CE-7.5: Difference between revisions

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{{Short description|Cryogenic rocket engine developed by the Indian Space Research Organisation}}
{{Use dmy dates|date=May 2019}}
{{Use dmy dates|date=May 2019}}
{{infobox rocket engine
{{infobox rocket engine
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   |length={{convert|2.14|m|ft|abbr=on}}  
   |length={{convert|2.14|m|ft|abbr=on}}  
   |dry_weight=435 kg
   |dry_weight=435 kg
|used_in=Upper stage of [[Geosynchronous Satellite Launch Vehicle|GSLV Mk.II]]}}
|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.
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 ==
== Overview ==
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* 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>
* 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&nbsp;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>
* Maximum thrust (Vacuum) – 73.55&nbsp;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&nbsp;kN to 82&nbsp;kN <ref name=gslvd3 /><ref name=isroGSLVD5-launch-vid>{{cite web |url=https://www.youtube.com/watch?v=Y7HIvfhoFHM#t=3024 | 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}}</ref>
* Operating Thrust Range (as demonstrated during GSLV Mk2  D5 flight) – 73.55&nbsp;kN to 82&nbsp;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 Specific Impulse - {{convert|454|±|3|isp}}<ref name=gslvd3brochure /><ref name=20Dec2008 />
* Engine Burn Duration (Nom) – 720 seconds<ref name=isroGSLVD5-20140927 />
* Engine Burn Duration (Nom) – 720 seconds<ref name=isroGSLVD5-20140927 />
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== Applications ==
== Applications ==
CE-7.5 is being used in the third stage of ISRO's GSLV Mk.II rocket.<ref>http://www.isro.gov.in/launchers/gslv</ref>
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 ==
== See also ==

Revision as of 13:32, 12 January 2022


Template:Infobox rocket engine 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.[1]

Overview

CE-7.5 is a regeneratively-cooled, variable-thrust, staged combustion cycle rocket engine.[2][3]

Specifications

The specifications and key characteristics of the engine are:

  • Operating Cycle – Staged combustion[4]
  • Propellant Combination – LOX / LH2[5]
  • Maximum thrust (Vacuum) – 73.55 kN[6]
  • Operating Thrust Range (as demonstrated during GSLV Mk2 D5 flight) – 73.55 kN to 82 kN [7][8]
  • Engine Specific Impulse - 454 ± 3 seconds (4.452 ± 0.029 km/s)[2][4]
  • Engine Burn Duration (Nom) – 720 seconds[6]
  • Propellant Mass – 12,800 kg[6]
  • Two independent regulators: thrust control and mixture ratio control[5]
  • Steering during thrust: provided by two gimballed steering engines[5]

Development

ISRO formally started the Cryogenic Upper Stage Project in 1994.[9] The engine successfully completed the Flight Acceptance Hot Test in 2008,[4] 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).[7] 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.[10][11]

Applications

CE-7.5 is being used in the third stage of ISRO's GSLV Mk.II rocket.[12]

See also

References

  1. ↑ Ramachandran, R. "Russian route". Frontline. Archived from the original on 24 October 2020. Retrieved 17 August 2021.
  2. ↑ 2.0 2.1 "GSLV-D3 brochure" (PDF). ISRO. Archived from the original (PDF) on 7 February 2014.
  3. ↑ "GSLV MkIII, the next milestone". Frontline. 7 February 2014.
  4. ↑ 4.0 4.1 4.2 "Flight Acceptance Hot Test Of Indigenous Cryogenic Engine Successful". ISRO. Retrieved 8 January 2014.
  5. ↑ 5.0 5.1 5.2 "Indigenous Cryogenic Upper Stage". Archived from the original on 6 August 2014. Retrieved 27 September 2014.
  6. ↑ 6.0 6.1 6.2 "GSLV-D5". ISRO. Archived from the original on 6 October 2014. Retrieved 27 September 2014.
  7. ↑ 7.0 7.1 Cite error: Invalid <ref> tag; no text was provided for refs named gslvd3
  8. ↑ "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". Doordarshan National TV. Archived from the original on 21 December 2021.
  9. ↑ "How ISRO developed the indigenous cryogenic engine". The Economic Times.
  10. ↑ "Archived copy". Archived from the original on 4 January 2014. Retrieved 5 January 2014.{{cite web}}: CS1 maint: archived copy as title (link)
  11. ↑ "Indigenous Cryogenic Upper Stage Successfully Flight Tested On-board GSLV-D5". ISRO. Archived from the original on 8 January 2014. Retrieved 6 January 2014.
  12. ↑ "GSLV - Isro".

Template:Rocket engines

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