RD-0124

RD-0124 (14D23)
Country of originRussia
Date1993-2006
First flight2006-12-27
DesignerKBKhA (Chief designers: Valery Kozelkov, Viktor Gorokhov [ru])[1]
ManufacturerKBKhA in-house[2]
ApplicationUpper Stage
Associated LVSoyuz-2, Angara, Soyuz-5
PredecessorRD-0110
StatusIn Production
Liquid-fuel engine
PropellantLOX / RP-1
CycleStaged Combustion
Configuration
Chamber4
Performance
Thrust, vacuum294.3 kN (66,200 lbf)
Thrust-to-weight ratio52.5
Chamber pressure15.7 MPa (2,280 psi)
Specific impulse, vacuum359 s (3.52 km/s)
Burn time300 s
Dimensions
Length1,575 mm (62.0 in)
Diameter2,400 mm (94 in)
Dry mass572 kg (1,261 lb)
Used in
Soyuz-2-1b and Soyuz-2-1v Block-I
References
References[3][4][5][6]

The RD-0124 (GRAU Index 14D23) is a rocket engine burning liquid oxygen and kerosene in an oxygen-rich staged combustion cycle, developed by the Chemical Automatics Design Bureau in Voronezh.[3] RD-0124 engines are used on the Soyuz-2.1b and Soyuz-2-1v. A variant of the engine, the RD-0124A, is used on the Angara rocket family's URM-2 upper stage.

  1. ^ Cite error: The named reference VG was invoked but never defined (see the help page).
  2. ^ Cite error: The named reference kbkha-history was invoked but never defined (see the help page).
  3. ^ a b Cite error: The named reference kbkha-rd0124 was invoked but never defined (see the help page).
  4. ^ Cite error: The named reference aiaa-2005-3946 was invoked but never defined (see the help page).
  5. ^ Cite error: The named reference khrunichev-rd0124a was invoked but never defined (see the help page).
  6. ^ Cite error: The named reference rsw-rd0124 was invoked but never defined (see the help page).