CleanupBot II at 20:11, 13 August 2023

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{{Short description|Cryogenic rocket engine developed by the Indian Space Research Organisation}}
{{Use dmy dates|date=May 2019}}
{{infobox rocket engine
|image=File:Indigenous Cryogenic Upper Stage of GSLV-F09 at Stage Preparation Facility.jpg
|image_size=
|caption=The CUS15 upper stage of GSLV-F09 powered by the CE-7.5 engine at Stage Preparation Facility
|name=CE-7.5
|country_of_origin=[[India]]
|designer=[[Liquid Propulsion Systems Centre|LPSC]], [[Indian Space Research Organisation]]
|manufacturer=[[Hindustan Aeronautics|Hindustan Aeronautics Limited]]<br>[[Indian Space Research Organisation|ISRO]]
|first_date=15 April 2010 (failure) <br />5 January 2014 (success)
|purpose=Upper-stage booster
|predecessor=
|status=In use
|cycle=[[Staged combustion cycle (rocket)|Staged combustion]]
|type=liquid
|fuel=[[LH2]]<ref>{{cite web |url=http://www.newindianexpress.com/states/kerala/article1521560.ece |title=Cryogenic engine test a big success, say ISRO officials |author= |website=Indian Express |access-date=27 December 2013}}</ref>
|oxidiser=[[LOX]]
|capacity=
|combustion_chamber=1
|nozzle_ratio=
|thrust(SL)=
|thrust(Vac)={{convert|73.5|kN|lbf|abbr=on}}<ref name=gslvd3>{{cite web|title=GSLV-D3|url=http://www.isro.org/gslv-d3/gslv-d3.aspx|archive-url=https://web.archive.org/web/20100416141241/http://isro.org/gslv-d3/gslv-d3.aspx|url-status=dead|archive-date=16 April 2010|publisher=ISRO|access-date=8 January 2014}}</ref>
|specific_impulse_vacuum={{convert|454|isp}}
|specific_impulse_sea_level=
|chamber_pressure={{convert|5.8|MPa|bar|abbr=on}} / {{convert|7.5|MPa|bar|abbr=on}}
|thrust_to_weight=
|diameter={{convert|1.56|m|ft|abbr=on}}
|length={{convert|2.14|m|ft|abbr=on}}
|dry_weight=435 kg
|used_in=Upper stage of [[Geosynchronous_Satellite_Launch_Vehicle|GSLV Mk.II]]}}
The '''CE-7.5''' is a [[cryogenic rocket engine]] developed by the [[Indian Space Research Organisation]] to power the upper stage of its [[GSLV]] Mk-2 launch vehicle. The engine was developed as a part of the Cryogenic Upper Stage Project (CUSP). It replaced the [[KVD-1]] (RD-56) Russian cryogenic engine that powered the upper stage of [[GSLV]] Mk-1.<ref>{{Cite web|last=Ramachandran|first=R.|title=Russian route|url=https://frontline.thehindu.com/cover-story/russian-route/article5596598.ece|url-status=live|archive-url=https://web.archive.org/web/20201024211229/https://frontline.thehindu.com/cover-story/russian-route/article5596598.ece|archive-date=24 October 2020|access-date=2021-08-17|website=Frontline|language=en}}</ref>

== Overview ==
CE-7.5 is a regeneratively-cooled, [[Throttleable rocket engine|variable-thrust]], staged combustion cycle [[rocket engine]].<ref name=gslvd3brochure>{{cite web |url=http://www.isro.org/gslv-d3/pdf/GSLV-D3_GSAT-4%20Brochure.pdf |title=GSLV-D3 brochure |publisher=ISRO |url-status=dead |archive-url=https://web.archive.org/web/20140207165809/http://www.isro.org/gslv-d3/pdf/GSLV-D3_GSAT-4%20Brochure.pdf |archive-date=February 7, 2014 }}</ref><ref name=gslvfrontline>{{cite news |url=http://www.frontline.in/cover-story/gslv-mkiii-the-next-milestone/article5596588.ece |title=GSLV MkIII, the next milestone |work=Frontline |date=2014-02-07 }}</ref>

== Specifications ==
The specifications and key characteristics of the engine are:
* Operating Cycle – [[Staged combustion cycle (rocket)|Staged combustion]]<ref name=20Dec2008 />
* Propellant Combination – [[LOX]] / [[LH2]]<ref name=isro-cus20140927>{{cite web |url=http://www.isro.gov.in/gslv-d5/cryogenic-engine.aspx |title=Indigenous Cryogenic Upper Stage |access-date=27 September 2014 |url-status=dead |archive-url=https://web.archive.org/web/20140806173146/http://isro.gov.in/gslv-d5/cryogenic-engine.aspx |archive-date=6 August 2014 }}</ref>
* Maximum thrust (Vacuum) – 73.55 kN<ref name=isroGSLVD5-20140927>{{cite web |url=http://www.isro.gov.in/gslv-d5/gslv-d5.aspx |title=GSLV-D5 |publisher=ISRO |access-date=27 September 2014 |url-status=dead |archive-url=https://web.archive.org/web/20141006082545/http://www.isro.gov.in/gslv-d5/gslv-d5.aspx |archive-date=6 October 2014 }}</ref>
* Operating Thrust Range (as demonstrated during GSLV Mk2 D5 flight) – 73.55 kN to 82 kN <ref name=gslvd3 /><ref name=isroGSLVD5-launch-vid>{{cite web |url=https://www.youtube.com/watch?v=Y7HIvfhoFHM#t=3024 |archive-url=https://ghostarchive.org/varchive/youtube/20211221/Y7HIvfhoFHM |archive-date=2021-12-21 |url-status=live| title=GSLV-D5 launch video – CE-7.5 thrust was uprated by 9.5% to 82 kN and then brought back to nominal thrust of 73.55 kN | publisher=Doordarshan National TV}}{{cbignore}}</ref>
* Engine Specific Impulse - {{convert|454|±|3|isp}}<ref name=gslvd3brochure /><ref name=20Dec2008 />
* Engine Burn Duration (Nom) – 720 seconds<ref name=isroGSLVD5-20140927 />
* Propellant Mass – 12,800 kg<ref name=isroGSLVD5-20140927 />
* Two independent regulators: thrust control and mixture ratio control<ref name=isro-cus20140927 />
* Steering during thrust: provided by two gimballed steering engines<ref name=isro-cus20140927 />

== Development ==
[[ISRO]] formally started the Cryogenic Upper Stage Project in 1994.<ref>{{cite web|url=http://articles.economictimes.indiatimes.com/2014-01-09/news/46030395_1_cryogenic-engine-mahendragiri-isro|title=How ISRO developed the indigenous cryogenic engine|work=The Economic Times}}</ref> The engine successfully completed the Flight Acceptance Hot Test in 2008,<ref name="20Dec2008">{{cite web|url=http://www.isro.gov.in/hi/node/591|title=Flight Acceptance Hot Test Of Indigenous Cryogenic Engine Successful|publisher=ISRO|access-date=8 January 2014}}</ref> and was integrated with propellant tanks, third-stage structures and associated feed lines for the first launch. The first flight attempt took place in April 2010 during the GSLV Mk.II D3/GSAT-3 mission. The engine ignited, but the ignition did not sustain as the Fuel Booster Turbo Pump (FBTP) shut down after reaching a speed of about 34,500 rpm 480 milliseconds after ignition, due to the FBTP being starved of Liquid Hydrogen (LH2).<ref name=gslvd3 /> On 27 March 2013 the engine was successfully tested under vacuum conditions. The engine performed as expected and was qualified to power the third stage of the GSLV Mk-2 rocket. On 5 January 2014 the cryogenic engine performed successfully and launched the [[GSAT-14]] satellite in the GSLV-D5/GSAT-14 mission.<ref>{{cite web |url=http://www.isro.gov.in/gslv-d5/mission.aspx |title=Archived copy |access-date=2014-01-05 |url-status=dead |archive-url=https://web.archive.org/web/20140104230506/http://www.isro.gov.in/gslv-d5/mission.aspx |archive-date=2014-01-04 }}</ref><ref name=06Jan2013>{{cite web|title=Indigenous Cryogenic Upper Stage Successfully Flight Tested On-board GSLV-D5|url=http://www.isro.org/pressrelease/scripts/pressreleasein.aspx?Jan06_2014|publisher=ISRO|access-date=6 January 2014|archive-url=https://web.archive.org/web/20140108174921/http://www.isro.org/pressrelease/scripts/pressreleasein.aspx?Jan06_2014|archive-date=8 January 2014|url-status=dead}}</ref>

== Applications ==
CE-7.5 is being used in the third stage of ISRO's GSLV Mk.II rocket.<ref>{{Cite web|url=http://www.isro.gov.in/launchers/gslv|title = GSLV - Isro}}</ref>

== See also ==

* [[CE-20]]
* [[GSLV]]

== References ==
{{Reflist|30em}}

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

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

[[Category:Rocket engines of India]]
[[Category:Rocket engines using hydrogen propellant]]
[[Category:Rocket engines using the staged combustion cycle]]

CE-7.5 - Revision history

CleanupBot II at 20:11, 13 August 2023