| 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 | |
| References | |
| References | |
The S5.142 (AKA DST-25) is a liquid pressure-fed rocket engine burning N2O4/UDMH with an O/F of 1.85. It is used for crew-rated spacecraft propulsion applications. It was used in KTDU-80 propulsion module from the Soyuz-TM to the Soyuz-TMA-M, as the low thrust thruster (DPO-M). As of the Soyuz MS, KTDU-80 does not use DPO-M anymore.
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). 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).
Versions
This engine has been used in crewed Russian space program since the Soyuz TM-23. There are two versions:
- 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.
- S5.142A: A version of the S5.142 adapted for the KVTK upper stage for the Angara rocket.
See also
References
- ^ "ЖРДМТ от 0,5 кгс до 250 кгс" [Small thrust jet engine from 0.5 kgf to 250 kgf] (in Russian). KB KhIMMASH. Archived from the original on 23 April 2013.
- "Двигатели 1944-2000: Аавиационные, Ракетные, Морские, Промышленные" [Aviadvigatel 19442-2000: Aviation, rocketry, naval and industry] (PDF) (in Russian). pp. 75–81. Retrieved 2015-07-25.
- ^ Pillet, Nicolas. "Le système de propulsion du vaisseau Soyouz" [The propulsion system of the Soyuz spacecraft] (in French). Kosmonavtika.com. Retrieved 2015-07-14.
- ^ "Основные двигатели разработки КБХМ" [The main engines produced by KbKhA] (in Russian). Retrieved 2015-07-25.
- ^ RKK Energia (June 1999). "3.17. Комбинированная Двигательная Установка (КДУ) (Combined Propulsion System)". Soyuz Crew Operations Manual (SoyCOM) (ROP-19) Final. pp. 122–129 – via NASASpaceFlight.com.
- ^ Zak, Anatoly (2016-07-07). "Propulsion system for the Soyuz MS spacecraft". Russian Space Web. Retrieved 2016-07-06.
External links
- KB KhIMMASH Official Page (in Russian) Archived 2013-04-23 at the Wayback Machine
| Spacecraft engines and motors | ||
|---|---|---|
| Liquid fuel engines |  | |
| Solid propellant motors | ||
| Related articles | ||
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