RD-0216

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RD-0216 (РД-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 L/V 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]
RD-0235 (РД-0235)
Country of origin USSR
First flight 1973-04-09[5]
Designer OKB-154[5]
Manufacturer Krasny Oktyabr factory[2]
Application ICBM propulsion
Associated L/V 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 has 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 10s 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

  1. ^ a b c d e "RD-0216, RD-0217. Intercontinental ballistic missile RS-10". KBKhA. Retrieved 2015-06-19.
  2. ^ a b Lardier, Christian. "Liquid Propellant Engines in the Soviet Union". IAA History Simposia. American Astronautical Society. 19: 39–73. |access-date= requires |url= (help)
  3. ^ a b c d e f g h i "RD-0216". Encyclopedia Astronautica. Archived from the original on 2017-11-11. Retrieved 2015-06-19.
  4. ^ "RD-0217". Encyclopedia Astronautica. Archived from the original on 2017-11-11. Retrieved 2015-06-19.
  5. ^ a b c d "RD-0216, RD-0217. Intercontinental ballistic missile RS-10". KBKhA. Retrieved 2015-06-19.
  6. ^ 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.
  7. ^ Zak, Anatoly. "UR-100 Family". RussianSpaceWeb.com. Retrieved 2015-06-19.
  8. ^ "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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