RD-0124
The RD-0124 (GRAU Index 14D23) is a rocket engine burning liquid oxygen and kerosene in an oxygen-rich staged combustion cycle, developed by the Chemical Automatics Design Bureau in Voronezh. RD-0124 engines are used on the Soyuz-2.1b and Soyuz-2-1v. A variant of the engine, the RD-0124A, is used on the Angara rocket family's URM-2 upper stage.
| Country of origin | Russia |
|---|---|
| Date | 1993-2006 |
| First flight | 2006-12-27 |
| Designer | KBKhA (Chief designers: Valery Kozelkov, Viktor Gorokhov) |
| Manufacturer | KBKhA in-house |
| Application | Upper Stage |
| Associated LV | Soyuz-2, Angara, Soyuz-5 |
| Predecessor | RD-0110 |
| Status | In Production |
| Liquid-fuel engine | |
| Propellant | LOX / RP-1 |
| Cycle | Staged Combustion |
| Configuration | |
| Chamber | 4 |
| Performance | |
| Thrust, vacuum | 294.3 kN (66,200 lbf) |
| Thrust-to-weight ratio | 52.5 |
| Chamber pressure | 15.7 MPa (2,280 psi) |
| Specific impulse, vacuum | 359 s (3.52 km/s) |
| Burn time | 300 s |
| Dimensions | |
| Length | 1,575 mm (62.0 in) |
| Diameter | 2,400 mm (94 in) |
| Dry weight | 572 kg (1,261 lb) |
| Used in | |
| Soyuz-2-1b and Soyuz-2-1v Block-I | |
| References | |
| References | |
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