CE-7.5: Difference between revisions

CE-7.5
Country of origin	India
Date	2002
Designer	LPSC, , Indian Space Research Organisation
Manufacturer	Hindustan Aeronautics Limited; ISRO
Application	Upper-stage booster
Status	In use
Liquid-fuel engine
Propellant	LOX / LH2
Cycle	Staged combustion
Configuration
Chamber	1
Performance
Thrust, vacuum	73.5 kN (16,500 lbf)
Chamber pressure	5.8 MPa (58 bar) / 7.5 MPa (75 bar)
Specific impulse, vacuum	454 seconds (4.45 km/s)
Dimensions
Length	2.14 m (7.0 ft)
Diameter	1.56 m (5.1 ft)
Dry weight	435 kg

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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]^{[citation needed]}
Propellant Combination – LOX / LH2^[6]
Maximum thrust (Vacuum) – 75 kN^[7]
Operating Thrust Range (as demonstrated during GSLV Mk2 D5 flight) – 73.55 kN to 82 kN ^[8]^[2]
Engine Specific Impulse - 454 ± 3 seconds (4.452 ± 0.029 km/s)^[5]^[3]
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 gimbaled 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. First flight attempt took place in April 2010 using GSLV Mk-2 D3 launch vehicle. However the engine failed to ignite.^[2] 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 using GSLV D5.^[10]^[11]

Applications

CE-7.5 is being used in the third stage of ISRO's GSLV Mk-2 rocket.->^{[citation needed]}

References

^ "Cryogenic engine test a big success, say ISRO officials". Indian Express. Retrieved 27 December 2013.
^ ^a ^b ^c "GSLV-D3". ISRO. Retrieved 8 January 2014.
^ ^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)
^ "GSLV MkIII, the next milestone". Frontline. 2014-02-07.
^ ^a ^b ^c "Flight Acceptance Hot Test Of Indigenous Cryogenic Engine Successful". ISRO. Retrieved 8 January 2014.
^ ^a ^b ^c "Indigenous Cryogenic Upper Stage". Retrieved 27 September 2014.
^ ^a ^b ^c "GSLV-D5". ISRO. Retrieved 27 September 2014.
^ "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.
^ "How ISRO developed the indigenous cryogenic engine". The Economic Times.
^ http://www.isro.gov.in/gslv-d5/mission.aspx
^ "Indigenous Cryogenic Upper Stage Successfully Flight Tested On-board GSLV-D5". ISRO. Retrieved 6 January 2014.

[1] "Cryogenic engine test a big success, say ISRO officials". Indian Express. Retrieved 27 December 2013.

[gslvd3-2] "GSLV-D3". ISRO. Retrieved 8 January 2014.

[gslvd3brochure-3] "GSLV-D3 brochure" (PDF). ISRO. Archived from the original (PDF) on February 7, 2014. {{cite web}}: Unknown parameter |deadurl= ignored (|url-status= suggested) (help)

[gslvfrontline-4] "GSLV MkIII, the next milestone". Frontline. 2014-02-07.

[20Dec2008-5] "Flight Acceptance Hot Test Of Indigenous Cryogenic Engine Successful". ISRO. Retrieved 8 January 2014.

[isro-cus20140927-6] "Indigenous Cryogenic Upper Stage". Retrieved 27 September 2014.

[isroGSLVD5-20140927-7] "GSLV-D5". ISRO. Retrieved 27 September 2014.

[isroGSLVD5-launch-vid-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] ttp://www.isro.gov.in/gslv-d5/mission.aspx

[06Jan2013-11] "Indigenous Cryogenic Upper Stage Successfully Flight Tested On-board GSLV-D5". ISRO. Retrieved 6 January 2014.

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 == 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 }}</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=http://web.archive.org/web/20140207165809/http://www.isro.org:80/gslv-d3/pdf/GSLV-D3_GSAT-4%20Brochure.pdf |archivedate=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 ==