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	==See also==		==See also==
	~~{{Portal\|Spaceflight\|India}}~~
	* [[CE-7.5]]		* [[CE-7.5]]
	* [[Geosynchronous Satellite Launch Vehicle Mk III]]		* [[Geosynchronous Satellite Launch Vehicle Mk III]]

>Monkbot: Task 18 (cosmetic): eval 21 templates: del empty params (4×); hyphenate params (5×);

2020-11-29T07:58:12Z

Task 18 (cosmetic): eval 21 templates: del empty params (4×); hyphenate params (5×);

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{{Infobox rocket engine
|name =CE-20
|image =CE-20 Engine Config Model.png
|image_size =250
|caption =A computer model of CE-20
|country_of_origin=[[India]]
|date =
|first_date =June 5, 2017
|last_date =
|designer =[[Liquid Propulsion Systems Centre|LPSC]], [[Indian Space Research Organisation|ISRO]]
|manufacturer =[[Hindustan Aeronautics Limited|HAL]]<ref>{{cite web|url=http://www.thehindu.com/sci-tech/hal-to-produce-cryogenic-engines-for-isro/article4661042.ece|title=HAL to produce cryogenic engines for ISRO|date=27 April 2013|work=The Hindu}}</ref>
|purpose =Upper stage booster
|associated =
|predecessor =
|successor =
|status =Active

|type =liquid
|oxidiser =[[LOX]]
|fuel =[[LH2]]
|mixture_ratio =5.05
|cycle =[[Gas-generator cycle (rocket)|Gas Generator]]
|pumps =

|description =
|combustion_chamber=1
|nozzle_ratio =100

|thrust =
|thrust_at_altitude=
|thrust(Vac) ={{convert|200|kN|lbf|abbr=on}}
|thrust(SL) =
|throttle_range ={{convert|180|–|220|kN|lbf|abbr=on}}
|thrust_to_weight=
|chamber_pressure={{convert|6|MPa|abbr=on}}
|specific_impulse=
|specific_impulse_vacuum={{convert|443|±|3|isp}}
|specific_impulse_sea_level=
|total_impulse =
|burn_time =640-800 seconds
|restarts =
|gimbal =
|capacity =

|dimensions =
|length =
|diameter =
|dry_weight ={{convert|588|kg|abbr=on}}

|used_in =Upper stage of [[Geosynchronous Satellite Launch Vehicle Mk III|GSLV Mk.III]]

|references =<ref name="AeroIndia2009_LPSC_1" /><ref name="AeroIndia2009_LPSC_2" />
|notes =
}}

The '''CE-20''' is a [[cryogenic rocket engine]] developed by the [[Liquid Propulsion Systems Centre]], a subsidiary of [[Indian Space Research Organisation]]. It has been developed to power the upper stage of the [[Geosynchronous Satellite Launch Vehicle Mk III]].<ref name="test">{{cite web|url=https://www.isro.gov.in/update/12-may-2012/indigenous-cryogenic-engine-tested-successfully|title=Indigenous Cryogenic Engine Tested Successfully|website=www.isro.gov.in}}</ref> It is the first Indian cryogenic engine to feature a [[gas-generator cycle]].<ref>{{cite web|author1=K. S. Jayaram|title=India's heavy-lift rocket on track for December debut following engine test|url=http://spacenews.com/indias-heavy-lift-rocket-on-track-for-december-debut-following-engine-test/|website=SpaceNews.com|date=22 February 2016}}</ref> The high thrust cryogenic engine is one of
the most powerful upper stage cryogenic engines in the world.<ref>{{cite journal|last1=Praveen|first1=RS|last2=Jayan|first2=N|last3=Bijukumar|first3=KS|last4=Jayaprakash|first4=J|last5=Narayanan|first5=V|last6=Ayyappan|first6=G|title=Development of Cryogenic Engine for GSLV MkIII: Technological Challenges|journal=IOP Conference Series: Materials Science and Engineering|date=February 2017|volume=171|pages=012059|doi=10.1088/1757-899X/171/1/012059|doi-access=free}}</ref>

==Overview==
The CE-20 is the first Indian [[cryogenic engine]] to feature a [[Gas-generator cycle (rocket)|gas-generator cycle]].<ref>{{cite web|author1=R. Ramachandran|title=GSLV MkIII, the next milestone|url=http://www.frontline.in/cover-story/gslv-mkiii-the-next-milestone/article5596588.ece|website=Frontline|language=en|date=22 January 2014}}</ref> The engine produces a nominal thrust of 200 kN, but has an operating thrust range between 180 kN to 220 kN and can be set to any fixed values between them. The combustion chamber burns liquid hydrogen and liquid oxygen at 6 MPa with 5.05 engine mixture ratio.<ref name="AeroIndia2009_LPSC_1">{{Cite web|url=http://www.bharat-rakshak.com/media/AeroIndia2009/krishG/IMG_0027.JPG.html|title=LPSC Handouts at Aer India-2009|date=2009-03-13|work=Specifications of CE-20|publisher=Liquid Propulsion Systems Centre|access-date=2009-08-29|df=dmy-all}}</ref><ref name="AeroIndia2009_LPSC_2">{{Cite web|url=http://www.bharat-rakshak.com/media/AeroIndia2009/krishG/IMG_0159.JPG.html|title=Aero India 2009, LPSC specification sheet :: IMG_0159|access-date=2018-09-12}}</ref> The engine has a [[thrust-to-weight ratio]] of 34.7 and a [[specific impulse]] of {{convert|444|isp}} in vacuum.

==Development and Testing==
[[File:CE20 Engine 640 second test Front.jpg|thumb|left|CE-20 during static testing at Cryo Main Engine and Static Test facility (CMEST) of ISRO Propulsion Complex (IPRC), Mahendragiri on 19 February 2016]]
* On 28 April 2015, CE-20 cleared a 635 seconds long duration hot test at IPRC, Mahendragiri test facility. This test was preceded by two cold start tests and four short duration hot tests.<ref>{{cite news|last1=Ram|first1=Arun|title=Isro’s desi cryogenic engine test successful - Times of India|url=https://timesofindia.indiatimes.com/india/Isros-desi-cryogenic-engine-test-successful/articleshow/47090046.cms|work=The Times of India|date=29 April 2015}}</ref>
* On 16 July 2015, the first developmental CE-20 engine 'E1' was successfully endurance hot tested at ISRO Propulsion Complex, Mahendragiri for a duration of 800 seconds with Mixture Ratio Controller (MRC) in closed loop mode. This duration is approximately 25% more than the engine burn duration in flight. This was tenth development test for CE-20 <ref>{{cite web|url=https://www.isro.gov.in/update/20-jul-2015/indigenously-developed-high-thrust-cryogenic-rocket-engine-successfully-ground|title=Indigenously Developed High Thrust Cryogenic Rocket Engine Successfully Ground Tested for a duration for 800 seconds - ISRO|website=www.isro.gov.in}}</ref>
* On 10 August 2015, a short duration (5.7 seconds) hot test on the CE20 engine was done to demonstrate the successful engine ignition with tank pressure conditions as in flight.<ref>{{cite web|title=Year End Review: Achievements of Department of Space during the year 2015|url=http://pib.nic.in/newsite/PrintRelease.aspx?relid=133949|website=Press Information Bureau, Government of India|access-date=12 February 2018}}</ref>
* On 19 February 2016, the second developmental CE-20 engine 'E2'<ref>{{Cite web|url=https://www.isro.gov.in/update/22-feb-2016/ce-20-engine-of-gslv-mkiii-successfully-hot-tested|title=CE 20 Engine of GSLV MKIII successfully hot tested - ISRO|website=www.isro.gov.in|language=en|access-date=2018-02-12}}</ref> was hot-tested for a duration of 640 seconds with Mixture Ratio Controller (MRC) in closed loop mode at ISRO Propulsion Complex, Mahendragiri.<ref>{{cite news|title=ISRO upbeat as indigenous cryo engine passes test|url=http://www.thehindu.com/sci-tech/science/isro-upbeat-as-indigenous-cryo-engine-passes-test/article8258313.ece|work=The Hindu|date=20 February 2016|language=en-IN}}</ref><ref>{{cite news|title=ISRO successfully conducts hot test of Cryo CE 20 engine|url=http://www.thehindubusinessline.com/news/science/isro-successfully-conducts-hot-test-of-cryo-ce-20-engine/article8258080.ece|access-date=12 February 2018|agency=Press Trust of India|publisher=The Hindu|date=19 Feb 2016}}</ref><ref>{{cite news|title=ISRO successfully conducts hot test of Cryo CE 20 engine|url=https://economictimes.indiatimes.com/news/science/isro-successfully-conducts-hot-test-of-cryo-ce-20-engine/articleshow/51060286.cms|access-date=12 February 2018|agency=PTI|date=19 Feb 2016}}</ref>
* On 03 December 2016, flight acceptance test of 25 seconds in high altitude conditions was carried out on third developmental CE-20 engine (E3).<ref>{{cite web|title=High Altitude Flight Acceptance Test of CE20 Engine Conducted Successfully|url=https://www.isro.gov.in/high-altitude-flight-acceptance-test-of-ce20-engine-conducted-successfully|access-date=12 February 2018}}</ref><ref>{{cite web|url=http://www.thehindu.com/sci-tech/science/GSLV-engine-tested-at-Mahendragiri/article16756493.ece|title=GSLV engine tested at Mahendragiri|date=3 December 2016|work=The Hindu}}</ref><ref name=":0">{{Cite news|url=https://www.isro.gov.in/sites/default/files/article-files/node/7064/outcomebudget2016-2017.pdf|title=Department of Space Outcome Budget 2016-17|access-date=12 October 2018}}</ref> It was successfully flown on the first developmental flight 'D1' of the GSLV Mk-III on 5 June 2017.<ref>{{Cite news|url=http://www.space.com/37093-india-launches-most-powerful-rocket-yet.html|title=India Just Launched Its Heaviest & Most Powerful Rocket Yet|last=Malik|first=Tariq|date=2017-06-05|work=Space.com|access-date=2017-06-07|df=dmy-all}}</ref>
*On 25 January 2017, CE-20 engine E2<ref name=":0" /> integrated with development stage for GSLV Mk III, C25 'D' was tested for duration of 50 seconds.<ref>{{Cite web|url=https://www.isro.gov.in/update/26-jan-2017/isro-successfully-tests-c25-cryogenic-upper-stage-of-gslv-mkiii|title=ISRO Successfully Tests C25 Cryogenic Upper Stage of GSLV MkIII - ISRO|website=www.isro.gov.in|language=en|access-date=2018-10-12}}</ref>
*On 17 February 2017, CE-20 engine E2<ref name=":0" /> integrated with development stage for GSLV Mk III, C25 'D' was tested for duration of 640 seconds.<ref>{{Cite web|url=https://www.isro.gov.in/update/18-feb-2017/isro-successfully-tests-its-cryogenic-stage-c25-gslv-mkiii-flight-duration|title=ISRO Successfully Tests its Cryogenic Stage (C25) for GSLV MkIII for the Flight Duration - ISRO|website=www.isro.gov.in|language=en|access-date=2018-10-12}}</ref>
*On 11 October 2018, CE-20 engine E6 completed 25 second long flight acceptance test in high altitude conditions for GSLV Mk III M1/Chandrayaan-2 mission<ref>{{Cite web|url=https://www.isro.gov.in/update/12-oct-2018/isro-successfully-tests-cryogenic-engine-ce-20-gslv-mk-iii-chandrayaan-2-mission|title=ISRO successfully tests Cryogenic Engine (CE-20) for GSLV Mk-III / Chandrayaan-2 Mission - ISRO|website=www.isro.gov.in|language=en|access-date=2018-10-12}}</ref>

==See also==
{{Portal|Spaceflight|India}}
* [[CE-7.5]]
* [[Geosynchronous Satellite Launch Vehicle Mk III]]
* [[GSAT-14]]

==References==
{{Reflist}}

==External links==
* [http://timesofindia.indiatimes.com/india/GSLV-Mk-III-project-on-course-as-India-test-fires-indigenous-cryo-engine-for-800-seconds/articleshow/48145813.cms India test-fires indigenous cryo engine for 800 seconds]
* [http://www.bharat-rakshak.com/media/AeroIndia2009/krishG/IMG_0027.JPG.html LPSC handouts during Aero India-2009 with Ce-20 specifications]
* [http://www.bharat-rakshak.com/media/AeroIndia2009/krishG/IMG_0159.JPG.html LPSC handouts during Aero India-2009 with specifications of all Liquid-fueled engines of India]
* [https://web.archive.org/web/20090726124921/http://www.isro.org/rep2009/citizens.htm Status of CE-20 in Space Transportation/GSLV - Mk III of ISRO's 2008-09 Annual Report]
* http://www.thehindu.com/sci-tech/science/isro-upbeat-as-indigenous-cryo-engine-passes-test/article8258313.ece#

{{Indian space programme}}
{{Rocket engines}}

{{Use Indian English|date=January 2014}}

{{DEFAULTSORT:Ce-25}}
[[Category:Rocket engines of India]]
[[Category:Rocket engines using hydrogen propellant]]
[[Category:Rocket engines using the gas-generator cycle]]

CE-20 - Revision history

Vikipft: cleaned up page per sources

CleanupBot II: Removed empty portal template using script

>Monkbot: Task 18 (cosmetic): eval 21 templates: del empty params (4×); hyphenate params (5×);