Editing Geosynchronous Satellite Launch Vehicle (section)

=== Third stage ===
The third stage of the GSLV Mark II is propelled by the Indian [[CE-7.5]] [[cryogenic rocket engine]] while the older defunct Mark I is propelled using a Russian made [[KVD-1]]. It uses liquid hydrogen (LH<sub>2</sub>) and liquid oxygen (LOX)<ref>{{cite web|url=http://www.isro.gov.in/gslv-d5/gslv-d5.aspx|title=GSLV-D5|access-date=4 January 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> The Indian cryogenic engine was built at the [[Liquid Propulsion Systems Centre]].<ref>{{cite web|url=http://www.spacenews.com/launch/100415isro-cryogenic-engine-fails.html|archive-url=https://archive.today/20120526091518/http://www.spacenews.com/launch/100415isro-cryogenic-engine-fails.html |url-status=dead|archive-date=May 26, 2012|title=ISRO's Cryogenic Stage Fails in Maiden Flight|publisher=SpaceNews|access-date=November 27, 2013}}</ref><ref name=hindu-gslvd3>{{cite news
|url=http://www.hindu.com/2010/01/01/stories/2010010152721100.htm|archive-url=https://web.archive.org/web/20100105175717/http://www.hindu.com/2010/01/01/stories/2010010152721100.htm|url-status=dead|archive-date=5 January 2010|location=Chennai, India|newspaper=The Hindu|title=GSLV, PSLV flights put off|date=1 January 2010}}</ref> The engine has a default thrust of {{cvt|75|kN}} but is capable of a maximum thrust of {{cvt|93.1|kN}}. In GSLV-F14 mission, a new white coloured C15 stage was introduced which has more environmental-friendly manufacturing processes, better insulation properties and the use of lightweight materials.<ref>{{Cite web |title=GSLV-F14/INSAT-3DS Gallery |url=https://www.isro.gov.in/GSLV_F14_INSAT_3DS_gallery.html |access-date=2024-02-08 |website=www.isro.gov.in}}</ref>
[[File:Payload Fairing with GSAT-6A being Integrated.jpg|thumb|upright=1.0|left|Payload fairing with [[GSAT-6A]] being integrated]]