RD-193
Russian liquid-fuei rocket engine
Country of origin | Russia |
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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 mass | 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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Rocket engines and solid motors for orbital launch vehicles
fuel
Cryogenic |
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Semi- cryogenic |
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Storable |
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Other |
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![](http://upload.wikimedia.org/wikipedia/commons/thumb/4/4d/RS-68_rocket_engine_test.jpg/120px-RS-68_rocket_engine_test.jpg)
fuel
- China
- Europe
- India
- Iran
- Salman
- Rafe
- Israel
- Japan
- USA
- * Different versions of the engine use different propellant combinations
- Engines in italics are under development