RD-0216
Country of origin | USSR |
---|---|
First flight | 1965-04-19[1] |
Designer | OKB-154[1] |
Manufacturer | PO Motorostroitel or Perm[2] |
Application | ICBM propulsion |
Associated LV | UR-100[1] |
Successor | RD-0235 |
Status | Retired |
Liquid-fuel engine | |
Propellant | N2O4[3] / UDMH[3] |
Cycle | Oxidizer Rich Staged combustion[1] |
Configuration | |
Chamber | 1[3] |
Performance | |
Thrust | 219 kilonewtons (49,000 lbf)[3] |
Chamber pressure | 17.4 megapascals (2,520 psi)[3] |
Specific impulse | 313 s (3.07 km/s)[3] |
Used in | |
UR-100 Core Stage [4] |
Country of origin | USSR |
---|---|
First flight | 1973-04-09[5] |
Designer | OKB-154[5] |
Manufacturer | Krasny Oktyabr factory[2] |
Application | ICBM propulsion |
Associated LV | UR-100N, Rokot and Strela[5] |
Status | Out of Production |
Liquid-fuel engine | |
Propellant | N2O4[6] / UDMH[6] |
Cycle | Oxidizer Rich Staged combustion[5] |
Configuration | |
Chamber | 1[6] |
Performance | |
Thrust | 240 kilonewtons (54,000 lbf)[6] |
Chamber pressure | 17.5 megapascals (2,540 psi)[6] |
Specific impulse | 320 s (3.1 km/s)[6] |
Used in | |
UR-100N Second Stage [6] |
The RD-0216 and RD-0217 are liquid rocket engines, burning N2O4 and UDMH in the oxidizer rich staged combustion cycle.[1][3] The only difference between the RD-0216 and the RD-0217 is that the latter doesn't have a heat exchanger to heat the pressuring gasses for the tanks.[3] Three RD-0216 and one RD-0217 were used on the first stage of the UR-100 ICBM.[7] The engines were manufactured until 1974 and stayed in operational use until 1991. More than 1100 engines were produced.[3]
For the UR-100N project, while first stage propulsion was based on the more powerful RD-0233 engine. The second stage used a variation of the RD-0217 called the RD-0235 (GRAU Index 15D113).[8] It used a vacuum optimized nozzle extension, and thus had an extra 10 seconds of isp and 21 kilonewtons (4,700 lbf)[6] of more thrust. It has a fixed nozzle and relies on the RD-0236 vernier engine for thrust vectoring. While the engine has been out of production for a while, the UR-100NU and the Rokot and Strela use it as of 2015.[6]
See also
References
- ^ a b c d e "RD-0216, RD-0217. Intercontinental ballistic missile RS-10". KBKhA. Retrieved 2015-06-19.
- ^ a b Lardier, Christian. "Liquid Propellant Engines in the Soviet Union". Thirty-third IAA History Symposium. 19. American Astronautical Society: 39–73.
- ^ a b c d e f g h i "RD-0216". Encyclopedia Astronautica. Archived from the original on 2016-03-03. Retrieved 2015-06-19.
- ^ "RD-0217". Encyclopedia Astronautica. Archived from the original on 2016-03-03. Retrieved 2015-06-19.
- ^ a b c d "RD-0216, RD-0217. Intercontinental ballistic missile RS-10". KBKhA. Retrieved 2015-06-19.
- ^ a b c d e f g h i "RD-0235". Encyclopedia Astronautica. Archived from the original on 2015-08-24. Retrieved 2015-06-19.
- ^ Zak, Anatoly. "UR-100 Family". RussianSpaceWeb.com. Retrieved 2015-06-19.
- ^ "Rockot Launch Vehicle". Khrunichev State Research and Production Space Center. Retrieved 2015-06-19.
External links
- KbKhA official information on the engine.
- KbKhA official information on the engine.
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fuel
Cryogenic |
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Semi- cryogenic |
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Storable |
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Other |
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![](http://upload.wikimedia.org/wikipedia/commons/thumb/4/4d/RS-68_rocket_engine_test.jpg/120px-RS-68_rocket_engine_test.jpg)
fuel
- China
- Europe
- India
- Iran
- Salman
- Rafe
- Israel
- Japan
- USA
- * Different versions of the engine use different propellant combinations
- Engines in italics are under development
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