RD-193
From Infogalactic: the planetary knowledge core
| Country of origin | Russia |
|---|---|
| Date | 2001 |
| Designer | NPO Energomash |
| Application | Main engine |
| Predecessor | RD-191 |
| Liquid-fuel engine | |
| Propellant | LOX / RP-1 |
| Cycle | Oxidizer-rich Staged combustion |
| Configuration | |
| Chamber | 1 |
| Performance | |
| Thrust (vac.) | 2,085 kN (469,000 lbf) |
| Thrust (SL) | 1,920 kN (430,000 lbf) |
| Thrust-to-weight ratio | 103 |
| Isp (vac.) | 337.5 s (3.310 km/s) |
| Isp (SL) | 311.2 s (3.052 km/s) |
| Dimensions | |
| Length | 3020 mm |
| Diameter | 2100 mm |
| Dry weight | 1900 kg [1] |
The RD-193 is a high performance single-combustion chamber rocket engine, developed in Russia. It is derived from the RD-170 originally used in the Energia launcher.
The RD-193 is fueled by a kerosene / LOX mixture and uses an oxygen-rich staged combustion cycle. RD-193 was proposed as a replacement for the NK-33, which is being used in the Soyuz-2-1v vehicle.[2]
Contents
Design
The engine is a simplified version of the RD-191. Characterized by the absence of swing assembly chamber and related to other structural elements, thus reducing the size and weight (300 kg) and lower its cost.[3]
See also
References
External links
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