 Mockup | |
| Country of origin | USSR/Russia |
|---|---|
| First flight | 1967-03-10[1] |
| Designer | OKB-154, Yankel I. Guerchkovitch[1][2][3] |
| Manufacturer | Voronezh Mechanical Plant[4] |
| Application | Upper Stage |
| Associated LV | Proton |
| Predecessor | RD-0208[1] |
| Status | In Production |
| Liquid-fuel engine | |
| Propellant | N2O4[1] / UDMH[1] |
| Mixture ratio | 2.6 |
| Cycle | Oxidizer Rich Staged combustion[1] |
| Configuration | |
| Chamber | 1 |
| Performance | |
| Thrust, vacuum | 582 kN (131,000 lbf)[1] |
| Chamber pressure | 14.7 MPa (2,130 psi)[1] |
| Specific impulse, vacuum | 326.5s[1] |
| Burn time | 220s[1] |
| Dimensions | |
| Length | 2,327 mm (91.6 in)[1] |
| Diameter | 1,470 mm (58 in)[1] |
| Dry mass | 566 kg (1,248 lb)[1] |
| 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 an 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.
- ^ a b c d e f g h i j k l m Cite error: The named reference
kbkha-rd0208was invoked but never defined (see the help page). - ^ Cite error: The named reference
kosmo-proton3ewas invoked but never defined (see the help page). - ^ Cite error: The named reference
rsw-rd0212was invoked but never defined (see the help page). - ^ Cite error: The named reference
vmp-lprewas invoked but never defined (see the help page).