RD-214

Last updated
RD-214 (РД-214)
RD-214 rocket engine.jpg
Museum of Space and Missile Technology (Saint Petersburg). RD-214 rocket engine for Cosmos LV first stage.
Country of origin USSR
Date1955-1959
Designer Energomash, V.Glushko
Manufacturer Plant No. 19 named after I. V. Stalin
Associated LV R-12 and Kosmos-2
StatusRetired
Liquid-fuel engine
Propellant AK-27I / TM-185
Mixture ratio3.97
Cycle Gas Generator
Configuration
Chamber4
Nozzle ratio9.42
Performance
Thrust, vacuum730.2 kilonewtons (164,200 lbf)
Thrust, sea-level635.2 kilonewtons (142,800 lbf)
Chamber pressure 4.36 megapascals (632 psi)
Specific impulse, vacuum264 s (2.59 km/s)
Specific impulse, sea-level230 s (2.3 km/s)
Burn time140 s
Dimensions
Length2,380 millimetres (94 in)
Diameter1,480 millimetres (58 in)
Dry weight655 kilograms (1,444 lb)
Used in
R-12 and Kosmos-2
References
References [1] [2]

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. [2] [3] 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. [4]

Contents

Development

For the requirements to have storable propellants and higher thrust, Glushko's OKB-456 developed the RD-211, which had four combustion chambers, each having twice the thrust of the RD-100, a Russian adaptation of the V-2 A-4 engine. [5] The four chambers were fed from a single turbopump powered by steam generated from catalytic decomposition of H2O2. [6] When then came the requirement for the Buran cruise missile project, a version for that application was developed in the RD-212. [7] Both RD-211 and RD-212 proved too weak for the application and the project were abandoned for the RD-213 for Buran. [8] When Yangel's OKB-586 was tasked with developing the first storable propellant ballistic missile in the Soviet arsenal, the RD-211 proved too weak. Thus, the project was definitely abandoned and the more powerful RD-214 was developed. [2] While Korolev's refusal to use toxic propellants basically left him out of the ballistic missile development race, the basic design of the RD-211 also served as basis for the RD-107/RD-108 engine, which went to be the most flown rocket engines in history. [5]

The initial R-12 was a pad launched missile. It had significant operative issues on readiness and vulnerability. Thus, the silo launched R-12U was developed. For this development the RD-214U was developed. When Yangel used the R-12U as the basis for the Kosmos-2 63S1, the RD-214F was developed and fire tested, but in the end the stock R-12U was used as first stage. So it was for all subsequent 63S1M and 11K63. [1] [5] [9]

Versions

This engine many versions:

RD-214 Family of Engines [1]
EngineRD-211RD-212RD-213RD-214RD-214URD-214F
AKA8D578D418D138D598D59U11D45
Development1953-19551954-19561956-19571955-19591959-19601960-1962
Engine type Gas generator [2]
PropellantAK-27I (73% nitric acid, 27% N2O4, and iodine passivant) / TM-185 (a kerosene and gasoline mix) [2]
Combustion chamber pressure3.923 megapascals (569.0 psi)3.923 megapascals (569.0 psi)4.66 megapascals (676 psi)4.36 megapascals (632 psi)4.36 megapascals (632 psi)4.38 megapascals (635 psi)
Thrust, vacuum642.3 kilonewtons (144,400 lbf)622.7 kilonewtons (140,000 lbf)749.2 kilonewtons (168,400 lbf)730.2 kilonewtons (164,200 lbf)730.6 kilonewtons (164,200 lbf)729.6 kilonewtons (164,000 lbf)
Thrust, sea level549.2 kilonewtons (123,500 lbf)559 kilonewtons (126,000 lbf)686.5 kilonewtons (154,300 lbf)635.2 kilonewtons (142,800 lbf)635.5 kilonewtons (142,900 lbf)635.5 kilonewtons (142,900 lbf)
Isp, vacuum253 s (2.48 km/s)254 s (2.49 km/s)264 s (2.59 km/s)264 s (2.59 km/s)264 s (2.59 km/s)264 s (2.59 km/s)
Isp, sea level224 s (2.20 km/s)227 s (2.23 km/s)231 s (2.27 km/s)230 s (2.3 km/s)230 s (2.3 km/s)230 s (2.3 km/s)
Burn time122s100s110s140s
Length2,700 millimetres (110 in)2,500 millimetres (98 in)2,500 millimetres (98 in)2,380 millimetres (94 in)2,380 millimetres (94 in)2,380 millimetres (94 in)
Diameter1,650 millimetres (65 in)1,480 millimetres (58 in)1,480 millimetres (58 in)1,500 millimetres (59 in)1,480 millimetres (58 in)1,480 millimetres (58 in)
Dry weight635 kilograms (1,400 lb)642 kilograms (1,415 lb)625 kilograms (1,378 lb)655 kilograms (1,444 lb)655 kilograms (1,444 lb)655 kilograms (1,444 lb)
Use R-12 (8K63) Project Buran Project Buran Project R-12 (8K63) R-12U (8K63S)
Kosmos-2 (11K63)
Project for Kosmos-2 (63S1)

See also

Related Research Articles

<span class="mw-page-title-main">R-12 Dvina</span> Medium-range ballistic missile

The R-12 Dvina was a theatre ballistic missile developed and deployed by the Soviet Union during the Cold War. Its GRAU designation was 8K63, and it was given the NATO reporting name of SS-4 Sandal. The R-12 rocket provided the Soviet Union with the capability to attack targets at medium ranges with a megaton-class thermonuclear warhead and constituted the bulk of the Soviet offensive missile threat to Western Europe. Deployments of the R-12 missile in Cuba caused the Cuban Missile Crisis in 1962. A total of 2335 missiles were produced; all were destroyed in 1993 under the START II treaty.

<span class="mw-page-title-main">RD-170</span> Soviet (now Russian) rocket engine, the most powerful in the world

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 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.

<span class="mw-page-title-main">NK-33</span> Soviet rocket engine

The NK-33 and NK-43 are rocket engines designed and built in the late 1960s and early 1970s by the Kuznetsov Design Bureau. The NK designation is derived from the initials of chief designer Nikolay Kuznetsov. The NK-33 was among the most powerful LOX/RP-1 rocket engines when it was built, with a high specific impulse and low structural mass. They were intended for the ill-fated Soviet N1F moon rocket, which was an upgraded version of the N1. The NK-33A rocket engine is now used on the first stage of the Soyuz-2-1v launch vehicle. When the supply of the NK-33 engines are exhausted, Russia will supply the new RD-193 rocket engine. It used to be the first stage engines of the Antares 100 rocket series, although those engines are rebranded the AJ-26 and the newer Antares 200 and Antares 200+ rocket series uses the RD-181 for the first stage engines, which is a modified RD-191, but shares some properties like a single combustion chamber unlike the two combustion chambers used in the RD-180 of the Atlas V and the four combustion chambers used in the RD-170 of the Energia and Zenit rocket families, and the RD-107, RD-108, RD-117, and RD-118 rocket engines used on all of the variants of the Soyuz rocket.

The RD-8 is a Soviet / Ukrainian liquid propellant rocket engine burning LOX and RG-1 in an oxidizer rich staged combustion cycle. It has a four combustion chambers that provide thrust vector control by gimbaling each of the nozzles in a single axis ±33°. It was designed in Dnipropetrovsk by the Yuzhnoye Design Bureau as the vernier thruster of the Zenit second stage. As such, it has always been paired with the RD-120 engine for main propulsion.

<span class="mw-page-title-main">RD-58</span>

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 N-1 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 N-1's roll-control engine.

<span class="mw-page-title-main">NPO Energomash</span> Russian rocket engine manufacturer

NPO Energomash “V. P. Glushko” is a major Russian rocket engine manufacturer. The company primarily develops and produces liquid propellant rocket engines. Energomash originates from the Soviet design bureau OKB-456, which was founded in 1946. NPO Energomash acquired its current name on May 15, 1991, in honor of its former chief designer Valentin Glushko.

<span class="mw-page-title-main">RD-107</span> Russian rocket engine

The RD-107 and its sibling, the RD-108, are a type of rocket engine initially used to launch R-7 Semyorka missiles. RD-107 engines were later used on space launch vehicles based on the R-7. As of 2021, very similar RD-107A and RD-108A engines are used to launch the Soyuz-2.1a, and Soyuz-2.1b, which are in active service.

<span class="mw-page-title-main">RD-253</span> Soviet engine design used on the first stage of Proton rockets

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-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 has been 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.

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.

<span class="mw-page-title-main">RD-0210</span>

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 not 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-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.

<span class="mw-page-title-main">RD-119</span>

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.

<span class="mw-page-title-main">RD-250</span> Rocket engine

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.

<span class="mw-page-title-main">RD-215</span> Rocket engine

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-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.

References

  1. 1 2 3 4 5 6 7 8 9 "NPO Energomash list of engines". NPO Energomash. Retrieved 2015-06-26.
  2. 1 2 3 4 5 "RD-214". Encyclopedia Astronautica. Archived from the original on 2015-08-24. Retrieved 2015-06-26.
  3. "Nitric acid/Kerosene". Encyclopedia Astronautica. Archived from the original on 2016-03-13. Retrieved 2015-06-26.
  4. "Soviet rocket's engines (NPO Energomash)". Buran-Energia.com. Retrieved 2015-06-27.
  5. 1 2 3 "R-12". Encyclopedia Astronautica. Archived from the original on March 5, 2002. Retrieved 2015-06-26.
  6. 1 2 "RD-211". Encyclopedia Astronautica. Archived from the original on January 8, 2002. Retrieved 2015-06-26.
  7. 1 2 "RD-212". Encyclopedia Astronautica. Archived from the original on January 8, 2002. Retrieved 2015-06-26.
  8. 1 2 "RD-213". Encyclopedia Astronautica. Archived from the original on May 5, 2002. Retrieved 2015-06-26.
  9. Zak, Anatoly. "Kosmos-2". RussianSpaceWeb.com. Retrieved 2015-06-26.