S5.142

S5.142
Country of origin Russia
Date 1990-1996
First flight 1996-02-21 (Soyuz TM-23)
Designer KB KhIMMASH
Application attitude control thruster
Predecessor 11D427M
Status In Production
Liquid-fuel engine
Propellant N2O4 / UDMH
Mixture ratio 1.85
Cycle pressure fed
Configuration
Chamber 1
Nozzle ratio 45
Performance
Thrust (vac.) 25 N (5.6 lbf)
Chamber pressure 0.88 MPa (128 psi)
Isp (vac.) 285 s (2.79 km/s)
Burn time 25,000 seconds
Restarts 300,000
Dimensions
Length 180 mm (7.1 in)
Diameter 136 mm (5.4 in)
Dry weight 0.9 kg (2.0 lb)
Used in
KTDU-80
References
References [1][2][3][4][5]

The S5.142 (AKA DST-25) is a liquid pressure-fed rocket engine burning N2O4/UDMH with an O/F of 1.85.[1] It is used for crew-rated spacecraft propulsion applications.[5] It is currently used in the Soyuz-TMA-M spacecraft propulsion module KTDU-80, as the low thrust thruster (DPO-M).[3] The S5.142 generates 25 N (5.6 lbf) of thrust with a chamber pressure of 0.88 MPa (128 psi) and a nozzle expansion of 45 that enables it to achieve a specific impulse of 285 s (2.79 km/s).[1] It is rated for 300,000 starts with a total firing time of 25,000 seconds and can do single burns from 0.03seconds to 4,000 seconds. Each unit weights 0.9 kg (2.0 lb).[1][5]

Versions

This engine has been used in manned Russian space program since the Soyuz TM-23.[1] The are two versions:[4]

See also

References

External links

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