RD-263

RD-263 (РД-263)
Country of originUSSR
Date1969-1975
DesignerEnergomash, V.Glushko
ManufacturerPA Yuzhmash[1]
Associated LVR-36M and Dnepr
StatusOut of production
Liquid-fuel engine
PropellantN2O4 / UDMH
Mixture ratio2.67
CycleOxidizer-rich staged combustion
Configuration
Chamber1[2]
Performance
Thrust, vacuum1,128 kilonewtons (254,000 lbf)
Thrust, sea-level1,040 kilonewtons (230,000 lbf)
Chamber pressure20.6 megapascals (2,990 psi)
Specific impulse, vacuum318 s (3.12 km/s)
Specific impulse, sea-level293 s (2.87 km/s)
Gimbal range7°[3]
Dimensions
Length2,150 millimetres (85 in)
Diameter1,080 millimetres (43 in)
Dry mass870 kilograms (1,920 lb)
Used in
R-36M and R-36MUTTKh core stage (15А14 and 15A18)
References
References[2][4]

The RD-263 (GRAU Index 15D117) is a liquid rocket engine, burning N2O4 and UDMH in the oxidizer rich staged combustion cycle.[2] Four RD-263 engines form a propulsion module RD-264 (GRAU Index 15D119).[5] For the R-36M KB Yuzhnoye only ordered the first stage propulsion to Energomash, instead of both stages, arguing that they were overworked with the RD-270 development. By April 1970 Yuzhnoye was getting the engine documentation. By the end of 1972 Energomash started to test fire the engines in its own test stand. And by September 1973 the engine was certified for flight.[1] While the engine is out of production, the ICBM as well as the Dnepr remain operational as of 2015.[3]

  1. ^ a b Cite error: The named reference rsw-r36m was invoked but never defined (see the help page).
  2. ^ a b c Cite error: The named reference ea-rd263 was invoked but never defined (see the help page).
  3. ^ a b Cite error: The named reference rsw-dnepr was invoked but never defined (see the help page).
  4. ^ Cite error: The named reference npoem-el was invoked but never defined (see the help page).
  5. ^ Cite error: The named reference ea-rd264 was invoked but never defined (see the help page).