KVD-1

KVD-1 (12KRB)
Country of originUSSR/Russia
First flight2001-04-20, GSAT-1 Mission, GSLV debut flight
Last flight2010-12-25, GSAT-5P launch, GSLV Mk I final flight
DesignerKB KhIMMASH
ApplicationUpper stage engine
Associated LVGSLV Mk 1
StatusRetired
Liquid-fuel engine
PropellantLiquid oxygen / liquid hydrogen
Mixture ratio6
CycleStaged combustion
Configuration
Chamber1 + 2 verniers
Performance
Thrust, vacuum69.6 kN (15,600 lbf)
Chamber pressure5.6 MPa (810 psi)
Specific impulse, vacuum462 s
Burn time800 s (600 s in a single burn)
Gimbal rangeNone; uses 2 vernier engines for attitude control[1]
Dimensions
Length2.14 m (7 ft 0 in)
Diameter1.58 m (5 ft 2 in)
Dry mass282 kg (622 lb)
References
References[2][3][4]

KVD-1 was an upper stage LOX/LH2 cryogenic engine developed by the Isayev Design Bureau (now KB KhIMMASH) of Russia in the early 1960s. It is a modified version of the RD-56, developed for a never-completed cryogenic upper stage of the N-1 super-heavy lift rocket, with the goal of enabling crewed lunar missions by the USSR.[5] The KVD-1 produces a thrust of 7.5 tonnes.

  1. ^ Cite error: The named reference b14643de-gslvdesc was invoked but never defined (see the help page).
  2. ^ Cite error: The named reference ea-rd56 was invoked but never defined (see the help page).
  3. ^ Cite error: The named reference kbhmisaeva-kvd was invoked but never defined (see the help page).
  4. ^ Cite error: The named reference kbhmisaeva-kvds592 was invoked but never defined (see the help page).
  5. ^ "KVD-1 (left) with its precursor 11D56". ESA. Retrieved 13 May 2023.