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 |
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.