RD-270
Large Soviet rocket engine that used hypergolic propellants / From Wikipedia, the free encyclopedia
Dear Wikiwand AI, let's keep it short by simply answering these key questions:
Can you list the top facts and stats about RD-270?
Summarize this article for a 10 year old
RD-270 (Russian: Раке́тный дви́гатель 270, Rocket Engine 270, 8D420) was a single-chamber liquid-bipropellant rocket engine designed by Energomash (USSR) in 1960–1970. It was to be used on the first stages of proposed heavy-lift UR-700 and UR-900 rocket families, as well as on the N1. It has the highest thrust among single-chamber engines of the USSR, 640 metric tons at the surface of Earth. The propellants used are unsymmetrical dimethylhydrazine (UDMH) and nitrogen tetroxide (N2O4). The chamber pressure was among the highest considered, being about 26 MPa. This was achieved by applying full-flow staged combustion cycle for all the incoming mass of fuel, which is turned into a gas and passes through multiple turbines before being burned in the combustion chamber. This allowed the engine to achieve a specific impulse of 301 s (2.95 km/s) at the Earth's surface.
This article needs additional citations for verification. (November 2018) |
Country of origin | USSR/Russia |
---|---|
Date | 1969 |
Designer | V. Glushko, USSR/Ukrainian Soviet Socialist Republic |
Manufacturer | Energomash |
Successor | RD-270M |
Status | Retired |
Liquid-fuel engine | |
Propellant | N2O4 / UDMH |
Cycle | Full-flow staged combustion |
Performance | |
Thrust, vacuum | 6.710 MN (1,508,000 lbf)[1] |
Thrust, sea-level | 6.270 MN (1,410,000 lbf)[1] |
Thrust-to-weight ratio | 189.91 |
Chamber pressure | 26.1 MPa (3,790 psi)[1] |
Specific impulse, vacuum | 322 s (3.16 km/s) |
Specific impulse, sea-level | 301 s (2.95 km/s) |
Dimensions | |
Length | 194 in (4,900 mm) |
Diameter | 132 in (3,400 mm) |
Dry weight | 3,370 kg (7,430 lb)[1] |
Used in | |
1st stage of proposed UR-700 and UR-900 |
The engine testing was underway when the decision was made to cancel the program. Development was stopped with all other work on corresponding rocket projects on 11 December 1970.