RD-0210

RD-0210 (РД-0210)
Country of origin USSR/Russia
First flight 1967-03-10[1]
Designer OKB-154, Yankel I. Guerchkovitch[1][2][3]
Manufacturer Voronezh Mechanical Plant[4]
Application Upper Stage
Associated L/V Proton
Predecessor RD-0208[1]
Status In Production
Liquid-fuel engine
Propellant N2O4[1] / UDMH[1]
Mixture ratio 2.6
Cycle Oxidizer Rich Staged combustion[1]
Configuration
Chamber 1
Performance
Thrust (vac.) 582 kN (131,000 lbf)[1]
Chamber pressure 14.7 MPa (2,130 psi)[1]
Isp (vac.) 326.5s[1]
Burn time 220s[1]
Dimensions
Length 2,327 mm (91.6 in)[1]
Diameter 1,470 mm (58 in)[1]
Dry weight 566 kg (1,248 lb)[1]
Used in
UR-200 and UR-500 and Proton second stage

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 a 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.

Development

When Chelomey's OKB-52 started their UR-200 ICBM project, they requested S. A. Kosberg's OKB-154 to develop the propulsion. They decided to use the same basic block for both the first and second stage. But to achieve the required performance, Kosberg had to develop a staged combustion engine, a then extremely aggressive feat. Only M. V. Melnikov of OKB-1 had designed a staged combustion engine before, the S1.5400, and it used a different propellant mix with significant less thrust.[3][5]

To simplify design and manufacture, the engine would be used both on the first and the second stages. The first stage would use a module - the RD-0202 - that comprised three RD-0203 and one RD-0204, while the upper stage would use a RD-0205 module comprising a RD-0206 main engine plus an auxiliary vernier engine, the RD-0207. The RD-0204 only difference to the RD-0203 was that it included a heat exchanger to heat the pressurant gases for the fist stage tank. The RD-0206 was very similar to the RD-0204, but its nozzle was vacuum optimized and had a fixed nozzle. The thrust vector control task was delegated to the four nozzle RD-0207 vernier engine. 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.[3][5][6]

When Chelomey started his super heavy ICBM UR-500 (8K82) project, he originally intended to use multiple UR-200 modules as a first stage. When this concept proved not viable, and the multi-body that was finally used was settled on, they had to search for new propulsion on the first stage. For the second stage, they adapted the UR-200 first stage's. It needed new tanks to match the first stage, but most of the rest could be adapted. The engines had to be started in the air and had to get longer nozzles, optimized for vacuum operation. Both of this features were demonstrated on the RD-0206, and were readily adapted. They also received a thrust vector gimbaling system, to have better control during launch. Thus, the RD-0208/RD-0209 were born. In a parallel case with the RD-0203/4, the RD-0209 was a version of the RD-0208 that included a heat exchanger.[7][8]

When the UR-500 proved to be too big as an ICBM, the application of the vehicle as a weapon was cancelled. But it could be adapted as a heavy launch vehicle that could perform important missions for the Soviet moonshot, and so the Proton-K (8K82) was born. This allowed Chelomey to pitch it as a competitor, along the UR-700 project, of Korolev's N-1. For this new missions, it would not need to comply with ICBM specification standards, but would need at least a third stage. The second stage was enlarged, and the RD-0208/9 were revised as the RD-0210 and RD-0211 by uprating them slightly and significantly increasing the burning time. For the third stage, the UR-200 second stage was adapted -again, 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. The RD-0213 was a RD-0206 brought to RD-0211/12 standards, and the RD-0214 was a revised RD-0207.[7][9][10]

History

The RD-0203/4 was the second staged combustion engine in the world, only after the S1.5400, and was also the first staged combustion engine with storable propellants.[11]

On 15 September 1968 the RD-0210, RD-0211 and the RD-0212 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 April 1971 a Proton orbited Salyut 1 the first space station to orbit the 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]

On 20 November 1998 a Proton launched Zarya the first module of the ISS.[11]

On 12 July 2000 a Proton launched Zvezda, the third module launched of the ISS and the center of the Russian portion of the station - the Russian Orbital Segment.[11]

Versions

The basic engine has been used for the UR-200 first and second stages, the UR-500 second stage and the Proton second and third stages. Each variation is as follows:

Modules

Some of these engines were bundled into modules of multiple engines. The relevant modules and auxiliary engines are:

RD-0210 Family of Engines
Engine RD-0203 RD-0204 RD-0206 RD-0208 RD-0209 RD-0210 RD-0211 RD-0213
AKA 8D44 8D44 8D47 8D411 8D412 8D411K 8D412K 8D48
Propulsion Module RD-0202 RD-0205
(with RD-0207) 		RD-0212
(with RD-0214)
Development 1961-1964 1961-1964 1961-1964 1962-1966 1962-1966 1962-1967 1962-1967 1962-1967
Engine Type Liquid oxidizer rich staged combustion using N2O4/UDMH propellant with an O/F ratio of 2.6
Combustion Chamber Pressure 14.7 MPa (2,130 psi)
Nozzle Single nozzle
(Fixed) 		Single nozzle
 Single nozzle
(Fixed) 		Single nozzle
with TVC 		Single nozzle
with TVC 		Single nozzle
with TVC 		Single nozzle
with TVC 		Single nozzle
(Fixed)
Thrust (Vacuum) 559 kN (126,000 lbf) 559 kN (126,000 lbf) 575.5 kN (129,400 lbf) 570 kN (130,000 lbf) 570 kN (130,000 lbf) 582 kN (131,000 lbf) 582 kN (131,000 lbf) 582 kN (131,000 lbf)
Thrust (Sea Level) 500 kN (110,000 lbf) 500 kN (110,000 lbf)
Isp (Vacuum) 311s 311s 326s 326s 326s 326.5s 326.5s 326.5s
Isp(Sea Level) 278s 278s
Burn Time 136s 136s 150s 150s 150s 220s 220s 250s
Length 1.8 m (71 in) 1.8 m (71 in) 2,327 mm (91.6 in) 2,327 mm (91.6 in) 2,327 mm (91.6 in) 2,327 mm (91.6 in) 3,008 mm (118.4 in)
Width 890 mm (35 in) 890 mm (35 in) 1,470 mm (58 in) 1,470 mm (58 in) 1,470 mm (58 in) 1,470 mm (58 in) 1,470 mm (58 in) 1,470 mm (58 in)
Dry Weight 381 kilograms (840 lb) 381 kilograms (840 lb) 540 kilograms (1,190 lb) 540 kilograms (1,190 lb) 566 kilograms (1,248 lb) 566 kilograms (1,248 lb) 550 kilograms (1,210 lb)
Use UR-200
First Stage 		UR-200
First Stage 		UR-200
Second Stage 		UR-500
Second Stage 		UR-500
Second Stage 		Proton
Second Stage 		Proton
Second Stage 		Proton
Third Stage
First Launch 1963-11-061963-11-061963-11-061965-07-161965-07-161967-03-101967-03-101967-03-10
Last Launch 1964-10-20 1964-10-20 1964-10-20 1966-07-06 1966-07-06
Status Retired Retired Retired Retired Retired In Production In Production In Production
References [1][3][7][12][13][14][23][24][25][26]

See also

References

  1. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 "RD0208, RD0209 Launch Vehicle Proton (8K82H-4 two stages). RD0210, RD0211, RD0212 (RD0213, RD0214) Launch Vehicle Proton (8K82K, 8K82KM three stages)". KBKhA. Retrieved 2015-06-08.
  2. ↑ Pillet, Nicolas. "Le troisième étage du lanceur Proton" (in French). Kosmonavtika.com. Retrieved 2015-06-08.
  3. 1 2 3 4 Zak, Anatoly. "RD-0212 engine". www.russianspaceweb.com. Retrieved 2015-06-08.
  4. ↑ "Liquid Rocket Engine". Voronezh Mechanical Plant. Retrieved 2015-06-08.
  5. 1 2 Zak, Anatoly. "UR-200 / 8K81 / SS-X-10". www.russianspaceweb.com. Retrieved 2015-06-08.
  6. 1 2 "UR-200". Encyclopedia Astronautica. Retrieved 2015-06-08.
  7. 1 2 3 Zak, Anatoly. "Birth of Proton: The Iconic Rocket That Almost Wasn't". www.russianspaceweb.com. Retrieved 2015-06-08.
  8. ↑ Zak, Anatoly. "Proton/UR-500/8k82/SL-9". 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 4 5 6 7 "KBKHA LIQUID ROCKET ENGINES, WHICH ENSURED THE SUCCESSFUL REALIZATION OF THE ADVANCED SPACE PROGRAMS (FOR THE FIRST TIME IN THE WORLD)". KBKhA. Retrieved 2015-06-08.
  12. 1 2 "RD-0203". Encyclopedia Astronautica. Retrieved 2015-06-08.
  13. 1 2 "RD-0204". Encyclopedia Astronautica. Retrieved 2015-06-08.
  14. 1 2 "RD-0206". Encyclopedia Astronautica. Retrieved 2015-06-08.
  15. ↑ "RD-0208". Encyclopedia Astronautica. Retrieved 2015-06-08.
  16. ↑ "RD-0209". Encyclopedia Astronautica. Retrieved 2015-06-08.
  17. ↑ "RD-0210". Encyclopedia Astronautica. Retrieved 2015-06-08.
  18. ↑ "RD-0211". Encyclopedia Astronautica. Retrieved 2015-06-08.
  19. ↑ "RD-0213". Encyclopedia Astronautica. Retrieved 2015-06-08.
  20. ↑ "RD-0202". Encyclopedia Astronautica. Retrieved 2015-06-08.
  21. ↑ "RD-0205". Encyclopedia Astronautica. Retrieved 2015-06-08.
  22. ↑ "RD-0212". Encyclopedia Astronautica. Retrieved 2015-06-08.
  23. ↑ "RD-0203, RD-0204, RD-0205, RD-0206, RD-0207. Intercontinental ballistic missile UR-200". KBKhA. Retrieved 2015-06-08.
  24. ↑ "RD-0210/0211 (8D411 K/8D412K) Liquid-propellant rocket engine". Khrunichev State Research and Production Space Center. Retrieved 2015-06-08.
  25. ↑ "RD-0212 (8D49) Liquid-propellant rocket engine". Khrunichev State Research and Production Space Center. Retrieved 2015-06-08.
  26. ↑ Pillet, Nicolas. "Le deuxième étage du lanceur Proton" (in French). Kosmonavtika.com. Retrieved 2015-06-08.

External links

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