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== Overview ==
== 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 |deadurl=yes |archiveurl=https://web.archive.org/web/20140207165809/http://www.isro.org:80/gslv-d3/pdf/GSLV-D3_GSAT-4%20Brochure.pdf |archivedate=February 7, 2014 |df= }}</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>
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 |deadurl=yes |archiveurl=https://web.archive.org/web/20140207165809/http://www.isro.org/gslv-d3/pdf/GSLV-D3_GSAT-4%20Brochure.pdf |archivedate=February 7, 2014 |df= }}</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 ==
== Specifications ==
The specifications and key characteristics of the engine are:
The specifications and key characteristics of the engine are:
* Operating Cycle – [[Staged combustion cycle (rocket)|Staged combustion]]<ref name=20Dec2008 />
* 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 |accessdate=27 September 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 |accessdate=27 September 2014 |deadurl=yes |archiveurl=https://web.archive.org/web/20140806173146/http://isro.gov.in/gslv-d5/cryogenic-engine.aspx |archivedate=6 August 2014 |df= }}</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 |accessdate=27 September 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 |accessdate=27 September 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 | 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>

Revision as of 12:54, 28 July 2017

CE-7.5
Country of originIndia
First flight15 April 2010 (failure)
5 January 2014 (success)
DesignerLPSC, Indian Space Research Organisation
ManufacturerHindustan Aeronautics Limited
ISRO
ApplicationUpper-stage booster
StatusIn use
Liquid-fuel engine
PropellantLOX / LH2[1]
CycleStaged combustion
Configuration
Chamber1
Performance
Thrust, vacuum73.5 kN (16,500 lbf)[2]
Chamber pressure5.8 MPa (58 bar) / 7.5 MPa (75 bar)
Specific impulse, vacuum454 seconds (4.45 km/s)
Dimensions
Length2.14 m (7.0 ft)
Diameter1.56 m (5.1 ft)
Dry mass435 kg

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.

Overview

CE-7.5 is a regeneratively-cooled, variable-thrust, staged combustion cycle rocket engine.[3][4]

Specifications

The specifications and key characteristics of the engine are:

  • Operating Cycle – Staged combustion[5]
  • Propellant Combination – LOX / LH2[6]
  • Maximum thrust (Vacuum) – 73.55 kN[7]
  • Operating Thrust Range (as demonstrated during GSLV Mk2 D5 flight) – 73.55 kN to 82 kN [2][8]
  • Engine Specific Impulse - 454 ± 3 seconds (4.452 ± 0.029 km/s)[3][5]
  • Engine Burn Duration (Nom) – 720 seconds[7]
  • Propellant Mass – 12800 kg[7]
  • Two independent regulators: thrust control and mixture ratio control[6]
  • Steering during thrust: provided by two gimballed steering engines[6]

Development

ISRO formally started the Cryogenic Upper Stage Project in 1994.[9] The engine successfully completed the Flight Acceptance Hot Test in 2008,[5] 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).[2] On 27th 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. ^ "Cryogenic engine test a big success, say ISRO officials". Indian Express. Retrieved 27 December 2013.
  2. ^ a b c "GSLV-D3". ISRO. Retrieved 8 January 2014.
  3. ^ a b "GSLV-D3 brochure" (PDF). ISRO. Archived from the original (PDF) on February 7, 2014. {{cite web}}: Unknown parameter |deadurl= ignored (|url-status= suggested) (help)
  4. ^ "GSLV MkIII, the next milestone". Frontline. 2014-02-07.
  5. ^ a b c "Flight Acceptance Hot Test Of Indigenous Cryogenic Engine Successful". ISRO. Retrieved 8 January 2014.
  6. ^ a b c "Indigenous Cryogenic Upper Stage". Archived from the original on 6 August 2014. Retrieved 27 September 2014. {{cite web}}: Unknown parameter |deadurl= ignored (|url-status= suggested) (help)
  7. ^ a b c "GSLV-D5". ISRO. Retrieved 27 September 2014.
  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.
  9. ^ "How ISRO developed the indigenous cryogenic engine". The Economic Times.
  10. ^ http://www.isro.gov.in/gslv-d5/mission.aspx
  11. ^ "Indigenous Cryogenic Upper Stage Successfully Flight Tested On-board GSLV-D5". ISRO. Retrieved 6 January 2014.
  12. ^ http://www.isro.gov.in/launchers/gslv

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