LVM3

File:LVM3-X Vehicle Configuration.jpg

ISRO initially planned two launcher families, the Polar Satellite Launch Vehicle for low Earth orbit and polar launches and the larger Geosynchronous Satellite Launch Vehicle for payloads to geostationary transfer orbit (GTO). The vehicle was reconceptualized as a more powerful launcher as the ISRO mandate changed. This increase in size allowed the launch of heavier communication and multipurpose satellites, human-rating to launch crewed missions, and future interplanetary exploration.[https://www.ndtv.com/india-news/isro-not-to-fly-living-being-before-actual-manned-space-mission-official-1916654 ISRO Not To Fly Living Being Before Actual Manned Space Mission: Official]. NDTV Indo-Asian News Service. 14 September 2018. Development of the LVM3 began in the early 2000s, with the first launch planned for 2009–2010.{{Cite web |title=Lok Sabha Unstarred Question No.3713 |url=https://www.isro.gov.in/sites/default/files/lu_3713.pdf |archive-url=https://web.archive.org/web/20200129131043/https://www.isro.gov.in/sites/default/files/lu_3713.pdf |archive-date=29 January 2020 |quote=The GSLV MkIII programme was initiated in 2002 as a heavy-lift launch vehicle to launch communications satellites weighing up to 4 tons into Geosynchronous Transfer Orbit (GTO) within a time frame of 7 years.}}{{Cite news |date=2002-08-17 |title=Development of GSLV-Mk III approved |url=https://economictimes.indiatimes.com/news/economy/policy/development-of-gslv-mk-iii-approved/articleshow/19366947.cms |access-date=2024-03-22 |work=The Economic Times |issn=0013-0389}}{{Cite web|url = http://www.sawfnews.com/Health/70695.aspx|title = India's GSLV Mk-3 First Flight Pushed Back to April 2014|date = 4 April 2013|access-date = 19 December 2014|website = Sawfnews|url-status = usurped|archive-url = https://web.archive.org/web/20130410172341/http://www.sawfnews.com/Health/70695.aspx|archive-date = 10 April 2013}} The unsuccessful launch of GSLV D3, due to failure in the cryogenic upper stage, delayed the LVM3 development program.{{Cite news |last=Pulakkat |first=Hari |title=GSLV Mark III launch: Why ISRO's biggest challenge will be at the end of this month |work=The Economic Times |url=https://economictimes.indiatimes.com/news/science/gslv-mark-iii-launch-why-isros-biggest-challenge-will-be-at-the-end-of-this-month/articleshow/58466879.cms |access-date=2022-08-23 |quote=Isro had gone through a difficult period a few years ago, when a launch of its GSLV Mark II failed. This failure had its impact on GSLV Mark III as well. “Because we had problems with Mark II,” says Isro chairman Kiran Kumar, “we had to rework some facilities of Mark III for Mark II. So Mark III got slightly delayed.”}}{{Cite web |title=GSLV Mk-III to put India on top |url=https://www.newindianexpress.com/states/tamil-nadu/2017/feb/26/gslv-mk-iii-to-put-india-on-top-1574839.html |access-date=2022-08-23 |website=The New Indian Express |date=26 February 2017 |quote=The failure of GSLV-D3 in 2010, where the first indigenous Cryogenic Upper Stage (CUS) was flight-tested, impacted the C25 stage programme due to the priority assigned for the additional investigation tests and added qualification tests demanded on CUS engine systems.}} The LVM3, although named "GSLV mark III" during development, features different systems and components from the GSLV mark II.

To manufacture the LVM3 in public–private partnership (PPP) mode, ISRO and NewSpace India Limited (NSIL) have started working on the project. To investigate possible PPP partnership opportunities for LVM3 production through the Indian private sector, NSIL has hired IIFCL Projects Limited (IPL).{{Cite web |date=19 January 2024 |title=NewSpace India Limited (NSIL) and ISRO convene Stakeholders' Conference for manufacturing the Heaviest Launcher LVM-3 of ISRO, under a PPP partnership with Indian Industry to meet the emerging Global Launch Service market needs |url=https://www.nsilindia.co.in/sites/default/files/Final%20Release%20Version%20Press%20Release_Stakeholders%20conference.pdf}} On Friday 10 May 2024, NSIL released a request for qualification (RFQ), inviting responses from private partners for the large-scale production of LVM-3.{{Cite web |last1=Pillai |first1=Soumya |last2=ThePrint |date=2024-05-11 |title=ISRO commercial arm invites private players to build LVM3 rocket that delivered Chandrayaan mission |url=https://theprint.in/science/isro-commercial-arm-invites-private-players-to-build-lvm3-rocket-that-delivered-chandrayaan-mission/2079535/ |access-date=2024-05-11 |website=ThePrint |language=en-US}}{{Cite web |last=Simhan |first=T. E. Raja |date=2024-05-10 |title=NSIL releases RFQ document inviting industry players to productionalise ISRO's heavy lift launcher LVM3 |url=https://www.thehindubusinessline.com/news/nsil-releases-rfq-document-inviting-industry-players-to-productionalise-isros-heavy-lift-launcher-lvm3/article68161469.ece |access-date=2024-05-11 |website=www.thehindubusinessline.com |language=en}}{{Cite web |date=2024-05-10 |title=India's NSIL partners with private sector to boost LVM3 production |url=https://www.indiatoday.in/science/story/indias-nsil-partners-with-private-sector-to-boost-lvm3-production-2537611-2024-05-10 |access-date=2024-05-11 |website=India Today |language=en}} Plans call for a 14-year partnership between ISRO and the chosen commercial entity. The private partner is expected to be able to produce four to six LVM3 rockets annually over the following twelve years, with the first two years serving as the "development phase" for the transfer of technology and know-how.{{Cite web |last=Dutt |first=Anonna |date=2024-05-27 |title=LVM3 commercialisation is a big step forward, at right time for India, say experts |url=https://indianexpress.com/article/technology/science/lvm3-commercialisation-is-a-big-step-forward-at-right-time-for-india-say-experts-9353776/ |access-date=2024-05-27 |website=The Indian Express |language=en}}

File:LVM3 M4 - S200 Strap-on thrusting and seperation, onboard camera footage.webm

The first stage consists of two S200 solid motors, also known as Large Solid Boosters (LSB) attached to the core stage. Each booster is {{convert|3.2|m|ft}} wide, {{convert|25|m|ft}} long, and carries {{convert|207|t|lb}} of hydroxyl-terminated polybutadiene (HTPB) based propellant in three segments with casings made out of M250 maraging steel. The head-end segment contains 27,100 kg of propellant, the middle segment contains 97,380 kg and the nozzle-end segment is loaded with 82,210 kg of propellants. It is the largest solid-fuel booster after the SLS SRBs, the Space Shuttle SRBs and the Ariane 5 SRBs. The flex nozzles can be vectored up to ±8° by electro-hydraulic actuators with a capacity of {{convert|294|kN|}} using hydro-pneumatic pistons operating in blow-down mode by high pressure oil and nitrogen. They are used for vehicle control during the initial ascent phase.{{cite web |title=S200 solid booster development |url=http://iafastro.directory/iac/archive/browse/IAC-10/C4/2/8908/ |access-date=11 May 2021}}{{cite news|url=http://www.thehindu.com/todays-paper/tp-features/tp-sci-tech-and-agri/gslv-mark-iii-faces-its-first-experimental-flight/article6660089.ece|title=GSLV Mark III faces its first experimental flight|author=N. Gopal Raj|work=The Hindu|date=3 December 2014 }} Hydraulic fluid for operating these actuators is stored in an externally mounted cylindrical tank at the base of each booster.{{cite web |title=LVM3-CARE mission brochure |url=https://www.isro.gov.in/sites/default/files/flipping_book/LVM-3/CARE/files/assets/common/downloads/LVM3-brochure.pdf |access-date=11 May 2021 |archive-date=11 October 2021 |archive-url=https://web.archive.org/web/20211011095054/https://www.isro.gov.in/sites/default/files/flipping_book/LVM-3/CARE/files/assets/common/downloads/LVM3-brochure.pdf |url-status=dead }} These boosters burn for 130 seconds and produce an average thrust of {{convert|3578.2|kN|}} and a peak thrust of {{convert|5150|kN|}} each. The simultaneous separation from core stage occurs at T+149 seconds in a normal flight and is initiated using pyrotechnic separation devices and six small solid-fueled jettison motors located in the nose and aft segments of the boosters.{{cite web|title=GSLV Mk. III Launch Vehicle Overview|url=http://www.spaceflight101.net/gslv-mk-iii.html|website=Spaceflight 101|access-date=11 February 2018|archive-url=https://web.archive.org/web/20180211032829/http://www.spaceflight101.net/gslv-mk-iii.html|archive-date=11 February 2018|location=Wayback Machine}}{{cite web|url=http://www.isro.org/pressrelease/contents/2010/pdf/S200_STATIC_TEST-01.pdf|title=ISRO Press Release: S200 First Static Test (S-200-ST-01)|access-date=17 June 2017|url-status=dead|archive-url=https://web.archive.org/web/20130311191452/http://isro.org/pressrelease/contents/2010/pdf/S200_STATIC_TEST-01.pdf|archive-date=11 March 2013}}

The first static fire test of the S200 solid rocket booster, ST-01, was conducted on 24 January 2010. The booster fired for 130 seconds and had nominal performance throughout the burn. It generated a peak thrust of about {{cvt|500|tf|kN lbf|order=out}}.{{Cite web|url=https://www.isro.gov.in/update/24-jan-2010/successful-static-testing-of-solid-propellant-booster-rocket-stage-s200-gslv-mk|title=Successful static testing of Solid Propellant Booster Rocket Stage S200 for GSLV Mk III Launch Vehicle|website=www.isro.gov.in|language=en|access-date=12 February 2018|archive-date=11 October 2021|archive-url=https://web.archive.org/web/20211011094949/https://www.isro.gov.in/update/24-jan-2010/successful-static-testing-of-solid-propellant-booster-rocket-stage-s200-gslv-mk|url-status=dead}}{{cite web|url=http://www.dnaindia.com/scitech/report_isro-successfully-tests-world-s-3rd-largest-solid-booster_1338945|title=Isro successfully tests world's 3rd largest solid booster|work=dna|access-date=4 October 2014}} A second static fire test, ST-02, was conducted on 4 September 2011. The booster fired for 140 seconds and again had nominal performance through the test.{{Cite web|url=http://www.vssc.gov.in/VSSC_V4/images/NewsLetter/apr2011-dec2011/article4.htm|title=Second Static Testing of Solid Propellant Booster Rocket Stage S200 for GSLV-Mk III Successfully Conducted|website=VSSC.gov.in|archive-url=https://web.archive.org/web/20180212155855/http://www.vssc.gov.in/VSSC_V4/images/NewsLetter/apr2011-dec2011/article4.htm|archive-date=12 February 2018|access-date=12 February 2018}} A third test, ST-03, was conducted on 14 June 2015 to validate the changes from the sub-orbital test flight data.{{Cite news|url=https://www.sakshi.com/news/andhra-pradesh/successfully-testing-a-geostationary-248632|title=విజయవంతంగా భూస్థిర పరీక్ష|date=15 June 2015|work=Sakshi|access-date=12 February 2018|language=en}}{{Cite news|url=http://www.thehindu.com/todays-paper/tp-national/tp-andhrapradesh/static-test-of-s200-motor-successful/article7316301.ece|title=Static test of S200 motor successful|author=Staff Reporter|date=15 June 2015|work=The Hindu|access-date=12 February 2018|language=en-IN|issn=0971-751X}}

File:L110 Liquid Stage at Stage Preparation Facility.jpg

The second stage, designated L110, is a liquid-fueled stage that is {{convert|21|m|ft}} tall and {{convert|4|m}} wide, and contains {{convert|110|MT|lb}} of unsymmetrical dimethylhydrazine (UDMH) and nitrogen tetroxide ({{chem2|N2O4}}). It is powered by two Vikas 2 engines, each generating {{convert|766|kN}} thrust, giving a total thrust of {{convert|1532|kN}}.{{cite web|title=L110 test to follow S200|url=http://indianspaceweb.blogspot.com/2010/01/l110-test-to-follow-s200.html|website=IndianSpaceWeb|date=4 January 2010|access-date=15 October 2014}} The L110 is the first clustered liquid-fueled engine designed in India. The Vikas engines uses regenerative cooling, providing improved weight and specific impulse compared to earlier Indian rockets.[http://www.isro.org/launchers/lvm3 LVM3] {{webarchive|url=https://web.archive.org/web/20141225090957/http://www.isro.org/launchers/lvm3 |date=25 December 2014 }} ISRO 23 December 2014 Each Vikas engine can be individually gimbaled to control vehicle pitch, yaw and roll control. The L110 core stage ignites 114 seconds after liftoff and burns for 203 seconds. Since the L110 stage is air-lit, its engines need shielding during flight from the exhaust of the operating S200 boosters and reverse flow of gases by a 'nozzle closure system' which gets jettisoned prior to L110 ignition.{{cite web |title=Nozzle closure system for gsLVM3 launch vehicle |url=https://archive.org/details/AbstractsOfTechnicalPapersARMS2008/page/n29/mode/1up |publisher=ARMS 2008 |access-date=11 May 2021}}

ISRO conducted the first static test of the L110 core stage at its Liquid Propulsion Systems Centre (LPSC) test facility at Mahendragiri, Tamil Nadu on 5 March 2010. The test was planned to last 200 seconds, but was terminated at 150 seconds after a leakage in a control system was detected.{{cite web|url=http://www.thehindu.com/sci-tech/article621253.ece|title=ISRO successfully conducts static testing of new age rocket|work=The Hindu|date=8 September 2010 |access-date=4 October 2014}} A second static fire test for the full duration was conducted on 8 September 2010.{{cite web|url=http://www.isro.org/pressrelease/scripts/pressreleasein.aspx?Sep08_2010|title=ISRO Press Release:Successful Static Testing of L 110 Liquid Core Stage of GSLV - Mk III|access-date=17 June 2017|url-status=dead|archive-url=https://web.archive.org/web/20140202232751/http://www.isro.org/pressrelease/scripts/pressreleasein.aspx?Sep08_2010|archive-date=2 February 2014}}

File:C25 Cryogenic Stage at Stage Preparation Facility.jpg

The cryogenic upper stage, designated C25, is {{convert|4|m}} in diameter and {{convert|13.5|m}} long, and contains {{convert|28|MT|lb}} of propellant LOX and LH₂, pressurized by helium stored in submerged bottles.{{cite web |title=Cryogenic Gas Bottle Development & Realization - Role of non-destructive evaluation |url=https://www.ndt.net/article/nde-india2016/papers/A206.pdf |access-date=11 May 2021 |archive-url=https://web.archive.org/web/20210511172507/https://www.ndt.net/article/nde-india2016/papers/A206.pdf |archive-date=11 May 2021}} It is powered by a single CE-20 engine, producing {{convert|200|kN|abbr=on}} of thrust. CE-20 is the first cryogenic engine developed by India which uses a gas generator, as compared to the staged combustion engines used in GSLV.{{cite web|title=Why ISRO's New Engine and Mk III Rocket Are Reasons to Forget 1990 Cryogenic Scandal|url=https://thewire.in/138915/cryogenic-ce-20-isro-gslv-mk-iii/|website=TheWire|access-date=11 February 2018|archive-url=https://web.archive.org/web/20180211192523/https://thewire.in/138915/cryogenic-ce-20-isro-gslv-mk-iii/|archive-date=11 February 2018|location=Wayback Machine}} In LVM3-M3 mission, a new white coloured C25 stage was introduced which has more environmental-friendly manufacturing processes, better insulation properties and the use of lightweight materials.{{cite web|title=ISRO's C25 cryogenic stage now sports white, ditches black; What's the science behind it?|url=https://www.wionews.com/india-news/isros-c25-cryogenic-stage-now-sports-white-ditches-black-whats-the-science-behind-it-575318/amp|website=wionews|access-date=27 March 2023}} The stage also houses the flight computers and Redundant Strap Down Inertial Navigation System of the launch vehicle in its equipment bay. The digital control system of the launcher uses closed-loop guidance throughout the flight to ensure accurate injections of satellites into the target orbit. Communications system of the launch vehicle consisting of an S-Band system for telemetry downlink and a C-Band transponder that allows radar tracking and preliminary orbit determination are also mounted on the C25. The communications link is also used for range safety and flight termination that uses a dedicated system that is located on all stages of the vehicle and features separate avionics.

The first static fire test of the C25 cryogenic stage was conducted on 25 January 2017 at the ISRO Propulsion Complex (IPRC) facility at Mahendragiri, Tamil Nadu. The stage fired for a duration of 50 seconds and performed nominally.{{Cite web|url=https://www.isro.gov.in/update/26-jan-2017/isro-successfully-tests-c25-cryogenic-upper-stage-of-gslv-mkiii|title=ISRO Successfully Tests C25 Cryogenic Upper Stage of GSLV MkIII|website=Indian Space Research Organisation|language=en|access-date=30 May 2018|archive-date=27 March 2018|archive-url=https://web.archive.org/web/20180327213208/https://www.isro.gov.in/update/26-jan-2017/isro-successfully-tests-c25-cryogenic-upper-stage-of-gslv-mkiii|url-status=dead}} A second static fire test for the full in-flight duration of 640 seconds was completed on 17 February 2017.{{cite web|url=http://isro.gov.in/update/18-feb-2017/isro-successfully-tests-its-cryogenic-stage-c25-gslv-mkiii-flight-duration|title=ISRO Successfully Tests its Cryogenic Stage (C25) for GSLV MkIII for the Flight Duration|website=Indian Space Research Organisation|access-date=17 June 2017|archive-url=https://web.archive.org/web/20170609075332/http://isro.gov.in/update/18-feb-2017/isro-successfully-tests-its-cryogenic-stage-c25-gslv-mkiii-flight-duration|archive-date=9 June 2017|url-status=dead}} This test demonstrated consistency in engine performance along with its sub-systems, including the thrust chamber, gas generator, turbopumps and control components for the full duration.

File:LVM3 M2, OneWeb India-1 campaign 27.jpg satellites]]

The CFRP composite payload fairing has a diameter of {{convert|5|m}}, a height of {{convert|10.75|m}} and a payload volume of {{convert|110|m3}}. It is manufactured by Coimbatore-based LMW Advanced Technology Centre.{{Cite news |author=|date=2024-04-02 |title=LMW ATC hands over payload to ISRO for GSLV MK - III |url=https://www.thehindu.com/news/cities/Coimbatore/lmw-atc-hands-over-payload-to-isro-for-gslv-mk-iii/article68020688.ece |access-date=2024-04-03 |work=The Hindu |language=en-IN |issn=0971-751X}} After the first flight of the rocket with CARE module, the payload fairing was modified to an ogive shape, and the S200 booster nose cones and inter-tank structure were redesigned to have better aerodynamic performance.{{cite web|author1=Department of Space, Government of India|title=Outcome Budget 2016-17|url=http://isro.gov.in/sites/default/files/article-files/budget-accounts/outcomebudget2016-2017.pdf|website=isro.gov.in|publisher=Department of Space, Government of India|access-date=1 June 2017|archive-url=https://web.archive.org/web/20161126142718/http://isro.gov.in/sites/default/files/article-files/budget-accounts/outcomebudget2016-2017.pdf|archive-date=26 November 2016}} The vehicle features a large fairing with a five-meter diameter to provide sufficient space even to large satellites and spacecraft. Separation of fairing in a nominal flight scenario occurs at approximately T+253 seconds and is accomplished by a linear piston cylinder separation and jettisoning mechanism (zip cord) spanning full length of PLF which is pyrotechnically initiated. The gas pressure generated by the zip cord expands a rubber below that pushes the piston and cylinder apart and thereby pushing the payload fairing halves laterally away from the launcher. The fairing is made of Aluminum alloy featuring acoustic absorption blankets.

{{Main|Gaganyaan|CE-20}}

File:HLVM3.svg

While the LVM3 is being human rated for Gaganyaan project, the rocket was always designed with potential human spaceflight applications in consideration. The maximum acceleration during ascent phase of flight was limited to 4 Gs for crew comfort and a {{convert|5|m|adj=on}} diameter payload fairing was used to be able to accommodate large modules like space station segments.{{cite book |title=From Fishing Hamlet to Red Planet: India's Space Journey |isbn=9789351776895 |chapter=2.8 2.8 The Next-Generation Launcher: GSLV-Mk III by S. Ramakrishnan |date=15 December 2015 |publisher=HarperCollins Publishers India |quote=Taking into account the LEO payload capability of up to 10 tonnes feasible with this vehicle, the payload fairing diameter was fixed as 5 metres to accommodate large modules like a space station segment or manned capsule. Incidentally, considering the possibility of future human space flight missions by India, the boost phase acceleration was capped at 4g, the standard human tolerance level accepted by spacefaring agencies.}}

Furthermore, a number of changes to make safety-critical subsystems reliable are planned for lower operating margins, redundancy, stringent qualification requirements, revaluation, and strengthening of components.{{cite AV media|url=https://www.youtube.com/watch?v=L9vVVLpeVos |archive-url=https://ghostarchive.org/varchive/youtube/20211221/L9vVVLpeVos |archive-date=2021-12-21 |url-status=live|title=PRL Ka Amrut Vyakhyaan-02, 'Reaching the sky: Indian Launch Vehicles'|date=11 August 2021|people=S. Somanath|time=53:10–53:40|access-date=6 October 2021|medium=video|via=YouTube}}{{cbignore}} Avionics improvement will incorporate a Quad-redundant Navigation and Guidance Computer (NGC), Dual chain Telemetry & Telecommand Processor (TTCP) and an Integrated Health Monitoring System (LVHM). The launch vehicle will have the High Thrust Vikas engines (HTVE) of L110 core stage operating at a chamber pressure of 58.5 bar instead of 62 bar. Human rated S200 (HS200) boosters will operate at chamber pressure of 55.5 bar instead of 58.8 bar and its segment joints will have three O-rings each. Electro mechanical actuators and digital stage controllers will be employed in HS200, L110 and C25 stages.{{Cite web|title=CSIR NAL Annual Report 2020-21|url=https://nal.res.in/sites/default/files/inline-files/Director%20Report%202020-21%20for%20web.pdf|url-status=live|archive-url=https://web.archive.org/web/20210804115645/https://nal.res.in/sites/default/files/inline-files/Director%20Report%202020-21%20for%20web.pdf|archive-date=4 August 2021|quote=In addition, ATF also successfully completed the acoustic qualification of the Strap on Electro Mechanical Actuator Structure for the GSLV MKIII launcher. This would help in improving reliability and also provide advantages in payload capability in comparison with the Electro Hydraulic actuators used earlier.}}

{{Main|SCE-200}}

File:Power Head Test Article (PHTA) for SCE-200.jpg

The L110 core stage in the LVM3 is planned to be replaced by the SC120, a kerolox stage powered by the SCE-200 engine{{cite web|url=http://www.newindianexpress.com/cities/thiruvananthapuram/Semi-cryogenic-Engine-ISRO-Charting-a-Revised-Plan/2015/03/02/article2693939.ece|archive-url=https://web.archive.org/web/20150306173135/http://www.newindianexpress.com/cities/thiruvananthapuram/Semi-cryogenic-Engine-ISRO-Charting-a-Revised-Plan/2015/03/02/article2693939.ece|url-status=dead|archive-date=6 March 2015|title=Semi-cryogenic Engine: ISRO Charting a Revised Plan|last=Rajwi|first=Tiki|date=2 March 2015|website=New Indian Express|access-date=20 May 2018}} to increase its payload capacity to {{convert|7.5|MT|lb}} to geostationary transfer orbit (GTO).{{cite web|url=http://www.thehindu.com/news/cities/Thiruvananthapuram/isro-developing-heavy-lift-launch-vehicles/article7262881.ece|title=ISRO developing heavy lift launch vehicles|date=30 May 2015|website=The Hindu|access-date=20 May 2018}} The SCE-200 uses kerosene instead of unsymmetrical dimethylhydrazine (UDMH) as fuel and has a thrust of around 200 tonnes. Four such engines can be clustered in a rocket without strap on boosters to deliver up to {{convert|10|t|lb}} to GTO.{{Cite web|title = Ukraine to test components of a powerful Indian rocket engine|url = http://www.russianspaceweb.com/rd810.html|access-date = 20 September 2019|website = russianspaceweb.com}} The first propellant tank for the SC120 was delivered in October 2021 by HAL.{{Cite news |date=2021-10-07 |title=HAL delivers 'heaviest' Semi-Cryogenic propellant tank to ISRO |newspaper=The Economic Times |url=https://economictimes.indiatimes.com/news/science/hal-delivers-heaviest-semi-cryogenic-propellant-tank-to-isro/articleshow/86838143.cms |access-date=2021-10-08}}

The SC120 powered version of LVM3 will not be used for the crewed mission of the Gaganyaan spacecraft.{{cite news |title=The ISRO Tender Notice With Fascinating New Details of Gaganyaan |url=https://thewire.in/space/the-isro-tender-notice-with-fascinating-technical-details-of-gaganyaan |access-date=29 January 2019}}{{Cite web |last=Singh |first=Surendra |date=28 January 2019 |title=GSLV Mk III: Isro eyes kerosene to boost GSLV Mk III's lifting power to 6 trillion |url=https://timesofindia.indiatimes.com/india/isro-eyes-kerosene-to-boost-gslv-mk-iiis-lifting-power-to-6-trillion/articleshow/67716433.cms |access-date=31 July 2019 |website=The Times of India |language=en}} In September 2019, in an interview by AstrotalkUK, S. Somanath, director of Vikram Sarabhai Space Centre claimed that the SCE-200 engine was ready to begin testing. As per an agreement between India and Ukraine signed in 2005, Ukraine was expected to test components of the SCE-200 engine, so an upgraded version of the LVM3 was not expected before 2022.{{Cite web |date=October 24, 2019 |title=Episode 90 – An update on ISRO's activities with S Somanath and R Umamaheshwaran |url=https://astrotalkuk.org/episode-90-an-update-on-isros-activities-with-s-somanath-and-r-umamaheshwaran/ |archive-url=https://web.archive.org/web/20191029030030/https://astrotalkuk.org/episode-90-an-update-on-isros-activities-with-s-somanath-and-r-umamaheshwaran/ |archive-date=2019-10-29 |access-date=October 30, 2019 |publisher=AstrotalkUK}} The SCE-200 engine is reported to be based on the Ukrainian RD-810, which itself is proposed for use on the Mayak family of launch vehicles.{{Cite news|title = ISRO moves on, gears up to test semi-cryogenic engine in Ukraine|url = https://www.thehindubusinessline.com/news/science/isro-moves-on-gears-up-to-test-semi-cryogenic-engine-in-ukraine/article29451601.ece|date = 19 September 2019|access-date = 20 September 2019|newspaper = The Hindu}}

The C25 stage with nearly {{cvt|25|t|lb}} propellant load will be replaced by the C32, with a higher propellant load of {{cvt|32|t|lb}}. The C32 stage will be re-startable and with uprated CE-20 engine.{{cite web |title=Report No. 362, Demands for Grants (2022-2023) of the Department of Space (Demand No. 95) |url=https://rajyasabha.nic.in/rsnew/Committee_site/Committee_File/ReportFile/19/165/362_2022_3_14.pdf |access-date=10 November 2022 |archive-url=https://web.archive.org/web/20220324113426/https://rajyasabha.nic.in/rsnew/Committee_site/Committee_File/ReportFile/19/165/362_2022_3_14.pdf |archive-date=24 March 2022 |page=14}} Total mass of avionics will be brought down by using miniaturised components.{{Cite news|date=2021-09-17|title=ISRO working on reusable GSLV Mk-III launch vehicle|url=https://www.thehindu.com/news/national/tamil-nadu/isro-working-on-reusable-gslv-mk-iii-launch-vehicle/article36507027.ece|newspaper=The Hindu|location=Chennai|access-date=2021-09-18}} On 30 November 2020, Hindustan Aeronautics Limited delivered an aluminium alloy based cryogenic tank to ISRO. The tank has a capacity of {{cvt|5755|kg}} of fuel, and a volume of {{cvt|89|m³}}.{{Cite news|title=HAL delivers biggest ever cryogenic propellant tank to ISRO|url=https://www.financialexpress.com/lifestyle/science/hal-delivers-biggest-ever-cryogenic-propellant-tank-to-isro/2140086/|newspaper=The Financial Express|date=2020-11-30|access-date=2020-12-01}}{{cite web |title=HAL Delivers Biggest Ever Cryogenic Propellant Tank to ISRO |url=https://hal-india.co.in/HAL%20Delivers%20Bi/ND__324 |access-date=5 October 2021}}

On 9 November 2022, CE-20 cryogenic engine of upper stage was tested with an uprated thrust regime of 21.8 tonnes in November 2022. Along a suitable stage with additional propellant loading this could increase payload capacity of LVM3 to GTO by up to {{cvt|450|kg}}.{{Cite web |date=2022-11-09 |title=Successful CE20 uprated Engine Hot Test with 21.8 T vacuum thrust |url=https://www.isro.gov.in/LVM3_CE20_uprated_Engine_Hot_Test.html |archive-url=https://web.archive.org/web/20221110133035/https://www.isro.gov.in/LVM3_CE20_uprated_Engine_Hot_Test.html |archive-date=2022-11-10 |access-date=2022-11-10 |work=Indian Space Research Organisation}} On 23 December 2022, CE-20 engine E9 was hot tested for 650 second duration. For the first 40 seconds of test, the engine was operated at 20.2 tonne thrust level, after this engine was operated at 20 tonne off-nominal zones and then for 435 seconds it was operated at 22.2 tonne thrust level. With this test, the 'E9' engine has been qualified for induction in flight.{{Cite web |title=Successful CE-20 Engine Hot Test with 20t off-nominal & 22.2t vacuum thrust |url=https://www.isro.gov.in/suceessful-ce-engine-hot-test.html |access-date=2022-12-24 |website=www.isro.gov.in |archive-date=24 December 2022 |archive-url=https://web.archive.org/web/20221224091931/https://www.isro.gov.in/suceessful-ce-engine-hot-test.html |url-status=dead }} It is hoped that after introduction of this stage, GTO payload capacity can be raised to 6 tonnes.{{Cite news |last=Mohandas |first=Pradeep |date=2024-07-13 |title=ISRO has a problem: too many rockets, too few satellites to launch {{!}} Analysis |url=https://www.thehindu.com/sci-tech/science/isro-has-a-problem-too-many-rockets-too-few-satellites-to-launch-analysis/article68399333.ece |access-date=2024-07-20 |work=The Hindu |language=en-IN |issn=0971-751X}}

{{Main|List of LVM3 launches}}

LVM3 currently has accumulated a total of 7 launches, {{as of|2023|07|19|lc=on}}. Of these, all 7 have been successful, giving it a cumulative success rate of {{percent|7|7|0}}.

;Decade-wise summary of LVM3 launches:

File:GSLV Mk III Lift Off 6.jpg|D1/GSAT-19

File:02 GSLV Mk III D2 with GSAT-29 on Second Launch Pad of Satish Dhawan Space Centre, Sriharikota (SDSC SHAR).jpg|D2/GSAT-29

File:GSLV Mk III M1, Chandrayaan-2 Lifting off 03.jpg|M1/Chandrayaan-2

File:LVM3 M2, OneWeb India-1 campaign 19.jpg|M2/OneWeb

File:LVM3 M4, Chandrayaan-3 - Launch vehicle lifting off from the Second Launch Pad (SLP) of SDSC-SHAR, Sriharikota 03.webp|M4/Chandrayaan-3

{{Portal|India|Rocketry|Spaceflight}}

• PSLV
• GSLV
• SSLV
• Gaganyaan
• List of Indian satellites
• Comparison of orbital launch systems
• Comparison of orbital launchers families

{{Notelist}}

{{Reflist}}

{{Commons category|Launch Vehicle Mark III}}

• [https://web.archive.org/web/20081218080432/http://www.bharat-rakshak.com/SPACE/space-launchers-gslv.html#gslvmk3 Bharat-Rakshak GSLV-III information]
• [https://web.archive.org/web/20080917045256/http://www.newscientist.com/special/india/mg18524871.000 New Scientist article including GSLV-III diagram]

{{Expendable launch systems}}

{{Indian space programme}}

{{DEFAULTSORT:GSLV Mk III}}

Category:Launch Vehicle Mark-3

Category:Satish Dhawan Space Centre

Category:ISRO space launch vehicles

Category:Expendable space launch systems

Category:Vehicles introduced in 2014