S5.142

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 was used in KTDU-80 propulsion module from the Soyuz-TM to the Soyuz-TMA-M, as the low thrust thruster (DPO-M).^[3] As of the Soyuz MS, KTDU-80 does not use DPO-M anymore.^[6]

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 0.03 seconds to 4,000 seconds. Each unit weights 0.9 kg (2.0 lb).^[1][5]

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

• S5.142 (AKA DST-25): Version used as DPO-M (attitude control thrusters) on the KTDU-80 unit of the Soyuz-TM up to the Soyuz-TMA-M.^[1]
• S5.142A: A version of the S5.142 adapted for the KVTK upper stage for the Angara rocket.^[4]

• KB KhIMMASH
• KTDU-80
• Soyuz-TMA

• KB KhIMMASH Official Page (in Russian) Archived 2013-04-23 at the Wayback Machine

This rocketry article is a stub. You can help Wik.ipedia.Pro by expanding it.

• v
• t