RD-0210

RD-0210 (РД-0210)
Mockup
Country of originUSSR/Russia
First flight1967-03-10[1]
DesignerOKB-154, Yankel I. Guerchkovitch[1][2][3]
ManufacturerVoronezh Mechanical Plant[4]
ApplicationUpper Stage
Associated LVProton
PredecessorRD-0208[1]
StatusIn Production
Liquid-fuel engine
PropellantN2O4[1] / UDMH[1]
Mixture ratio2.6
CycleOxidizer Rich Staged combustion[1]
Configuration
Chamber1
Performance
Thrust, vacuum582 kN (131,000 lbf)[1]
Chamber pressure14.7 MPa (2,130 psi)[1]
Specific impulse, vacuum326.5s[1]
Burn time220s[1]
Dimensions
Length2,327 mm (91.6 in)[1]
Diameter1,470 mm (58 in)[1]
Dry mass566 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.

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  2. ^ Cite error: The named reference kosmo-proton3e was invoked but never defined (see the help page).
  3. ^ Cite error: The named reference rsw-rd0212 was invoked but never defined (see the help page).
  4. ^ Cite error: The named reference vmp-lpre was invoked but never defined (see the help page).