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RD-0203

RD-0210 (РД-0210)
Mockup rocket motor RD-0210 Salon du Bourget 2013 DSC 0081.jpg
Mockup
Country of origin USSR/Russia
First flight 1967-03-10
Designer OKB-154, Yankel I. Guerchkovitch
Manufacturer Voronezh Mechanical Plant
Application Upper Stage
Associated L/V Proton
Predecessor RD-0208
Status In Production
Liquid-fuel engine
Propellant N2O4 / UDMH
Mixture ratio 2.6
Cycle Oxidizer Rich Staged combustion
Configuration
Chamber 1
Performance
Thrust (vac.) 582 kN (131,000 lbf)
Chamber pressure 14.7 MPa (2,130 psi)
Isp (vac.) 326.5s
Burn time 220s
Dimensions
Length 2,327 mm (91.6 in)
Diameter 1,470 mm (58 in)
Dry weight 566 kg (1,248 lb)
Used in
UR-200 and UR-500 and Proton second stage

The RD-0210 (GRAU Index: 8D411K) is also known as the RD-465. It and its twin, the RD-0211, are rocket engines burning N2O4 and UDMH in a oxidizer rich staged combustion cycle. They have single nozzle, possess TVC and are the latest evolution in the RD-0203/4 lineage. They are the engines used on the Proton second stage. The RD-0213 is a fixed nozzle variation that is used on the RD-0212 module of the Proton third stage.

When Chelomey's OKB-52 started their UR-200 ICBM project, they requested S. A. Kosberg's OKB-154 to develop the propulsion. They decided to use the same basic block for both the first and second stage. But to achieve the required performance, Kosberg had to develop a staged combustion engine, a then extremely aggressive feat. Only M. V. Melnikov of OKB-1 had designed a staged combustion engine before, the S1.5400, and it used a different propellant mix with significant less thrust.

To simplify design and manufacture, the engine would be used both on the first and the second stages. The first stage would use a module - the RD-0202 - that comprised three RD-0203 and one RD-0204, while the upper stage would use a RD-0205 module comprising a RD-0206 main engine plus an auxiliary vernier engine, the RD-0207. The RD-0204 only difference to the RD-0203 was that it included a heat exchanger to heat the pressurant gases for the first stage tank. The RD-0206 was very similar to the RD-0204, but its nozzle was vacuum optimized and had a fixed nozzle. The thrust vector control task was delegated to the four nozzle RD-0207 vernier engine. While the UR-200 project was in direct competition to the R-36 and was cancelled in favor of the latter, it did had a few test launches and thus was a proven design.


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