RD-0124
Sign in to saveThe 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 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.
Key facts
- Rocket engine.name
- RD-0124 (14D23)
- Rocket engine.image
- Rocket-motor-RD-0124-Salon-du-bourget-2013-DSC 0055.jpg
- Rocket engine.caption
- RD-0124 model on display at the 2013 Paris Air Show
- Rocket engine.country_of_origin
- Russia
- Rocket engine.date
- 1993–2006
- Rocket engine.first_date
- 2006-12-27
- Rocket engine.designer
- Valery Kozelkov and )
- Rocket engine.manufacturer
- Chemical Automatics Design Bureau
- Rocket engine.purpose
- Upper stage engine
- Rocket engine.associated
- Current: Angara, Soyuz-2.1b, Soyuz-2.1v Planned: Soyuz 5
- Rocket engine.predecessor
- RD-0110
- Rocket engine.status
- In production
- Rocket engine.type
- liquid
- Rocket engine.fuel
- RG-1
- Rocket engine.oxidiser
- LOX
- Rocket engine.cycle
- Staged combustion
- Rocket engine.combustion_chamber
- 4
- Rocket engine.thrust_to_weight
- 52.5
via Wikipedia infobox
Wikidata facts
- Image
- Rocket-motor-RD-0124-Salon-du-bourget-2013-DSC 0055.jpg
Sources (1)
via Wikidata · CC0
~3 min read
Article
5 sectionsContents
- Design
- History
- Versions
- See also
- References
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 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.
== Design == RD-0124 engines use a multi-stage turbopump powered by pre-combustion of the engine propellants in the preburner. The kerosene fuel is used for regenerative cooling of the engine. Vehicle attitude control during ascent is provided by gimbaling the engine in two planes. The propellant tanks are helium-pressurized. Four combustion chambers are fed by a single turbopump system. The engine operates at a high chamber pressure and, for the type of propellants used, achieves a very high specific impulse of nearly 360 seconds in vacuum.