RD-861

RD-861 (РД-861)
Country of originSoviet Union
First flightOctober 27, 1967
DesignerYuzhnoye Design Bureau
ManufacturerYuzhmash
ApplicationUpper stage
Associated LVTsyklon-3
PredecessorRD-854
SuccessorRD-861K
StatusOut of production
Liquid-fuel engine
PropellantN2O4 / UDMH
Mixture ratio2.1
CycleGas generator
Configuration
Chamber1 + 4
Nozzle ratio112.4 (main)
Performance
Thrust, vacuum78.71 kN (17,690 lbf)
Chamber pressure8.88 MPa (1,288 psi)
Specific impulse, vacuum317 seconds
Burn timeUp to 130s
Restarts1
Dimensions
Length1.56 m (5 ft 1 in)
Diameter1.53 m (5 ft 0 in)
Dry mass123 kg (271 lb)
Used in
Tsyklon-2 and Tsyklon-3 third stage
References
References[1][2][3][4][5]

The RD-861 is a Soviet liquid propellant rocket engine burning UDMH and nitrogen tetroxide in a gas generator combustion cycle. It has a main combustion chamber, with four vernier nozzles fed by the gas generator output.[2] It can be reignited a single time.[4]

  1. ^ Cite error: The named reference ea-rd854 was invoked but never defined (see the help page).
  2. ^ a b Cite error: The named reference ea-rd861 was invoked but never defined (see the help page).
  3. ^ Cite error: The named reference ea-rd861k was invoked but never defined (see the help page).
  4. ^ a b Cite error: The named reference kosmo-tsiklone3 was invoked but never defined (see the help page).
  5. ^ Cite error: The named reference ukrspexport-rd861k was invoked but never defined (see the help page).