 | |
| Function | Medium-lift launch vehicle[1] |
|---|---|
| Manufacturer | ISRO |
| Country of origin | India |
| Cost per launch | ₹402crore (US$48 million)[2] |
| Size | |
| Height | 43.43 m (142.5 ft)[3][1] |
| Diameter | 4 m (13 ft)[3] |
| Mass | 640,000 kg (1,410,000 lb)[1] |
| Stages | 3[1] |
| Capacity | |
| Payload toLEO | |
| Mass | 10,000 kg (22,000 lb)[4][5] |
| Payload toGTO | |
| Mass | 4,200 kg (9,300 lb)[1][6][5] |
| Payload toTLI | |
| Mass | 3,000 kg (6,600 lb)[7][5] |
| Associated rockets | |
| Family | Geosynchronous Satellite Launch Vehicle |
| Comparable | |
| Launch history | |
| Status | Active |
| Launch sites | Satish Dhawan SLP |
| Total launches | 8 |
| Success(es) | 8 |
| Failure | 0 |
| Partial failure | 0 |
| First flight |
|
| Last flight | 2 November 2025 |
| Carries passengers or cargo | |
| First stage – S200 Boosters | |
| Height | 25 m (82 ft)[1] |
| Diameter | 3.2 m (10 ft)[1] |
| Empty mass | 31,000 kg (68,000 lb) each[8] |
| Gross mass | 236,000 kg (520,000 lb) each[8] |
| Propellant mass | 205,000 kg (452,000 lb) each[8] |
| Powered by | Solid S200 |
| Maximum thrust | 5,150 kN (525 tf)[9][10][11] |
| Specific impulse | 274.5 seconds (2.692 km/s) (vacuum)[8] |
| Burn time | 128 s[8] |
| Propellant | HTPB /AP[8] |
| Second stage – L110 | |
| Height | 21.39 m (70.2 ft)[12] |
| Diameter | 4.0 m (13.1 ft)[8] |
| Empty mass | 9,000 kg (20,000 lb)[12] |
| Gross mass | 125,000 kg (276,000 lb)[12] |
| Propellant mass | 116,000 kg (256,000 lb)[12] |
| Powered by | 2Vikas engines |
| Maximum thrust | 1,692 kN (172.5 tf)[8][13][14] |
| Specific impulse | 293 seconds (2.87 km/s)[8] |
| Burn time | 203 s[12] |
| Propellant | UDMH /N2O4 |
| Third stage – C25 | |
| Height | 13.545 m (44.44 ft)[8] |
| Diameter | 4.0 m (13.1 ft)[8] |
| Empty mass | 5,000 kg (11,000 lb)[12] |
| Gross mass | 33,000 kg (73,000 lb)[12] |
| Propellant mass | 28,000 kg (62,000 lb)[8] |
| Powered by | 1CE-20 |
| Maximum thrust | 186.36 kN (19.003 tf)[8] |
| Specific impulse | 442 seconds (4.33 km/s) |
| Burn time | 643 s[8] |
| Propellant | LOX /LH2 |
TheLaunch Vehicle Mark-3 orLVM3[1][15][16] (previously referred as theGSLV Mk III)[a] is athree-stagemedium-lift launch vehicle developed byISRO.[1] Primarily designed to launch communication satellites intogeostationary orbit,[18] it is also due to launch crewed missions under theIndian Human Spaceflight Programme.[19] LVM3 has a higher payload capacity than its predecessor,GSLV.[20][21][22][23]
After several delays and a sub-orbital test flight on 18 December 2014, ISRO successfully conducted the first orbital test launch of LVM3 on 5 June 2017 from theSatish Dhawan Space Centre.[24]
Total development cost of project was₹2,962.78 crore (equivalent to₹45 billion or US$530 million in 2023).[25] In June 2018, the Union Cabinet approved₹4,338 crore (equivalent to₹58 billion or US$690 million in 2023) to build 10 LVM3 rockets over a five-year period.[26]
The LVM3 has launchedCARE, India's space capsule recovery experiment module,Chandrayaan-2 andChandrayaan-3, India's second and third lunar missions, and will be used to carryGaganyaan, the first crewed mission under Indian Human Spaceflight Programme. In March 2022, UK-based global communication satellite providerOneWeb entered into an agreement with ISRO to launch OneWeb satellites aboard the LVM3 along with thePSLV, due to the launch services from Roscosmos being cut off, caused by theRussian invasion of Ukraine.[27][28][29] The first launch took place on 22 October 2022, injecting 36 satellites intoLow Earth orbit.
ISRO initially planned two launcher families, thePolar Satellite Launch Vehicle forlow Earth orbit andpolar launches and the largerGeosynchronous Satellite Launch Vehicle for payloads togeostationary 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.[30] Development of the LVM3 began in the early 2000s, with the first launch planned for 2009–2010.[31][32][33] The unsuccessful launch ofGSLV D3, due to failure in the cryogenic upper stage,[33] delayed the LVM3 development program.[34][35] The LVM3, although named "GSLV Mark III" during development, features different systems and components from the GSLV Mark II.
To manufacture the LVM3 inpublic–private partnership (PPP) mode, ISRO andNewSpace 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).[36] On Friday 10 May 2024, NSIL released arequest for qualification (RFQ), inviting responses from private partners for the large-scale production of LVM-3.[37][38][39] 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.[40]
| Specification | First stage- 2 x S200 Strap-on | Second stage- L110 | Third stage- C25 CUS |
|---|---|---|---|
| Length | 25.75 m | 21.39 m | 13.545 m |
| Diameter | 3.20 m | 4.0 m | 4.0 m |
| Nozzle Diameter | 3.27 m | ~1.80 m | |
| Propellant | SolidHTPB-basedcomposite propellant | UH 25 (75%UDMH, 25%hydrazine) /Nitrogen Tetroxide | Liquid Hydrogen /Liquid Oxygen |
| Inert Mass | 31,000 kg | 9,000 kg | 5,000 kg |
| Propellant Mass | 205,000 kg | 116,000 kg | 28,000 kg |
| Launch Mass | 236,000 kg | 125,000 kg | 33,000 kg |
| Case / Tank Material | M250Maraging Steel | Aluminium Alloy | |
| Segments | 3 | NA | |
| Engine(s) | S200 LSB | 2 xVikas Engine | 1 xCE-20 |
| Engine Type | Solid | Gas Generator | |
| Maximum Thrust (SL) | 5,150 kN | 1,588 kN | 186.36 kN |
| Avg. Thrust (SL) | 3,578.2 kN | ||
| Thrust (Vac.) | NA | 756.5 kN | 200 kN |
| Specific Impulse (SL) | 227 sec | 293 sec | NA |
| Specific Impulse (Vac.) | 274.5 sec | 443 sec | |
| Maximum Pressure | 56.92 bar | 58.5 bar | 60 bar |
| Average Pressure | 39.90 bar | NA | |
| Engine Dry Weight | NA | 900 kg | 588 kg |
| Altitude Control | Flex Nozzle Gimbaling | Engine Gimbaling | 2 Vernier Engines |
| Area Ratio | 12.1 | 13.99 | 100 |
| Flex Nozzle Length | 3.474 m | NA | |
| Throat Diameter | 0.886 m | NA | |
| Thrust Vector Control | Hydro-Pneumatic Pistons | NA | |
| Vector Capability | +/- 8° | NA | |
| Slew Rate | 10°/sec | NA | |
| Actuator Load | 294 kN | NA | |
| Engine Diameter | 0.99 m | ||
| Mixture Ratio | NA | 1.7 (Ox/Fuel) | 5.05 (Ox/Fuel) |
| Turbopump Speed | NA | 10,000 rmp | |
| Flow Rate | NA | 275 kg/sec | |
| Guidance | Inertial Platform, Closed Loop | ||
| Restart Capability | NA | No | RCS for Coast Phase |
| Burn Time | 130 sec | 200 sec | 643 sec |
| Ignition | T+0 sec | T+110 sec | |
| Stage Separation | Pyrotechnic fasteners, Jettison Motors | Active/Passive Collets | NA |
| Separation Time | T+149 sec | ||
The first stage consists of two S200 solid motors, also known as Large Solid Boosters (LSB) attached to the core stage. Each booster is 3.2 metres (10 ft) wide, 25 metres (82 ft) long, and carries 207 tonnes (456,000 lb) ofhydroxyl-terminated polybutadiene (HTPB) based propellant in three segments with casings made out ofM250 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 theSLS SRBs, theSpace Shuttle SRBs and theAriane 5 SRBs. The flex nozzles can be vectored up to ±8° byelectro-hydraulic actuators with a capacity of 294 kilonewtons (66,000 lbf) 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.[41][42][43] The hydraulic fluid for operating these actuators is stored in an externally mounted cylindrical tank at the base of each booster.[44] These boosters burn for 130 seconds and produce an average thrust of 3,578.2 kilonewtons (804,400 lbf) and a peak thrust of 5,150 kilonewtons (1,160,000 lbf) each. The simultaneous separation from core stage occurs at T+149 seconds in a normal flight and is initiated usingpyrotechnic separation devices and six small solid-fueledjettison motors located in the nose and aft segments of the boosters.[42][9]
The firststatic fire test of the S200solid rocket booster, ST-01, was conducted on 24 January 2010.[9] The booster fired for 130 seconds and had nominal performance throughout the burn. It generated a peak thrust of about 4,900 kN (1,100,000 lbf).[45][10] 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.[46] A third test, ST-03, was conducted on 14 June 2015 to validate the changes from the sub-orbital test flight data.[47][48]
The second stage, designatedL110, is a liquid-fueled stage that is 21 metres (69 ft) tall and 4 metres (13 ft) wide, and contains 110 metric tons (240,000 lb) ofunsymmetrical dimethylhydrazine (UDMH) andnitrogen tetroxide (N2O4). It is powered by twoVikas 2 engines, each generating 766 kilonewtons (172,000 lbf) thrust, giving a total thrust of 1,532 kilonewtons (344,000 lbf).[13][14] The L110 is the first clusteredliquid-fueled engine designed in India. The Vikas engines usesregenerative cooling, providing improved weight andspecific impulse compared to earlier Indian rockets.[42][49] 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.[42][14] 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 is jettisoned prior to L110 ignition.[50]
ISRO conducted the first static test of the L110 core stage at its Liquid Propulsion Systems Centre (LPSC) test facility atMahendragiri,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.[51] A second static fire test for the full duration was conducted on 8 September 2010.[52]
The cryogenicupper stage, designatedC25, is 4 metres (13 ft) in diameter and 13.5 metres (44 ft) long, and contains 28 metric tons (62,000 lb) of propellantLOX andLH2, pressurized by helium stored in submerged bottles.[49][53] It is powered by a singleCE-20 engine, producing 200 kN (45,000 lbf) of thrust. CE-20 is the first cryogenic engine developed by India which uses agas generator, as compared to thestaged combustion engines used in GSLV.[54] 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.[55] The stage also houses theflight computers and Redundant Strap DownInertial 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 consists of anS-Band system for telemetry downlink and aC-Band transponder that allows for radar tracking and preliminary orbit determination are also mounted on the C25. The communications link is also used forrange safety and flight termination that uses a dedicated system that is located on all stages of the vehicle and features separate avionics.[42]
The first static fire test of theC25 cryogenic stage was conducted on 25 January 2017 at theISRO Propulsion Complex (IPRC) facility at Mahendragiri, Tamil Nadu. The stage fired for a duration of 50 seconds and performed nominally.[56] A second static fire test for the full in-flight duration of 640 seconds was completed on 17 February 2017.[57] 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.[57]
The CFRP compositepayload fairing has a diameter of 5 metres (16 ft), a height of 10.75 metres (35.3 ft) and a payload volume of 110 cubic metres (3,900 cu ft).[8] It is manufactured by Coimbatore-basedLMW Advanced Technology Centre.[58] After the first flight of the rocket withCARE module, the payload fairing was modified to anogive shape, and the S200 boosternose cones and inter-tank structure were redesigned to have better aerodynamic performance.[59] 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 andjettisoning mechanism (zip cord) spanning the full length of PLF which ispyrotechnically initiated. The gas pressure generated by thezip cord expands a rubber below that pushes the piston and cylinder apart, pushing the payload fairing halves laterally away from the launcher. The fairing is made of aluminum alloy featuringacoustic absorption blankets.[42]
While the LVM3 is being human rated forGaganyaan project, the rocket was always designed with potential human spaceflight applications in consideration. The maximum acceleration during ascent phase of flight was limited to4 Gs for crew comfort and a 5-metre (16 ft) diameter payload fairing was used to be able to accommodate large modules like space station segments.[60]
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.[61] Avionics improvement will incorporate a Quad-redundantNavigation and Guidance Computer (NGC), Dual chain Telemetry & Telecommand Processor (TTCP) and an Integrated Health Monitoring System (LVHM). The launch vehicle will have theHigh 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 threeO-rings each. Electro mechanical actuators and digital stage controllers will be employed in HS200, L110 and C25 stages.[62]
_for_SCE-200.jpg)
The L110 core stage in the LVM3 is planned to be replaced by the SC120, akerolox stage powered by theSE-2000 engine[63] to increase its payload capacity to 7.5 metric tons (17,000 lb) togeostationary transfer orbit (GTO).[64] The SCE-200 uses kerosene instead ofunsymmetrical 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 10 tonnes (22,000 lb) to GTO.[65] The first propellant tank for the SC120 was delivered in October 2021 by HAL.[66]
The SC120 powered version of LVM3 will not be used for the crewed mission of theGaganyaan spacecraft.[67][68] In September 2019, in an interview by AstrotalkUK,S. Somanath, director ofVikram Sarabhai Space Centre claimed that the SE-2000 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 SE-2000 engine, so an upgraded version of the LVM3 was not expected before 2022.[69] The SE-2000 engine is reported to be based on the UkrainianRD-810, which is itself proposed for use on theMayak family of launch vehicles.[70]
The C25 stage with nearly 25 t (55,000 lb) propellant load will be replaced by the C32, with a higher propellant load of 32 t (71,000 lb). The C32 stage will be re-startable and with uprated CE-20 engine.[71] Total mass of avionics will be brought down by using miniaturised components.[72] On 30 November 2020,Hindustan Aeronautics Limited delivered an aluminium alloy-based cryogenic tank to ISRO. The tank has a capacity of 5,755 kg (12,688 lb) of fuel, and a volume of 89 m3 (3,100 cu ft).[73][74]
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 450 kg (990 lb).[75] On 23 December 2022, CE-20 engine E9 was hot tested for a duration of 650 seconds. For the first 40 seconds of the 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.[76] It is hoped that after introduction of this stage, GTO payload capacity can be raised to 6 tonnes.[77]
LVM3 currently has accumulated a total of 8 launches, as of 2 November 2025[update]. Of these, all 8 have been successful, giving it a cumulative success rate of100%.
| Decade | Successful | Partial success | Failure | Total |
|---|---|---|---|---|
| 2010s | 4 | 0 | 0 | 4[78] |
| 2020s | 4 | 0 | 0 | 4 |
| Total | 8 | 0 | 0 | 8 |
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.
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."
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.
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 crewed 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.
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.
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