Kosberg N2O4/UDMH rocket engine. 582.1 kN. Proton stage 3. Design 1962. Version of RD-0210. Staged combustion cycle (Oxidizer pre-burner gas routed to main chamber after driving turbine). Main engine for Proton Stage 3 in system RD-0212. Isp=326s.
Application: Proton stage 3.
Chambers: 4. Thrust (sl): 446.000 kN (100,264 lbf). Thrust (sl): 45,476 kgf. Chamber Pressure: 147.00 bar. Area Ratio: 81.3.
AKA: RD-473; RD-0213; 8D48.
More... - Chronology...
Status: Design 1962.
Diameter: 4.15 m (13.61 ft).
Thrust: 582.10 kN (130,861 lbf).
Specific impulse: 327 s.
Burn time: 230 s.
First Launch: 1962-68.
Associated Launch Vehicles
Monoblock UR-500 Russian orbital launch vehicle. During UR-500 design studies, two variants of the first stage were considered: polyblock and monoblock. The monoblock approach was that the first stage be assembled from two separate modules with the same diameter: an upper oxidiser module and a lower fuel and engine block. In assembly trials of this design it proved difficult, because of the height of the first stage, to obtain access to the upper stages and payload atop the rocket. Although there was a payload advantage compared to the more compact polyblock design, this was relatively small and outweighed by the operational difficulties. More...
Polyblock UR-500 Russian orbital launch vehicle. UR-500 design studies considered two variants of the first stage: polyblock and monoblock. The polyblock variant consisted of a centre large diameter oxidizer tank surrounded by several smaller diameter fuel tanks. This version could be assembled in a special rig with the lateral blocks being sequentially mounted on the centre. In January 1962 this design was chosen as most advantageous, following studies that indicated improved wind loads and bending moment characteristics compared to the monoblock design. The developed version of the design would become known as the Proton. More...
Associated Manufacturers and Agencies
Kosberg Russian manufacturer of rocket engines. Kosberg Design Bureau, Russia. 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...
Haeseler, Dietrich, Visit to the museum of Chemical Automatics Design Bureau, Voronezh 1992 via Dietrich Haeseler.
R-56 Block O N2O4/UDMH propellant rocket stage. Loaded/empty mass 32,000/2,000 kg. Thrust 544.20 kN. Vacuum specific impulse 327 seconds. Empty mass estimated (rounded figures given in source material indicates impossible 31 tonnes gross with 30 tonnes propellant). More...
UR-500 Stage 2 N2O4/UDMH propellant rocket stage. Loaded/empty mass 137,700/16,000 kg. Thrust 3,183.20 kN. Vacuum specific impulse 320 seconds. Original Proton second stage design. More...
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