- Versions
- See also
- References
- External links
{{Infobox rocket engine
|name =S5.142
|image =
|image_size =
|caption =
|country_of_origin=Russia
|date =1990-1996
|first_date =1996-02-21 (Soyuz TM-23)
|last_date =
|designer =KB KhIMMASH
|manufacturer =
|purpose =attitude control thruster
|associated =
|predecessor =11D427M
|successor =
|status =Retired
|type =liquid
|fuel =UDMH
|oxidiser =N2O4
|mixture_ratio =1.85
|cycle =pressure fed
|pumps =
|description =
|combustion_chamber=1
|nozzle_ratio =45
|thrust =
|thrust_at_altitude=
|thrust(Vac) ={{convert|25|N|lbf|abbr=on}}
|thrust(SL) =
|thrust_to_weight=
|chamber_pressure={{convert|0.88|MPa|psi|abbr=on}}
|specific_impulse=
|specific_impulse_vacuum={{convert|285|isp|abbr=on}}
|specific_impulse_sea_level=
|total_impulse =
|burn_time =25,000 seconds
|restarts =300,000
|gimbal =
|capacity =
|dimensions =
|length ={{convert|180|mm|in|abbr=on}}
|diameter ={{convert|136|mm|in|abbr=on}}
|dry_weight ={{convert|0.9|kg|lb|abbr=on}}
|used_in =KTDU-80
|references =[1]
|notes =
}}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 uses DPO-M anymore.[6] The S5.142 generates {{convert|25|N|lbf|abbr=on}} of thrust with a chamber pressure of {{convert|0.88|MPa|psi|abbr=on}} and a nozzle expansion of 45 that enables it to achieve a specific impulse of {{convert|285|isp|abbr=on}}.[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 {{convert|0.9|kg|lb|abbr=on}}.[1][5] VersionsThis engine has been used in manned 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]
See also- KB KhIMMASH
- KTDU-80
- Soyuz-TMA
References1. ^1 2 3 {{cite web |url=http://lpre.de/kbhm/index.htm |title=Основные двигатели разработки КБХМ |trans-title=The main engines produced by KbKhA |language=Russian |accessdate=2015-07-25}}
2. ^1 2 3 4 5 6 {{cite web |url=http://kbhmisaeva.ru/main.php?id=33 |title=ЖРДМТ от 0,5 кгс до 250 кгс |trans-title=Small thrust jet engine from 0.5 kgf to 250 kgf |publisher=KB KhIMMASH |language=Russian |accessdate=2015-07-25}}
3. ^1 2 {{cite web |url=http://www.kosmonavtika.com/vaisseaux/soyouz/tech/kdu/kdu.html |title=Le système de propulsion du vaisseau Soyouz |trans-title=The propulsion system of the Soyuz spacecraft |first1=Nicolas |last1=Pillet |publisher=Kosmonavtika.com |language=French |accessdate=2015-07-14}}
4. ^1 2 3 {{cite book |url=http://forum.nasaspaceflight.com/index.php?topic=6832.msg115484 |title=Soyuz Crew Operations Manual (SoyCOM) (ROP-19) Final |date=June 1999 |chapter=3.17. Комбинированная Двигательная Установка (КДУ) (Combined Propulsion System) |pages=122–129 |author=RKK Energia |website=NASASpaceFlight.com |subscription=yes }}
5. ^1 2 {{cite web |url=http://www.russianspaceweb.com/soyuz-ms-kdu.html |title=Propulsion system for the Soyuz MS spacecraft |last=Zak |first=Anatoly |publisher=Russian Space Web |date=2016-07-07 |access-date=2016-07-06}}
[1][2][3][4][5]
}}External links- KB KhIMMASH Official Page (in Russian)
{{Orbital spacecraft rocket engines}}{{rocket-stub}} 4 : Rocket engines of Russia|Rocket engines using hypergolic propellant|Rocket engines using the pressure-fed cycle|KB KhimMash rocket engines |