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==Versions==
==Versions==
This engine has been used in [[Human spaceflight|manned]] [[Russian space program]] since the [[Soyuz TM-23]].<ref name=kbhmisaeva-33 /> There are two versions:<ref name=lprd-kbhm />
This engine has been used in [[Human spaceflight|crewed]] [[Russian space program]] since the [[Soyuz TM-23]].<ref name=kbhmisaeva-33 /> There are two versions:<ref name=lprd-kbhm />
* '''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]].<ref name=kbhmisaeva-33 />
* '''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]].<ref name=kbhmisaeva-33 />
* '''S5.142A''': A version of the S5.142 adapted for the [[KVTK (rocket stage)|KVTK]] upper stage for the [[Angara (rocket family)|Angara]] rocket.<ref name=lprd-kbhm />
* '''S5.142A''': A version of the S5.142 adapted for the [[KVTK (rocket stage)|KVTK]] upper stage for the [[Angara (rocket family)|Angara]] rocket.<ref name=lprd-kbhm />
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<ref name=aviadvigatel>{{cite web |url=http://www.k204.ru/books/Aviadvigatel2.pdf |title=Двигатели 1944-2000: Аавиационные, Ракетные, Морские, Промышленные |trans-title=Aviadvigatel 19442-2000: Aviation, rocketry, naval and industry |pages=75–81 |format=PDF |language=Russian |accessdate=2015-07-25}}</ref>
<ref name=aviadvigatel>{{cite web |url=http://www.k204.ru/books/Aviadvigatel2.pdf |title=Двигатели 1944-2000: Аавиационные, Ракетные, Морские, Промышленные |trans-title=Aviadvigatel 19442-2000: Aviation, rocketry, naval and industry |pages=75–81 |format=PDF |language=Russian |accessdate=2015-07-25}}</ref>
<ref name=lprd-kbhm>{{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}}</ref>
<ref name=lprd-kbhm>{{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}}</ref>
<ref name=kbhmisaeva-33>{{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}}</ref>
<ref name=kbhmisaeva-33>{{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 |url-status=dead
|archive-url=https://web.archive.org/web/20130423190227/http://kbhmisaeva.ru/main.php?id=33 |archive-date=23 April 2013}}</ref>
<ref name=kn-soyuzukdu>{{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}}</ref>
<ref name=kn-soyuzukdu>{{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}}</ref>
<ref name=rkke-som>{{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 |author-link=S.P. Korolev Rocket and Space Corporation Energia |name-list-style=amp |website=NASASpaceFlight.com |url-access=subscription }}</ref>
<ref name=rkke-som>{{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 |author-link=S.P. Korolev Rocket and Space Corporation Energia |name-list-style=amp |via=NASASpaceFlight.com |url-access=subscription }}</ref>
<ref name=rsw-soyuzmskdu>{{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}}</ref>
<ref name=rsw-soyuzmskdu>{{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}}</ref>
}}
}}


==External links==
==External links==
* [http://kbhmisaeva.ru/main.php?id=53 KB KhIMMASH Official Page (in Russian)]
* [http://kbhmisaeva.ru/main.php?id=53 KB KhIMMASH Official Page (in Russian)] {{Webarchive|url=https://web.archive.org/web/20130423190210/http://kbhmisaeva.ru/main.php?id=53 |date=2013-04-23 }}


{{Orbital spacecraft rocket engines}}
{{Orbital spacecraft rocket engines}}

Latest revision as of 11:43, 22 February 2024

S5.142
Country of originRussia
Date1990-1996
First flight1996-02-21 (Soyuz TM-23)
DesignerKB KhIMMASH
Applicationattitude control thruster
Predecessor11D427M
StatusRetired
Liquid-fuel engine
PropellantN2O4 / UDMH
Mixture ratio1.85
Cyclepressure fed
Configuration
Chamber1
Nozzle ratio45
Performance
Thrust, vacuum25 N (5.6 lbf)
Chamber pressure0.88 MPa (128 psi)
Specific impulse, vacuum285 s (2.79 km/s)
Burn time25,000 seconds
Restarts300,000
Dimensions
Length180 mm (7.1 in)
Diameter136 mm (5.4 in)
Dry mass0.9 kg (2.0 lb)
Used in
KTDU-80
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]

Versions

[edit]

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]

See also

[edit]

References

[edit]
  1. ^ a b c d e f "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.
  2. ^ "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.
  3. ^ a b Pillet, Nicolas. "Le système de propulsion du vaisseau Soyouz" [The propulsion system of the Soyuz spacecraft] (in French). Kosmonavtika.com. Retrieved 2015-07-14.
  4. ^ a b c "Основные двигатели разработки КБХМ" [The main engines produced by KbKhA] (in Russian). Retrieved 2015-07-25.
  5. ^ a b c 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.
  6. ^ a b Zak, Anatoly (2016-07-07). "Propulsion system for the Soyuz MS spacecraft". Russian Space Web. Retrieved 2016-07-06.
[edit]


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