RD-250

RD-250 (РД-250)
Country of originUSSR
First flightDecember 16th, 1965
DesignerOKB-456
ManufacturerPA Yuzhmash
Associated LVR-36, Tsyklon-2 and Tsyklon-3
StatusOut of Production
Liquid-fuel engine
PropellantN2O4 / UDMH
Mixture ratio2.6
CycleGas-generator
Configuration
Chamber2
Performance
Thrust, vacuum882 kN (198,000 lbf)
Thrust, sea-level788 kN (177,000 lbf)
Chamber pressure8.33 MPa (1,208 psi)
Specific impulse, vacuum301 s (2.95 km/s)
Specific impulse, sea-level270 s (2.6 km/s)
Dimensions
Dry mass788 kg (1,737 lb)
Used in
R-36, Tsyklon-2 and Tsyklon-3 first stage
References
References[1][2][3][4][5][6]

The RD-250 (GRAU Index 8D518) is the base version of a dual-nozzle family of liquid rocket engines, burning N2O4 and UDMH in the gas-generator open cycle.[7] The RD-250 was developed by OKB-456 for Yangel's PA Yuzhmash ICBM, the R-36 (8K67). Its variations were also used on the Tsyklon-2 and Tsyklon-3 launch vehicles. It was supposed to be used on the Tsyklon-4, but since the cancellation of the project it should be considered as out of production.

  1. ^ Cite error: The named reference npoem-el was invoked but never defined (see the help page).
  2. ^ Cite error: The named reference ea-rd250 was invoked but never defined (see the help page).
  3. ^ Cite error: The named reference ea-rd251 was invoked but never defined (see the help page).
  4. ^ Cite error: The named reference ea-rd252 was invoked but never defined (see the help page).
  5. ^ Cite error: The named reference kosmo-tsiklone2 was invoked but never defined (see the help page).
  6. ^ Cite error: The named reference kosmo-tsiklone3 was invoked but never defined (see the help page).
  7. ^ "The RD-250 engine at the center of an international storm". www.russianspaceweb.com. Retrieved 2023-01-03.