RD-120

RD-120 (РД-120)
Country of originUSSR/Russia
DesignerNPO Energomash, V.K.Chvanov, V.P. Radovsky
ManufacturerYuzhmash
ApplicationUpper stage
StatusOperational
Liquid-fuel engine
PropellantLOX / RP-1
CycleStaged combustion cycle
Performance
Thrust, vacuumStandard: 834 kN (187,000 lbf)
Uprated: 912 kN (205,000 lbf)
Thrust-to-weight ratioStandard: 75.55[note 1]
Uprated: 82.66[note 2]
Chamber pressureStandard: 162.8 bar (16.28 MPa)
Uprated: 178.1 bar (17.81 MPa)
Specific impulse, vacuum350 s (3.4 km/s)
Burn time315 seconds
Dimensions
Length3.87 m (12.7 ft)
Diameter1.95 m (6.4 ft)
Dry mass1,125 kg (2,480 lb)
Used in
Zenit-2, Zenit-3SL
References
References[1][2][3]

The RD-120 (GRAU Index 11D123) is a liquid upper stage rocket engine burning RG-1 (refined kerosene) and LOX in an oxidizer rich staged combustion cycle with an O/F ratio of 2.6.[2][3][4] It is used in the second stage of the Zenit family of launch vehicles.[1] It has a single, fixed combustion chamber and thus on the Zenit it is paired with the RD-8 vernier engine. The engine was developed from 1976 to 1985 by NPO Energomash with V.P. Radovsky leading the development.[3] It is manufactured by, among others, Yuzhmash in Ukraine.[5]

It should not be confused with the RD-0120, which is a discontinued LOX/hydrogen rocket engine that was used in the Soviet Energia launch system.


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  1. ^ a b Cite error: The named reference npoem-rd120 was invoked but never defined (see the help page).
  2. ^ a b Cite error: The named reference npoem-el was invoked but never defined (see the help page).
  3. ^ a b c Cite error: The named reference k204-wiki2emash was invoked but never defined (see the help page).
  4. ^ Cite error: The named reference aviadvigatel was invoked but never defined (see the help page).
  5. ^ Cite error: The named reference yuzhmash-rd120 was invoked but never defined (see the help page).