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RD-0235

RD-0216 (РД-0216)
Country of origin USSR
First flight 1965-04-19
Designer OKB-154
Manufacturer PO Motorostroitel or Perm
Application ICBM propulsion
Associated L/V UR-100
Successor RD-0235
Status Retired
Liquid-fuel engine
Propellant N2O4 / UDMH
Cycle Oxidizer Rich Staged combustion
Configuration
Chamber 1
Performance
Thrust 219 kilonewtons (49,000 lbf)
Chamber pressure 17.4 megapascals (2,520 psi)
Specific impulse 313 s (3.07 km/s)
Used in
UR-100 Core Stage
RD-0235 (РД-0235)
Country of origin USSR
First flight 1973-04-09
Designer OKB-154
Manufacturer
Application ICBM propulsion
Associated L/V UR-100N, Rokot and Strela
Status Out of Production
Liquid-fuel engine
Propellant N2O4 / UDMH
Cycle Oxidizer Rich Staged combustion
Configuration
Chamber 1
Performance
Thrust 240 kilonewtons (54,000 lbf)
Chamber pressure 17.5 megapascals (2,540 psi)
Specific impulse 320 s (3.1 km/s)
Used in
UR-100N Second Stage

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 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.

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). It used a vacuum optimized nozzle extension, and thus had an extra 10s of isp and 21 kilonewtons (4,700 lbf) 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.



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