RD-0214

Last updated
RD-0214 (РД-0214)
Country of origin USSR
First flightRD-0207:1963-11-06 [1]
RD-0214:1967-03-10 [2]
Designer OKB-154, Yankel I. Guerchkovitch [2] [3] [4]
Manufacturer Voronezh Mechanical Plant
Application Vernier Engine
PredecessorRD-0207
StatusIn Production
Liquid-fuel engine
Propellant N2O4 [2] / UDMH [2]
Mixture ratio2.54 [4]
Cycle Gas Generator [2]
Configuration
Chamber4
Performance
Thrust, vacuum30.9 kilonewtons (6,900 lbf) [2]
Chamber pressure 5.3 megapascals (770 psi) [2]
Specific impulse, vacuumRD-0207:297seconds [5]
RD-0214:293 seconds [2]
Burn timeRD-0207:133seconds [5]
RD-0214:270s [2]
Dimensions
Length524 millimetres (20.6 in) [4]
Diameter3,780 millimetres (149 in) [4]
Dry weight90 kilograms (200 lb) [2]
Used in
Proton third stage

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. [4]

Contents

Development

When Chelomey's OKB-52 started their UR-200 ICBM project, they requested S. A. Kosberg's OKB-154 to develop the propulsion. For the second stage, they used a single RD-0206, a variation of the first stage RD-0203, but required a vernier engine. To this end, the RD-0207 vernier engine was designed. It also included a heat exchanger to heat the pressurant gases for the second stage tank. [4] [6] [7] While the UR-200 project was in direct competition to the R-36 and was cancelled in favor of the latter, it did have a few test launches and thus was a proven design. [4] [6] [7]

Then Chelomey moved his proposals to the super heavy ICBM UR-500 (8K82) and later to the Proton-K (8K82K). A heavy launch vehicle that could perform important missions for the Soviet moonshot. For this new missions, it would not need to comply with ICBM specification standards, but would need at least a third stage. For the third stage, the UR-200 second stage was adapted—with the same 4.1 m tanking as the first and second stages and the RD-0205 module with an RD-0206 and an RD-0207 vernier engine was given an overhaul. The new module—known as RD-0212—consisted of an RD-0213 and an RD-0214 vernier engine. Many reliability enhancements were done and much extra test firings were performed. Yet, even as of 2015 design issues were found to have caused failures. [4] [8] [9] [10]

History

The first launch test of the UR-200 was on November 5, 1963, and was unsuccessful. The second vehicle, launched on April 11, 1964, also failed. The final RD-0207 flight was on October 20, 1964.

The first RD-0214 flight was on October 3, 1967.

On September 15, 1968, the RD-0214 module launched the Zond 5 around the Moon on a free return trajectory, that sent the first alive organisms around the moon and back to Earth. [11]

On 19 May 1971 a Proton launched the Mars 2 probe to Mars. The orbiter was identical to the Venera 9 bus, and the lander was the first man-made object to reach the surface of Mars. [11]

On 8 June 1975 a Proton launched the Venera 9 to Venus. It consisted of an orbiter based on the Mars 2 design, and a lander that sent the first pictures from the surface of Venus. [11]

Versions

There are two basic versions of this engine:

Modules

These engines are actually bundled into modules. The relevant modules and auxiliary engines are:

See also

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

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<span class="mw-page-title-main">RD-0110</span> Soviet (later Russian) rocket engine

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<span class="mw-page-title-main">RD-0110R</span>

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

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The RD-0243 is a propulsion module composed of an RD-0244 main engine and a RD-0245 vernier engine. Both are liquid rocket engine, burning N2O4 and UDMH. The RD-0244 main engine operates in the oxidizer rich staged combustion cycle, while the vernier RD-0245 uses the simpler gas generator cycle. Since volume is at a premium on submarine launches, this module is submerged on the propellant tank. Its development period was from 1977 to 1985, having had its first launch on December 27, 1981. Originally developed for the RSM-54, it was used later for the Shtil'.

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.

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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 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.

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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>

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

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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.

References

  1. ↑ "RD-0203, RD-0204, RD-0205, RD-0206, RD-0207. Intercontinental ballistic missile UR-200". KBKhA. Archived from the original on 5 May 2014.
  2. 1 2 3 4 5 6 7 8 9 10 "RD0208, RD0209 Launch Vehicle Proton (8K82H-4 two stages). RD0210, RD0211, RD0212 (RD0213, RD0214) Launch Vehicle Proton (8K82K, 8K82KM three stages)". KBKhA. Archived from the original on 15 August 2015.
  3. ↑ Pillet, Nicolas. "Le troisième étage du lanceur Proton" (in French). Kosmonavtika.com. Retrieved 2015-06-08.
  4. 1 2 3 4 5 6 7 8 Zak, Anatoly. "RD-0212 engine". www.russianspaceweb.com. Retrieved 2015-06-08.
  5. 1 2 3 "RD-0207". Encyclopedia Astronautica. Archived from the original on June 25, 2002. Retrieved 2015-06-08.
  6. 1 2 Zak, Anatoly. "UR-200 / 8K81 / SS-X-10". www.russianspaceweb.com. Retrieved 2015-06-08.
  7. 1 2 "UR-200". Encyclopedia Astronautica. Archived from the original on May 2, 2002. Retrieved 2015-06-08.
  8. ↑ Zak, Anatoly. "Birth of Proton: The Iconic Rocket That Almost Wasn't". www.russianspaceweb.com. Retrieved 2015-06-08.
  9. ↑ Zak, Anatoly. "Proton's second stage". www.russianspaceweb.com. Retrieved 2015-06-08.
  10. ↑ Zak, Anatoly. "Proton's third stage". www.russianspaceweb.com. Retrieved 2015-06-08.
  11. 1 2 3 "KBKHA LIQUID ROCKET ENGINES, WHICH ENSURED THE SUCCESSFUL REALIZATION OF THE ADVANCED SPACE PROGRAMS (FOR THE FIRST TIME IN THE WORLD)". KBKhA. Archived from the original on 15 August 2015.
  12. ↑ "RD-0214". Encyclopedia Astronautica. Archived from the original on June 25, 2002. Retrieved 2015-06-08.
  13. ↑ "RD-0205". Encyclopedia Astronautica. Archived from the original on August 26, 2002. Retrieved 2015-06-08.
  14. ↑ "RD-0212". Encyclopedia Astronautica. Archived from the original on June 2, 2002. Retrieved 2015-06-08.
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