RD-0124
RD-0124 model on display at the 2013 Paris Air Show | |
| Country of origin | Russia |
|---|---|
| Date | 1993–2006 |
| First flight | 2006-12-27 |
| Designer | Valery Kozelkov and Viktor Gorokhov) |
| Manufacturer | Chemical Automatics Design Bureau |
| Application | Upper stage engine |
| Associated LV | Current: Angara, Soyuz-2.1b, Soyuz-2.1v Planned: 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 | RD-0124: 270 seconds RD-0124A: 424 seconds |
| Dimensions | |
| Length | 1,575 mm (62.0 in) |
| Diameter | 2,400 mm (94 in) |
| Dry mass | RD-0124: 572 kg (1,261 lb) RD-0124A: 548 kg (1,208 lb) |
| Used in | |
| Soyuz 2.1b / Soyuz 2.1v Block I stage Angara URM-2 stage | |
| References | |
| References | |
The RD-0124 (Russian: Ракетный Двигатель-0124, romanized: Raketnyy Dvigatel-0124, lit. 'Rocket Engine 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 Block I stage used on 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.