A | B | C | D | E | F | G | H | CH | I | J | K | L | M | N | O | P | Q | R | S | T | U | V | W | X | Y | Z | 0 | 1 | 2 | 3 | 4 | 5 | 6 | 7 | 8 | 9
| Country of origin | Russia |
|---|---|
| Date | 2011[1] |
| 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, vacuum | 2,085 kN (469,000 lbf) |
| Thrust, sea-level | 1,920 kN (430,000 lbf) |
| Thrust-to-weight ratio | 103 |
| Specific impulse, vacuum | 337.5 s (3.310 km/s) |
| Specific impulse, sea-level | 311.2 s (3.052 km/s) |
| Dimensions | |
| Length | 3020 mm |
| Diameter | 2100 mm |
| Dry weight | 1900 kg [2] |
The RD-193 is a high performance single-combustion chamber rocket engine, developed in Russia from 2011 to 2013. 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.[1]
Design
The engine is a simplified version of the RD-191, omitting the swing assembly chamber and its related structural elements, thus reducing size and weight (300 kg) and lowering cost.[3]
See also
References
- ^ a b Zak, Anatoly. "RD-193". russianspaceweb.com. Retrieved 2015-06-04.
- ^ "В России создан новый ракетный двигатель". ВПК. 2013-04-08. Archived from the original on 2013-04-14. Alt URL
- ^ Огнев В. (2013). "Универсальный ракетный двигатель РД-193. Мнение инженера-разработчика". Журнал «Новости космонавтики». Archived from the original on 22 February 2020.
External links
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| Current rockets |
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| Cancelled proposals | ||
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