UR-700 Launch Profile. At lift-off, nine engines - six on the six outer stage 1 modules, and three on the three core modules - fired. During the stage 1 burn, the three engines of the core modules were fed by propellants in forward tanks of the outer six modules. Therefore the Stage 2 core burn started with full tanks in the core modules. Stage 3, a modification of the Proton first stage, placed the 151 tonne LK-700 spacecraft into a 200 km earth parking orbit.
Credit: © Mark Wade
Russian heavy-lift orbital launch vehicle. UR-700 with high energy upper stage consisting of 7 x RO-31 Nuclear A engines using LH2+Methane propellants with a total thrust of 280 tonnes. Usable third stage propellant 196 tonnes, payload increased to 230 to 250 tonnes
LEO Payload: 270,000 kg (590,000 lb) to a 200 km orbit at 51.00 degrees.
Status: Design 1968.
More... - Chronology...
Gross mass: 4,823,000 kg (10,632,000 lb).
Payload: 270,000 kg (590,000 lb).
Height: 76.00 m (249.00 ft).
Diameter: 17.60 m (57.70 ft).
Thrust: 56,500.00 kN (12,701,700 lbf).
Apogee: 200 km (120 mi).
RO-31 Kosberg nuclear/lh2 rocket engine. 392 kN. UR-700 Third Stage. Study 1967. Engine proposed for UR-700 third stage to achieve 250 tonne payload to low earth orbit. Probably closely related to RD-0411. More...
UR-700 The UR-700 was the member of Vladimir Chelomei's Universal Rocket family designed in the 1960's to allow direct manned flight by the LK-700 spacecraft to the surface of the moon. Later versions, some of completely different configuration, were studied for manned Mars expeditions. More...
Associated Manufacturers and Agencies
Chelomei Russian manufacturer of rockets, spacecraft, and rocket engines. Chelomei Design Bureau, Reutov, Russia. More...
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