| 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 | Retired |
| Liquid-fuel engine | |
| Propellant | N2O4 / UDMH |
| Mixture ratio | 1.85 |
| Cycle | pressure fed |
| Configuration | |
| Chamber | 1 |
| Nozzle ratio | 45 |
| Performance | |
| Thrust, vacuum | 25 N (5.6 lbf) |
| Chamber pressure | 0.88 MPa (128 psi) |
| Specific impulse, vacuum | 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 mass | 0.9 kg (2.0 lb) |
| Used in | |
| KTDU-80 (excluding Soyuz MS) | |
| References | |
| References | [1] [2] [3] [4] [5] [6] |
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]
Spacecraft engines and motors | ||
|---|---|---|
| Liquid fuel engines |  | |
| Solid propellant motors | ||
| Related articles | ||
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