N2O4/UDMH propellant rocket stage. Loaded/empty mass 134,900/13,180 kg. Thrust 2,399.19 kN. Vacuum specific impulse 325 seconds. Proton UR-500 second stage. Flew only on two-stage version of Proton. Empty mass is correct; all other values estimated based on UR-500 Stage 2 original design and UR-500K stage 2 figures.
No Engines: 4.
Status: Retired 1966.
More... - Chronology...
Gross mass: 134,900 kg (297,400 lb).
Unfuelled mass: 13,180 kg (29,050 lb).
Height: 10.90 m (35.70 ft).
Diameter: 4.15 m (13.61 ft).
Span: 4.15 m (13.61 ft).
Thrust: 2,399.19 kN (539,359 lbf).
Specific impulse: 325 s.
Burn time: 160 s.
Number: 4 .
RD-0210 Kosberg N2O4/UDMH rocket engine. 582.1 kN. Isp=326s. Cluster of four similar engines used in second stage of Proton - one providing tank pressurization (8D412K/RD-0211) and three (8D411K/RD-0210). Staged combustion cycle. First flight 1965. More...
Associated Launch Vehicles
UR-500 Russian orbital launch vehicle. The original UR-500 two stage configuration was designed as a monster ICBM. It was flown four times from 1965, but never deployed as an operational missile. The design was succeeded by three and four stage versions for launching of large payloads into space. More...
N2O4/UDMH Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. Unsymmetrical Dimethylhydrazine ((CH3)2NNH2) became the storable liquid fuel of choice by the mid-1950's. Development of UDMH in the Soviet Union began in 1949. It is used in virtually all storable liquid rocket engines except for some orbital manoeuvring engines in the United States, where MMH has been preferred due to a slightly higher density and performance. More...
Home - Browse - Contact
© / Conditions for Use