RD-0214

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]

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 had 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 4.1m 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 tests firings were performed. Yet, even as of 2015 design issues where 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 which was sent the first pictured from the surface of Venus.^[11]

Versions

There are two basic versions of this engine:

• RD-0207 (GRAU Index: 8D67): A small gas generator rocket vernier engine using the same propellants as the RD-0206 and bundled with it in the RD-0205 propulsion module. It has four combustion chambers that can gimbal 45 degrees in a single plane and allow the UR-200 second stage to have vector control.^[5]
• RD-0214 (GRAU Index: 8D811): An evolution of the RD-0207 engine, used as vernier engine of the RD-0212 propulsion module along the RD-0213. It has four combustion chambers that can gimbal 45 degrees in a single plane and allow the Proton third stage to have vector control.^[12]

Modules

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

• RD-0205 (GRAU Index: 8D46): A module comprising an RD-0206 and an RD-0207 vernier engine. Propulsion of the UR-200 second stage.^[13]
• RD-0212 (GRAU Index: 8D49): Also known as the RD-473, it is a propulsion module comprising one RD-0213 and an RD-0214 vernier engine. Propulsion module of the third stage of the Proton rockets.^[14]

See also

• RD-0206 - Companion of the RD-0207.
• RD-0213 - Companion of the RD-0214.
• Proton - uses RD-0214.
• UR-200 - Used the RD-0207.
• KBKhA - The RD-0207 and RD-0214 design bureau.
• Voronezh Mechanical Plant - A space hardware manufacturing company that makes the RD-0214.
• Vernier Engine
• Rocket engine

References

External links

• KbKhA Home Page
• Voronezh Mechanical Plant
• Khrunichev State Research and Production Space Center

Rocket engines and solid motors for orbital launch vehicles
See also: Comparison of orbital rocket engines
Liquid fuel	Cryogenic (LH2 / LOX) China YF-73 YF-75 YF-75D YF-77 Europe HM7B Vinci Vulcain India CE-7.5 CE-20 Japan LE-5 LE-7 Russia KVD-1 (RD-56) RD-0120 USA BE-3U J-2 RL10 RS-25 (SSME) RS-68 Cryogenic (CH4 / LOX) USA BE-4 Raptor Semi-cryogenic (RP-1 / LOX) China YF-100 YF-115 India SCE-200 New Zealand Rutherford Russia NK-33 RD-58 RD-0105, 0109 RD-0107, 0108, 0110 RD-0110R RD-0124 RD-107, 108, 117, 118 RD-120 RD-170, 171 RD-180 RD-191, 151, 181 RD-193 S1.5400 Ukraine RD-8 RD-801 RD-810 USA F-1 H-1 Kestrel LR-79 LR-89 LR-105 Merlin 1 RS-27 RS-27A RS-56 S-3D XLR50 Hypergolic (UDMH, UH 25, Aerozine or MMH reacting with N2O4) China YF-1, 2, 3 YF-20, 21, 22, 24, 25 YF-23 YF-40 YF-50D Europe Aestus Astris Vexin Viking India PS4 Vikas Israel LK-4 Russia 17D61 RD-0202 to 0206, 0208 to 0213 RD-0207, 0214 RD-0216, 0217, 0235 RD-0233, 0234 RD-0236 RD-0237 RD-0243, 0244, 0245 RD-0255, 0256, 0257 RD-250, 251, 252, 261, 262 RD-253, 275 RD-263, 268, 273 RD-270 RD-854, 861 RD-855 RD-856 RD-864, 869 S5.92 S5.98M Ukraine RD-843 USA AJ10 LR-87 LR-91 TR-201 Hypergolic (other oxidizers) Europe Gamma Russia RD-119 RD-214 USA XLR81
Solid fuel	China FG-02 FG-36 FG-46 FG-47 SpaB-65 SpaB-140C Europe Mage 1 P-4 P-6 PAP P80 P230 Topaze Waxwing Zefiro 9 Zefiro 23 India S7 S9 S12 S139 S200 Israel LK-1 RSA-3 Japan KM-V1 KM-V2b M-14 M-24 M-34 M-34c SRB-A USA AJ-60A Algol Castor 30 GEM Orbus-6 Orbus-21 Orion Space Shuttle SRB Star 27 Star 37 Star 48 UA120 USRM X-248 X-254
Engines under development are in italics.