RD-0210
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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Wikipedia