SPACE LAUNCH REPORT PSLV Flight History by Variant/Year (1979-Present) by Ed Kyle Last Update: January 01, 2024 L(F) = Number of Launches(Number of Failures) PSLV PSLV-CA PSLV-XL PSLV-DL PSLV-QL PSLV Total Year L(F) L(F) L(F) L(F) L(F) L(F) ------------------------------------------------------------------ 1990 - - - - - - 1991 - - - - - - 1992 - - - - - - 1993 1(1) - - - - 1(1) 1994 1(0) - - - - 1(0) 1995 - - - - - - 1996 1(0) - - - - 1(0) 1997 1(1) - - - - 1(1) 1998 - - - - - - 1999 1(0) - - - - 1(0) 2000 - - - - - - 2001 1(0) - - - - 1(0) 2002 1(0) - - - - 1(0) 2003 1(0) - - - - 1(0) 2004 - - - - - - 2005 1(0) - - - - 1(0) 2006 - - - - - - 2007 1(0) 1(0) - - - 2(0) 2008 - 2(0) 1(0) - - 3(0) 2009 - 2(0) - - - 2(0) 2010 - 1(0) - - - 1(0) 2011 1(0) 1(0) 1(0) - - 3(0) 2012 - 1(0) 1(0) - - 2(0) 2013 - 1(0) 2(0) - - 3(0) 2014 - 1(0) 2(0) - - 3(0) 2015 - 1(0) 3(0) - - 4(0) 2016 1(0) - 5(0) - - 6(0) 2017 - - 3(1) - - 3(1) 2018 - 2(0) 2(0) - - 4(0) 2019 - 1(0) 1(0) 1(0) 2(0) 5(0) 2020 - - 1(0) 1(0) - 2(0) 2021 - - - 1(0) - 1(0) 2022 - 1(0) 2(0) - - 3(0) 2023 - 2(0) 1(0) - - 3(0) 2024 - - - 1(0) - 1(0) ------------------------------------------------------------------ PSLV PSLV-CA PSLV-XL PSLV-DL PSLV-QL PSLV Total L(F) L(F) L(F) L(F) L(F) L(F) ------------------------------------------------------------------ Suborb - - - - - - Orbit 12(2) 17(0) 25(1) 4(0) 2(0) 60(3) Total 12(2) 17(0) 25(1) 4(0) 2(0) 60(3) ------------------------------------------------------------------ Footnotes: SPACE LAUNCH REPORT PSLV Launch History by Ed Kyle DATE VEHICLE ID PAYLOAD MASS(t) SITE* ORBIT* ------------------------------------------------------------------ 09/20/93 PSLV D1 IRS-1E 0.846 SR 1 [FTO] 10/15/94 PSLV D2 IRS-P2 0.804 SR 1 SSO 03/21/96 PSLV D3 IRS-P3 0.930 SR 1 SSO 09/29/97 PSLV C1 IRS-1D 1.250 SR 1 [LEO] 05/26/99 PSLV C2 IRS-P4/Kitsat-3/Tubsat-C 1.191 SR 1 SSO 10/22/01 PSLV C3 TES,BIRD,PROBA 1.294 SR 1 SSO 09/12/02 PSLV C4 Metsat 1 1.055 SR 1 GTO 10/17/03 PSLV C5 IRS-P6 1.36 SR 1 SSO 05/05/05 PSLV C6 Cartosat 1/Hamsat 1.60 SR 2 SSO 01/10/07 PSLV C7 CartoSat 2/SRE 1 1.29 SR 1 SSO 04/23/07 PSLV-CA C8 AGILE/AMM 0.54 SR 2 LEO 01/21/08 PSLV-CA C10 Tecsar(Polaris) 0.295 SR 1 LEO 04/28/08 PSLV-CA C9 Cartosat 2A 0.768 SR 2 SSO 10/22/08 PSLV-XL C11 Chandrayaan 1 1.38 SR 2 EEO 04/20/09 PSLV-CA C12 RISAT 2/ANUSAT 0.34 SR 2 LEO 09/23/09 PSLV-CA C14 Oceansat 2/5xusats 0.972 SR 1 SSO 07/12/10 PSLV-CA C15 Cartosat 2B/Altsat 2A 0.82 SR 1 SSO 04/20/11 PSLV C16 ResourceSat-2 1.4 SR 1 SSO 07/15/11 PSLV-XL C17 GSAT-12 1.41 SR 2 GTO- 10/12/11 PSLV-CA C18 Mega-Tropiques 1.047 SR 1 LEO 04/26/12 PSLV-XL C19 Risat 1 1.858 SR 1 SSO 09/09/12 PSLV-CA C21 SPOT 6/Proiteres 0.727 SR 1 SSO 02/25/13 PSLV-CA C20 SARAL/Sapphire 0.676 SR 1 SSO 07/01/13 PSLV-XL C22 IRNSS-1A 1.425 SR 1 GTO- 11/05/13 PSLV-XL C25 Mars Orbiter Mission 1.337 SR 1 EEO 04/04/14 PSLV-XL C24 IRNSS 1B 1.432 SR 1 GTO- 06/30/14 PSLV-CA C23 SPOT 7 (+4usats) 0.765 SR 1 SSO 10/15/14 PSLV-XL C26 IRNSS 1C 1.425 SR 1 GTO- 03/28/15 PSLV-XL C27 IRNSS 1D 1.425 SR 2 GTO- 07/10/15 PSLV-XL C28 3xDMC3 1.439 SR 1 SSO 09/28/15 PSLV-XL C30 Astrosat + 6usats 1.631 SR 1 LEO 12/16/15 PSLV-CA C29 TeLEOS 1 + 5usats 0.625 SR 1 LEO 01/20/16 PSLV-XL C31 IRNSS 1E 1.425 SR 2 GTO- 03/10/16 PSLV-XL C32 IRNSS 1F 1.425 SR 2 GTO- 04/28/14 PSLV-XL C33 IRNSS 1G 1.425 SR 1 GTO- 06/22/16 PSLV-XL C34 Cartosat 2 + 19 usats 1.288 SR 2 SSO 09/26/16 PSLV C35 ScatSat 1/Multisats 0.675 SR 1 SSO 12/07/16 PSLV-XL C36 Resourcesat 2A 1.235 SR 1 SSO 02/15/17 PSLV-XL C37 Cartosat 2D +103 nsats 1.378 SR 1 SSO 06/23/17 PSLV-XL C38 Cartosat 2E+30nsats 0.955 SR 1 SSO 08/31/17 PSLV-XL C39 IRNSS 1H 1.425 SR 2 [EEO] 01/12/18 PSLV-XL C40 Cartosat 2F/usats 1.313 SR 1 SSO 04/11/18 PSLV-XL C41 IRNSS 1I 1.425 SR 1 GTO- 09/16/18 PSLV-CA C42 NovaSAR-S/SSTL-S1 0.889 SR 1 SSO 11/29/18 PSLV-CA C43 HySIS + 30usats 0.38 SR 1 SSO 01/24/19 PSLV-DL C44 Microsat R 0.75 SR 1 SSO 04/01/19 PSLV-QL C45 EMISat+usats 0.64 SR 2 SSO 05/21/19 PSLV-CA C46 RISAT 2B 0.615 SR 1 LEO 11/27/19 PSLV-XL C47 Cartosat 3 1.625 SR 2 SSO 12/11/19 PSLV-QL C48 RISAT 2BR1 +9usats ~0.8 SR 1 LEO 11/07/20 PSLV-DL C49 EOS-1 + 9usats ~0.7 SR 1 LEO 12/17/20 PSLV-XL C50 CMS 1 1.41 SR 2 GTO- 02/28/21 PSLV-DL C51 Amazonia 1 + 18 usats ~0.72 SR 1 SSO 02/14/22 PSLV-XL C52 EOS-04 + 2usats 1.715 SR 1 SSO 06/30/22 PSLV-CA C53 DS-EO/NeuSAR/POEM ~0.6 SR 2 LEO 11/26/22 PSLV-XL C54 EOS-06 + usats 1.171 SR 1 SSO 04/22/23 PSLV-CA C55 TeLEOS 2 + cubes ~0.76 SR 1 LEO 07/30/23 PSLV-CA C56 DS-SAR 0.423 SR 1 LEO 01/01/24 PSLV-DL C58 XPoSat, POEM-3, etc. 0.47 SR 1 LEO ------------------------------------------------------------------ NOTES: [D1] 1993 D1 - Unsuccessful due to software error in on board guidance and control processor No orbit due attitude control failure [C1] Fourth stage helium pressurant leak caused 130 m/s shortfall. Planned 817km circular sun synchronous not achieved. IRS-1D used >70% of own propellant to reach 742 x 822 km "functional" orbit from low 306 x 822 km x 98.5deg insertion orbit. [C6] First use of Second Launch Pad (SLP) [C8] First Core Alone PSLV. Used big plane change maneuver to reach 550 km x 2.5 deg circular orbit. 352 kg primary payload AGILE (Astro-rivelatore Gamma a Immagini LEggero), an Italian Space Agency gamma-ray observatory, mounted on top of Dual Launch Adapter (DLA). 185 kg Advanced Avionics Module (AAM) was mounted inside DLA to test upgraded avionics for PSLV and GSLV. Stg 4 propellant reduced by 400 kg for this flight. [C11] India's first lunar mission. First PSLV-XL with stretched strap-on boosters. [C22] To planned subsynchronous transfer orbit. IRNSS to lift self to GEO x 29 deg. [C25] Satellite raised itself to trans-Mars trajectory with six perigee burns. India's first Mars orbiting exploration satellite. [C24/C26] To planned subsynchronous transfer orbit. IRNSS to lift self to GEO x 0.0 deg. [C27] To planned subsynchronous transfer orbit. IRNSS to lift self to GEO x 30.5 deg. [C31] To planned subsynchronous transfer orbit. IRNSS to lift self to GEO x 28 deg. [C32] To planned subsynchronous transfer orbit. IRNSS to lift self to GEO x 5.0 deg. [C39] Planned sub-synchronous. PLF failed to separate. 167 x 6555 km x 19.2 deg orbit, far short of planned 650 x 20650 km. [C50] Planned subsynchronous orbit. [C53] To 570 km x 10 deg. POEM is fourth stage with attached experiments. [C54] 0626 UTC. EOS-6 to 732 x 747 km x 98.35 deg. NS 2B/Pixxel TD 1/Astrocast 301-304/Thybolt 1,2 to 500 km x 97.44 deg. [C55] To 585 km x 10 deg orbit. TeLEOS 2 weighed 741 kg. [C56] To 535 km x 5 deg orbit. [C58] To 638x653 km x 5.99 deg orbit for XPoSat, then drop to 343x353 km x 9.66 deg for POEM PS4 hosted sat operations. *ABBREVIATIONS: FLP = First Launch Pad SR = Satish Dhawan Space Center, Sriharikota, India SLP = Second Launch Pad [FTO] = Failed to Orbit GTO = Geosynchronous Transfer Orbit GTO+ = Supersynchronous or High Perigee Transfer Orbit GTO- = Subsynchronous Transfer Orbit GTOi = Inclined GTO GEO = Geosynchronous Orbit HCO = Heliocentric (solar) Orbit HTO = High Earth Transfer Orbit LEO = Low Earth Orbit [LEO] = Unplanned LEO LEO/S (SSO) = Sun Synchronous Low Earth Orbit LEO/P = Polar Low Earth Orbit MEO = Medium Earth Orbit MTO = Medium Earth Transfer Orbit SLV/ASLV Record ------------------------------------------------------------------ SLV-3 E1 August 10, 1979 Partially successful. A jammed valve in the second stage control system resulted in the leak of oxidizer. SLV-3 E2 July 18, 1980 Successful SLV-3 D1 May 31, 1981 Successful SLV-3 D2 April 17, 1983 Successful ASLV-D1 March 24, 1987 Unsuccessful due to non-ignition of first stage ASLV-D2 July 13, 1988 Unsuccessful . The flight was normal only up to 46 seconds after lift off ASLV-D3 May 20, 1992 Successful ASLV-D4 May 4, 1994 Successful ------------------------------------------------------------------ PSLV Vehicle Configurations ------------------------------------------------------------------ LEO GTO Configuration Liftoff Liftoff Payload Payload Height Mass (tonnes) (tonnes) (meters) (tonnes) 200 km x 49.5 deg [800 km x 98 deg] ================================================================== PSLV ("-G") 3.7 t 1.1 t 4 stage PSLV 44.4 m 295 t [1.6 t] +6xS-9 boosters PSLV-CA [1.1 t] 4 stage PSLV 44.4 m 230 t PSLV-DL [~1.3 t] 4 stage PSLV 44.4 m 257 t +2xS-12 boosters PSLV-QL [~1.5] 4xS-12 boosters 44.4 m 287 t PSLV-XL [1.8 t] 1.3 t 4 Stage PSLV 44.4 m 316 t +6xS-12 boosters ================================================================== Vehicle Components ------------------------------------------------------------------ Stg 1 Strap-On Strap-On Stg 2 Stg 3 Stg 4 PLF PS1 Boosters Boosters PS2 PS3 PS4 S138 S9 S12 L40 S7 L2 (PSOM-XL) (6 Ea) (6 Ea) (2 Air- (2 Air- Start) Start) ================================================================== Dia. (m) 2.8 m 1.0 m 1.0 m 2.8 m 2.0 m 2.8 m 3.2 m Length (m) 20.3 m 10.0 m 12.4 m 12.5 m 3.6 m 2.9 m 8.3 m Mp (tonnes) 138 t 8.92 t 12.0 t 40.6 t 7.6 t 2.5 t 41.5 t (>C5) 2.1 t (CA) GLOW (t) 168 t 10.93 t 14.7 t 46.0 t 8.3 t 2.92 t 1.1 t 46.9 t (>C5) 2.52 t (CA) Engine S138 S9 S12 Vikng 4 S7 L2 Engine Mfgr ISRO ISRO ISRO SEP ISRO ISRO Fuel HTPB HTPB HTPB UDMH HTPB MMH Oxidizer N2O4 N2O4 T(SL t) 447.22 t 46.39 t T(Vac t) 500.68 t 51.25 t 73.42 t 73.93 t 33.52 t 1.43 t 81.58 t (>C5) ISP (SL s) 237 s 229 s ISP (Vac s) 269 s 253 s 296 s 294 s 308 s Tburn (s) 98 s 45 s 49 s 162 s 109 s 516.6 s 147 s (>C5) No. Eng 1 1 Ea 1 Ea 1 1 2 ================================================================== Typical PSLV-C Launch Timeline ------------------------------------------------------------------ Time Event Alt/Velocity ------------------------------------------------------------------ T+0 s S125 Core Stage Ignites 0 km T+1.2 s 4 Ground Lit Boosters Ignite - Liftoff 0 km T+25 s 2 Airlit Boosters Ignite 2.4 km T+45 s 4 Ground Lit Boosters Burnout T+68 s 4 Ground Lit Boosters Separate 23.7 km T+90 s 2 Air Lit Boosters Burnout/Separate 42.6 km T+113 s First Stage Burnout/Second Stage Ignition 68.5 km T+157 s Payload Fairing Jettison 117 km T+266 s Second Stage Shutdown/Thrid Stage Ignition 248 km T+389 s Third Stage Shutdown/Sep 425 km Varies Fourth Stage Burn After Coast 800 km typ but varies 7.5 km/s LEO 10 km/s GTO ------------------------------------------------------------------ SPACE LAUNCH REPORT PSLV History India's Space Research Organization (ISRO) introduced the Polar Satellite Launch Vehicle (PSLV) series in 1993. PSLV, designed to lift 1.5 metric ton satellites to sun synchronous polar orbit from Satish Dhawan Space Centre, SHAR, Sriharikota, India, is a conglomerate of Indian and European components. PSLV performance was progressively improved during the 1990s. The standard "G" version, first flown operationally in 1997, stands 44.4 meters tall and weighs 295 metric tons at liftoff. It consists of four stages that use solid and liquid propellants alternately. The first stage uses a 2.8 meter diameter, 20 meter long, 472 ton thrust solid motor that burns 138 tons of propellant for 107 seconds. The first stage is augmented by six solid strap-on boosters that produce 67.5 tons of thrust each for 45 seconds. Four of the strap-on boosters ignite at liftoff. The two air-start strap-ons ignite 25 seconds after liftoff. The strap-on boosters are jettisonned after burn-out. More powerful "XL" boosters carrying 12 tonnes of propellant and producing up to 73.4 tonnes of thrust debuted in 2008. PSLV Second Stage Viking 4 Engine (ISRO)PSLV Second Stage Engine PSLV's 12.5 x 2.8 m PS-2 (L40) second stage is powered by a 73.9 ton-thrust Viking 4 engine that burns unsymmetrical dimethyl hydrazine (UDMH) fuel and nitrogen tetroxide (N2O4) oxidizer for 162 seconds. Viking 4, called "Vikas" by ISRO, was originally built by Europe's SEP for the Ariane 1 launch vehicle. The third stage is another 2.8 meter diameter solid motor. It burns 7.6 tons of propellant for 109 seconds, producing 33.5 tons of thrust. The fourth and final stage is a twin-engine liquid propulsion system that is housed within the payload fairing below the satellite. It burns 2.5 tons of mono-methyl hydrazine (MMH) fuel and nitrogen tetroxide (N2O4) oxidizer. The 1.43 ton thrust stage can burn for up to 420 seconds. The vehicle is controlled by a strap-down inertial navigation/guidance system housed in a vehicle equipment bay that is mounted on top of the fourth stage. An 8.3 meter tall, 3.2 meter diameter payload fairing protects the payload during ascent through the atmosphere. The first PSLV launch, in 1993, failed due to a software guidance error. The second flight one year later successfully boosted India's IRS-P2 Earth resource monitoring satellite into an 820 km x 98.7 degree sun synchronous orbit. Eight PSLV launches occurred during the first 10 years of its use, with six successes. In 2002, PSLV-C4 performed the first PSLV geosynchronous transfer orbit (GTO) mission. The original PSLV/GSLV launch complex was supplemented in 2005 with a new, mobile launch facility. PSLV-C6 was the first rocket to use the pad. Whereas the original pad featured a fixed launch stand and a 75 meter tall mobile service tower, the new "second launch pad" uses rail-mobile launch stands that allow vehicles to be stacked in a vertical integration building located some distance from the launch pad itself. The January 10, 2007 PSLV-C7 mission included the first use of a PSLV dual launch adapter, which deployed both Cartosat 2 and the SRE 1 demonstration recovery capsule and carried a small microsatellite. The PSLV-CA (Core Alone) model premiered on April 23, 2007. The CA model did not include the six strap-on boosters used by the standard PSLV variant. Two small roll control modules and two first stage motor control injection tanks were still attached to the side of the first stage. About 400 kg of propellant was offloaded from the fourth stage compared to the standard PSLV. Chandrayaan 1, India's first lunar orbiter, was launched by the first PSLV-XL variant on October 22, 2008. PSLV-XL, boosted by more powerful, stretched strap-on boosters, weighed 22 tonnes more at liftoff than the standard PSLV. On the C25 mission in November 2013, a PSLV-XL placed India's Mars Orbiter Mission - the country's first Mars mission - into an elliptical orbit from which the spacecraft boosted itself into a trans-Mars trajectory using six perigee burns. Beginning that same year, the launcher became busy orbiting India's first navigation satellite constellation (IRNSS). The PSLV C37 mission, launched on September 26, 2016, was the first time that the rocket had inserted multiple payloads into two separate orbit altitudes. At 2.25 hours duration, it was also the longest PSLV mission to date. References: Jonathan's Space Report Launch Vehicle Database "http://www.planet4589.org/space/lvdb/index.html" Encylopedia Astronautica "http://www.astronautix.com/" Gunter's Space Page "http://www.skyrocket.de/space" SpaceFlightNow "http://www.spaceflightnow.com" "www.isro.org"