an oxidizer-rich staged combustion cycle. The only difference between the RD-0233 and the RD-0234 is that the latter has a heat exchanger to heat the pressuring gasses for the tanks. Three RD-0233 and one RD-0234 are used on the first stage of the UR-100UTTKh ICBM. While the engine is out of production, the ICBM as well as Rokot and Strela remain operational as of 2015.
The RD-0236 is a vernier thruster engine for liquid-fueled rockets. It burns a hypergolic mixture of unsymmetrical dimethylhydrazine (UDMH) fuel with dinitrogen tetroxide oxidizer in a gas generator cycle. It is used along the RD-0235 main engine on the UTTKh second stage, which was featured in the UR-100N ICBM as well as the Strela and Rokot launch vehicles derived from it. Its function is to supply thrust vector control by gimbaling each of its four nozzles in a plane. While the engine is out of production, the ICBM as well as Strela remain operational as of 2015. The Rokot launch vehicle conducted its final launch before retirement in December 2019.
The RD-0237 is a vernier thruster engine used on liquid-fueled rockets burning a hypergolic mixture of unsymmetrical dimethylhydrazine (UDMH) fuel with dinitrogen tetroxide oxidizer, pressure-fed to the engine. It is used on the UR-100UTTKh MIRV vehicle to supply thrust vector control by gimbaling of its nozzle. While the engine is out of production, the ICBM and Strela remain operational as of 2015.
The RD-263 is a liquid-fuel rocket engine, burning a hypergolic mixture of unsymmetrical dimethylhydrazine (UDMH) fuel with dinitrogen tetroxide oxidizer in the oxidizer rich staged combustion cycle. Four RD-263 engines form a propulsion module RD-264. For the R-36M KB Yuzhnoye only ordered the first stage propulsion to Energomash, instead of both stages, arguing that they were overworked with the RD-270 development. By April 1970 Yuzhnoye was getting the engine documentation. By the end of 1972 Energomash started to test fire the engines in its own test stand. And by September 1973 the engine was certified for flight. While the engine is out of production, the ICBM as well as the Dnepr remain operational as of 2015.
The RD-119 was a liquid rocket engine, burning liquid oxygen and UDMH in the gas-generator cycle. It has a huge expansion ratio on the nozzle and uses a unique propellant combination to achieve an extremely high isp of 352 s for a semi-cryogenic gas-generator engine. It also has a unique steering mechanism. The engine main nozzle is fixed, and the output of the gas generator is fed into four nozzles on the side of the engine. Instead of using gimbaled verniers to supply vector control, the combustion gases are distributed by an electrically driven system that can control the thrust among the nozzles.
The RD-214 (GRAU Index 8D59) was a liquid rocket engine, burning AK-27I (a mixture of 73% nitric acid and 27% N2O4 + iodine passivant and TM-185 (a kerosene and gasoline mix) in the gas generator cycle. As was the case with many V-2 influenced engines, the single turbine was driven by steam generated by catalytic decomposition of hydrogen peroxide. It also had four combustion chambers and vector control was achieved by refractory vanes protruding into the nozzle's exhaust.
The RD-250 is the base version of a dual-nozzle family of liquid-fuel rocket engines, burning a hypergolic mixture of unsymmetrical dimethylhydrazine (UDMH) fuel with dinitrogen tetroxide oxidizer in an gas-generator open cycle. The RD-250 was developed by OKB-456 for Yangel's PA Yuzhmash ICBM, the R-36 (8K67). Its variations were also used on the Tsyklon-2 and Tsyklon-3 launch vehicles. It was supposed to be used on the Tsyklon-4, but since the cancellation of the project it should be considered as out of production.
The RD-856, also known as the RD-69M, is a four-nozzle liquid-fuel rocket vernier engine, burning a hypergolic mixture of unsymmetrical dimethylhydrazine (UDMH) fuel with dinitrogen tetroxide oxidizer in a gas generator cycle. It was used on the R-36, Tsyklon-2 and Tsyklon-3 second stage as thrust vector control by gimbaling of its nozzle. The engine is distributed through a cylindrical structure that is integrated around the main engine RD-252 module. The structure includes aerodynamic protection for the nozzles. The engine was started by a pyrotechnic ignitor.
