KTDU-35

KTDU-35
Country of originUSSR
Date1962–1967
First flight1966-11-28 (Kosmos 133)
DesignerOKB-2, Anton Tavzarachvili
ApplicationSpacecraft main propulsion
PredecessorS5.4
SuccessorKTDU-426
StatusRetired
Liquid-fuel engine
PropellantAK27I / UDMH
Mixture ratio1.85
Cyclegas generator
Configuration
ChamberS5.60: 1
S5.35: 2
Performance
Thrust, vacuumS5.60:4.09 kN (920 lbf)
S5.35:4.03 kN (910 lbf)
Chamber pressureS5.60:3.92 MPa (569 psi)
Specific impulse, vacuumS5.60:278 seconds
S5.35:270 seconds
Burn time500 seconds
Restarts25
Dimensions
Length1.1 m (43 in)
Diameter1.5 m (59 in)
Dry mass305 kg (672 lb)
Used in
Soyuz from 7K-OK to 7K-T and Progress 7K-TG
References
References[1][2][3][4][5][6]

The KTDU-35 (GRAU Index 11D62) was a Soviet spacecraft propulsion system composed of two liquid rocket engines, the primary, S5.60 (SKD) and the secondary S5.35 (DKD), fed from the same propellant tanks. Both engines burn UDMH and AK27I in the gas generator cycle.[4] It was designed by OKB-2, the famous Isaev Design Bureau, for the original Soyuz programme.[3]

Within the Soyuz and Progress, the SKD is the primary engine, the DKD is the backup engine for main orbital correction and de-orbit operations. The engine generate 4.09 kN (920 lbf) (SKD) or 4.03 kN (910 lbf) (DKD) of thrust with a specific impulse of 278 seconds and 270 seconds, respectively. The SKD nozzle is fixed in the aft of the craft, and the dual DKD nozzles are on either side. The spacecraft attitude system (DPO) is responsible for pointing the vehicle in the correct direction and keep it that way during SKD burns.[7]

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  3. ^ a b Cite error: The named reference ea-ktdu35 was invoked but never defined (see the help page).
  4. ^ a b Cite error: The named reference lprd-kbhm was invoked but never defined (see the help page).
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