See also
- UR-100N - ICBM for which this engine was originally developed for.
- Rokot - launch vehicle that is a repurposed UR-100N.
- Strela - launch vehicle that is a repurposed UR-100N.
- Rocket engine using liquid fuel
| Country of origin | USSR |
|---|---|
| First flight | 1973-04-09 [1] |
| Designer | OKB-154 [1] |
| Associated L/V | UR-100N, Rokot and Strela [1] |
| Status | Out of Production |
| Liquid-fuel engine | |
| Propellant | N2O4 [1] / UDMH [1] |
| Cycle | Oxidizer Rich Staged Combustion [1] |
| Configuration | |
| Chamber | 1 [2] |
| Performance | |
| Thrust | 520 kilonewtons (120,000 lbf) [2] |
| Chamber pressure | 20.5 megapascals (2,970 psi) [2] |
| Isp (vac.) | 310 s (3.0 km/s) [2] |
| Isp (SL) | 285 s (2.79 km/s) [2] |
| Burn time | 121 seconds [2] |
| Used in | |
| UR-100N core stage [2] | |
The RD-0233 (GRAU Index 15D95) and RD-0234 (GRAU Index 15D96) are liquid rocket engines, burning N2O4 and UDMH in the oxidizer rich staged combustion cycle. [3] [1] [2] 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. [4] Three RD-0233 and one RD-0234 are used on the first stage of the UR-100UTTKh ICBM. [5] While the engine is out of production, the ICBM as well as Rokot and Strela remain operational as of 2015. [5]
The UR-100 was an intercontinental ballistic missile (ICBM) developed and deployed by the Soviet Union from 1966 to 1996. UR (УР) in its designation stood for Universal Rocket. It was known during the Cold War by the NATO reporting name SS-11 Sego and internally by the GRAU index 8K84. The Strela and Rokot carrier rockets are based on it.
The UR-100N, also known as RS-18A is an intercontinental ballistic missile in service with Soviet and Russian Strategic Missile Troops. The missile was given the NATO reporting name SS-19 Stiletto and carries the industry designation 15A30.
Rokot, also transliterated Rockot, was a Russian space launch vehicle that was capable of launching a payload of 1,950 kilograms into a 200 kilometre Earth orbit with 63° inclination. It was based on the UR-100N intercontinental ballistic missile (ICBM), supplied and operated by Khrunichev State Research and Production Space Center. The first launches started in the 1990s from Baikonur Cosmodrome out of a silo. Later commercial launches commenced from Plesetsk Cosmodrome using a launch ramp specially rebuilt from one for the Kosmos-3M rocket. The cost of the launcher itself was about $15 million in 1999; The contract with ESA for launching Swarm in September 2013 was worth €27.1 million.
The UR-200 was an intercontinental ballistic missile (ICBM) developed by Vladimir Chelomey's OKB-52 in the Soviet Union. It was known during the Cold War by the NATO reporting name SS-10 Scrag and internally by the GRAU index 8K81. The design was authorized by the Decisions of the Central Committee of the CPSU of March 16 and August 1, 1961, and the draft project was finished in July 1962. It first flew on November 4, 1963 from the Baikonur Cosmodrome. The ninth and final flight was conducted on October 20, 1964.
Strela is a Russian orbital carrier rocket, derived from the Soviet/Russian UR-100NU missile. It conducted its maiden test launch on 5 December 2003, carried its first functional payload on 27 June 2013, and a second one on 19 December 2014.
The Universal Rocket or UR family of missiles and carrier rockets is a Russian, previously Soviet rocket family. Intended to allow the same technology to be used in all Soviet rockets, the UR is produced by the Khrunichev State Research and Production Space Center. Several variants were originally planned, of which only three flew, and only two of which entered service. In addition, the cancelled UR-500 ICBM formed the basis for the Proton carrier rocket.
The RD-253 ( Russian: Раке́тный дви́гатель 253, Rocket Engine 253) and its later variants, the RD-275and 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 UDMH/N2O4, which are highly toxic but hypergolic and storable at room temperature, simplifying the engine's design.
The RD-0214 (GRAU Index: 8D811) is a rocket vernier engine burning N2O4 and UDMH in a gas generator cycle. It has four nozzles that can each gimbal 45 in plane to provide TVC to the RD-0212 propulsion module of Proton third stage. It is a revised version of the RD-0207.
The RD-0210 (GRAU Index: 8D411K) is also known as the RD-465. It and its twin, the RD-0211, are rocket engines burning N2O4 and UDMH in an oxidizer rich staged combustion cycle. They have single nozzle, possess TVC 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 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 has 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-0236 (GRAU Index 15D114) is a liquid rocket vernier engine, burning N2O4 and UDMH in the gas generator cycle. It is used along the RD-0235 main engine on the UR-100UTTKh second stage. 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 Rokot and Strela remain operational as of 2015.
The RD-0237 (GRAU Index 15D114) is a pressure-fed liquid rocket vernier engine, burning N2O4 and UDMH. 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 (GRAU Index 15D117) is a liquid rocket engine, burning N2O4 and UDMH in the oxidizer rich staged combustion cycle. Four RD-263 engines form a propulsion module RD-264 (GRAU Index 15D119). 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 H2O2. It also had four combustion chambers and vector control was achieved by refractory vanes protruding into the nozzle's exhaust.
The RD-250 (GRAU Index 8D518) is the base version of a dual-nozzle family of liquid rocket engines, burning N2O4 and UDMH in the oxidizer rich staged combustion 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-215 (GRAU Index 8D513) was a dual nozzle liquid rocket engine, burning AK-27 (a mixture of 73% nitric acid and 27% N2O4 + iodine passivant) and UDMH. It was used in a module of two engines (four nozzles) known as the RD-216 (GRAU Index 8D514). The RD-215 was developed by OKB-456 for Yangel's Yuzhmash R-14 (8K65) ballistic missile. Its variations were also used on the Kosmos-1, Kosmos-3 and Kosmos-3M launch vehicles.
The RD-861 is a Soviet liquid propellant rocket engine burning UDMH and nitrogen tetroxide in a gas generator combustion cycle. It has a main combustion chamber, with four vernier nozzles fed by the gas generator output. It can be reignited a single time.
The RD-0255 is a propulsion module composed of an RD-0256 main engine and a RD-0257 vernier engine. Both are liquid rocket engine, burning UDMH in N2O4. The RD-0256 main engine operates in the oxidizer rich staged combustion cycle, while the vernier RD-0257 uses the simpler gas generator cycle. It was used on the R-36MUTTKh (GRAU:15A18) and R-36M2 (GRAU:15A18M). Subsequently, it has been in the Dnepr second stage and as of 2016 it is still in active service.
The RD-864 is a Soviet liquid propellant rocket engine burning UDMH and nitrogen tetroxide in a gas generator combustion cycle. It has a four combustion chambers that provide thrust vector control by gimbaling each nozzle in a single axis +/- 55°. It is used on the third stage of the R-36M UTTKh and Dnepr. For the R-36M2, an improved version, the RD-869 was developed.
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