List of GSLV launches

This is a list of launches conducted by the Indian Space Research Organisation (ISRO) using Geosynchronous Satellite Launch Vehicle (GSLV) rockets. This list does not include LVM 3 (formerly known as GSLV Mk III) launches, which can be found here.

GSLV MK. I flight D1
This was the first developmental flight of the GSLV Mk.I featuring Russian cryogenic engine KVD-1. It was used to place an experimental satellite GSAT-1 into the orbit. However, due to sub-optimal performance and lack of fuel the vehicle did not achieve the intended orbit and the satellite had to maneuver itself using onboard fuel to correct the shortfall. ISRO claims the launch to be successful. In a 2014 interview, ISRO Chairman K. Radhakrishnan attributed the failure to incorrect mixture ratio used in the cryogenic upper stage.

GSLV MK. II flight D5
This was the second test flight with indigenous cryogenic stage CE-7.5 and the first successful launch with the CE-7.5. The flight lifted and successfully placed the 1982 kg GSAT-14 into the orbit. This flight became the harbinger of successful launch with the indigenous cryogenic stage.

GSLV MK. II flight F09
This was the fourth consecutive successful flight of GSLV Mk. II with indigenous cryogenic engine. The flight placed the regional satellite South Asia Satellite was previously named as South Asian Association for Regional Cooperation (SAARC) Satellite. The satellite was a gift from India to its neighbors to bolsters Prime Minister Narendra Modi's neighborhood first policy Afghanistan, Bangladesh, Bhutan, Maldives, Nepal and Sri Lanka are the users of the multi-dimensional facilities provided by the satellite.

Launch history
, rockets from the GSLV family have made 16 launches, resulting in 10 successes, four failures, and two partial failures. All launches have occurred from the Satish Dhawan Space Centre, known before 2002 as the Sriharikota Range (SHAR).

{| class="wikitable plainrowheaders" style="width: 100%;"
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2001–2009
! scope="col" | Flight No. ! scope="col" | Date / time (UTC) ! scope="col" | Rocket, Configuration ! scope="col" | Launch site ! scope="col" | Payload ! scope="col" | Payload mass ! scope="col" | Orbit ! scope="col" | User ! scope="col" | Launch outcome

! scope="row" rowspan = 2 style="text-align:center;| D1
 * 18 April 2001 10:13
 * Mk I
 * First
 * 🇮🇳 GSAT-1
 * 1540 kg
 * GTO
 * INSAT
 * Partial failure
 * colspan="8"| Developmental flight, payload placed into lower than planned orbit, and did not have sufficient fuel to reach a usable orbit.
 * colspan="8"| Developmental flight, payload placed into lower than planned orbit, and did not have sufficient fuel to reach a usable orbit.

! scope="row" rowspan = 2 style="text-align:center;| D2
 * 8 May 2003 11:28
 * Mk I
 * First
 * 🇮🇳 GSAT-2
 * 1825 kg
 * GTO
 * INSAT
 * Success
 * colspan="8"| Developmental flight.
 * colspan="8"| Developmental flight.

! scope="row" rowspan = 2 style="text-align:center;| F01
 * 20 September 2004 10:31
 * Mk I
 * First
 * 🇮🇳 GSAT-3
 * 1950 kg
 * GTO
 * INSAT
 * Success
 * colspan="8"| First operational flight.
 * colspan="8"| First operational flight.

! scope="row" rowspan = 2 style="text-align:center;| F02
 * 10 July 2006 12:08
 * Mk I
 * Second
 * 🇮🇳 INSAT-4C
 * 2168 kg
 * GTO
 * INSAT
 * Failure
 * colspan="8"| One of the L40 strap-on engines failed at lift-off. Both rocket and satellite had to be destroyed over the Bay of Bengal after the rocket's trajectory veered outside permitted limits.
 * colspan="8"| One of the L40 strap-on engines failed at lift-off. Both rocket and satellite had to be destroyed over the Bay of Bengal after the rocket's trajectory veered outside permitted limits.

! scope="row" rowspan = 2 style="text-align:center;| F04
 * 2 September 2007 12:51
 * Mk I
 * Second
 * nowrap | 🇮🇳 INSAT-4CR
 * 2160 kg
 * GTO
 * INSAT
 * Partial failure
 * colspan="8"| High roll rate build-up due control system malfunction on one L40 strapon resulted in premature shutdown of other strap-on stages. Due to an error in the guidance subsystem achieved orbit had lower apogee and inclination higher than expected. Orbit corrected through satellite, eventually the INSAT-4CR was placed in its slot. Satellite completed its planned design life while it was fully operational. ISRO claims this GSLV flight to be successful.
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2010–2017
! scope="col" | Flight No. ! scope="col" | Date / time (UTC) ! scope="col" | Rocket, Configuration ! scope="col" | Launch site ! scope="col" | Payload ! scope="col" | Payload mass ! scope="col" | Orbit ! scope="col" | User ! scope="col" | Launch outcome ! scope="row" rowspan = 2 style="text-align:center;| D3
 * 15 April 2010 10:57
 * Mk II
 * Second
 * 🇮🇳 GSAT-4
 * 2220 kg
 * GTO
 * INSAT
 * Failure
 * colspan="8"| First flight test of the ISRO designed and built Cryogenic Upper Stage (CUS). Failed to reach orbit due to malfunction of the Fuel Booster Turbo Pump (FBTP) of the cryogenic upper stage.
 * colspan="8"| First flight test of the ISRO designed and built Cryogenic Upper Stage (CUS). Failed to reach orbit due to malfunction of the Fuel Booster Turbo Pump (FBTP) of the cryogenic upper stage.

! scope="row" rowspan = 2 style="text-align:center;| F06
 * 25 December 2010 10:34
 * Mk I
 * Second
 * 🇮🇳 GSAT-5P
 * 2310 kg
 * GTO
 * INSAT
 * Failure
 * colspan="8"| First flight of GSLV Mk.I (c). Aft shroud of upper stage engine bay disintegrated due to aerodynamic loads, snapping the electrical continuity to L40 strapons. Vehicle was destroyed by range safety officer after loss of control over liquid-fueled boosters.
 * colspan="8"| First flight of GSLV Mk.I (c). Aft shroud of upper stage engine bay disintegrated due to aerodynamic loads, snapping the electrical continuity to L40 strapons. Vehicle was destroyed by range safety officer after loss of control over liquid-fueled boosters.

! scope="row" rowspan = 2 style="text-align:center;| D5
 * 5 January 2014 10:48
 * Mk II
 * Second
 * 🇮🇳 GSAT-14
 * 1980 kg
 * GTO
 * INSAT
 * Success
 * colspan="8"| The flight was scheduled for 19 August 2013, but one hour and 14 minutes before the lift off, a leakage was reported and the launch was halted. Second flight of GSLV with indigenous cryogenic upper stage (CUS) developed by ISRO's Liquid Propulsion Systems Centre (LPSC) was launched successfully on 5 January 2014. It was a launch with precision of 40 m. All the three stages performed successfully.  This was the first successful flight of the cryogenic stage which was developed indigenously in India.
 * colspan="8"| The flight was scheduled for 19 August 2013, but one hour and 14 minutes before the lift off, a leakage was reported and the launch was halted. Second flight of GSLV with indigenous cryogenic upper stage (CUS) developed by ISRO's Liquid Propulsion Systems Centre (LPSC) was launched successfully on 5 January 2014. It was a launch with precision of 40 m. All the three stages performed successfully.  This was the first successful flight of the cryogenic stage which was developed indigenously in India.

! scope="row" rowspan = 2 style="text-align:center;| D6
 * 27 August 2015 11:22
 * Mk II
 * Second
 * 🇮🇳 GSAT-6
 * 2117 kg
 * GTO
 * INSAT
 * Success
 * colspan="8"| GSLV Mk II D6 with an Indigenous Cryogenic Engine (ICE) successfully ferried GSAT-6 payload into Geostationary Transfer Orbit (GTO) with injection parameters of 170 km x 35945 km, 19.96° inclination. The cuboid-shaped GSAT-6 satellite includes a technology demonstrator S-Band unfurlable antenna with a diameter of six metre which will provide S-band communication services during its expected mission life of nine years.
 * colspan="8"| GSLV Mk II D6 with an Indigenous Cryogenic Engine (ICE) successfully ferried GSAT-6 payload into Geostationary Transfer Orbit (GTO) with injection parameters of 170 km x 35945 km, 19.96° inclination. The cuboid-shaped GSAT-6 satellite includes a technology demonstrator S-Band unfurlable antenna with a diameter of six metre which will provide S-band communication services during its expected mission life of nine years.

! scope="row" rowspan = 2 style="text-align:center;| F05
 * 8 September 2016 11:20
 * MK II
 * Second
 * 🇮🇳 INSAT-3DR
 * 2211 kg
 * GTO
 * INSAT
 * Success
 * colspan="8"| First operational flight of GSLV Mk II. The injection parameters were met with extreme precision. Perigee was within 300m (within 0.18%) of the expected value whereas apogee was within 0.2% (80 km). The difference between expected and actual inclination degree was 0.
 * colspan="8"| First operational flight of GSLV Mk II. The injection parameters were met with extreme precision. Perigee was within 300m (within 0.18%) of the expected value whereas apogee was within 0.2% (80 km). The difference between expected and actual inclination degree was 0.

INSAT-3DR is an advanced atmospheric weather satellite. as well as the second heaviest satellite placed in orbit by an indigenous cryogenic engine propelled GSLV ! scope="row" rowspan = 2 style="text-align:center;|F09
 * 5 May 2017 11:27
 * Mk II
 * Second
 * 🇮🇳 GSAT-9 / South Asia Satellite
 * 2230 kg
 * GTO
 * INSAT
 * Success
 * colspan="8"| South Asia Satellite was previously named as South Asian Association for Regional Cooperation (SAARC) Satellite.
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2018
! scope="col" | Flight No. ! scope="col" | Date / time (UTC) ! scope="col" | Rocket, Configuration ! scope="col" | Launch site ! scope="col" | Payload ! scope="col" | Payload mass ! scope="col" | Orbit ! scope="col" | User ! scope="col" | Launch Outcome ! scope="row" rowspan = 2 style="text-align:center;| F08 ! scope="row" rowspan = 2 style="text-align:center;| F11
 * 29 March 2018 11:26
 * Mk II
 * Second
 * 🇮🇳 GSAT-6A
 * 2140 kg
 * GTO
 * INSAT
 * Success
 * colspan="8"| Used an enhanced version of the Vikas engine called High Thrust Vikas Engine (HTVE) which had a thrust of 848 kN in GS2 stage. Electro-hydraulic Actuation used for gimballing in GS2 stage was replaced by more reliable Electro-Mechanical Actuation.
 * colspan="8"| Used an enhanced version of the Vikas engine called High Thrust Vikas Engine (HTVE) which had a thrust of 848 kN in GS2 stage. Electro-hydraulic Actuation used for gimballing in GS2 stage was replaced by more reliable Electro-Mechanical Actuation.
 * 19 December 2018 10:40
 * Mk II
 * Second
 * 🇮🇳 GSAT-7A
 * 2250 kg
 * GTO
 * INSAT
 * Success
 * colspan="8"| Used an enhanced version of the Vikas engine called High Thrust Vikas Engine (HTVE) along with uprated cryogenic engine C15.
 * colspan=9 style="background:white;" |
 * colspan=9 style="background:white;" |
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2021
! scope="col" | Flight No. ! scope="col" | Date / time (UTC) ! scope="col" | Rocket, Configuration ! scope="col" | Launch site ! scope="col" | Payload ! scope="col" | Payload mass ! scope="col" | Orbit ! scope="col" | User ! scope="col" | Launch Outcome ! scope="row" rowspan = 2 style="text-align:center;| F10
 * 12 August 2021 00:13
 * Mk II
 * Second
 * 🇮🇳 GISAT-1 / EOS-03
 * 2268 kg
 * GTO
 * ISRO
 * Failure
 * colspan="8"|Carried EOS-03, a geostationary multi-spectral imaging satellite. The third stage failed to ignite, leading to the loss of the mission. The cause of failure was found to be a 50 millibar drop in pressure in the Liquid Hydrogen tank of the Cryogenic Upper Stage (CUS)
 * colspan=9 style="background:white;" |
 * colspan=9 style="background:white;" |
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2023
! scope="col" | Flight No. ! scope="col" | Date / time (UTC) ! scope="col" | Rocket, Configuration ! scope="col" | Launch site ! scope="col" | Payload ! scope="col" | Payload mass ! scope="col" | Orbit ! scope="col" | User ! scope="col" | Launch Outcome ! rowspan="2" |F12
 * 29 May 2023 10:42
 * Mk II
 * Second
 * 🇮🇳 NVS-01
 * 2232 kg
 * GTO
 * ISRO
 * Success
 * colspan="8" |NVS-01 is the first in the second generation navigational satellites. It carried navigational payload operating in L1,L5 and s bands. For the first time, an indigenous atomic clock was flown in NVS-01.
 * colspan="8" |NVS-01 is the first in the second generation navigational satellites. It carried navigational payload operating in L1,L5 and s bands. For the first time, an indigenous atomic clock was flown in NVS-01.


 * colspan=9 style="background:white;" |
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2024
! scope="col" | Flight No. ! scope="col" | Date / time (UTC) ! scope="col" | Rocket, Configuration ! scope="col" | Launch site ! scope="col" | Payload ! scope="col" | Payload mass ! scope="col" | Orbit ! scope="col" | User ! scope="col" | Launch Outcome ! rowspan="2" |F14
 * 17 February 2024 12:05
 * Mk II
 * Second
 * 🇮🇳 INSAT-3DS
 * 2275 kg
 * GTO
 * ISRO
 * Success
 * colspan="8" |Follow on mission to INSAT-3DR. In this 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.
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