LVM3

---

title: "LVM3" type: doc version: 1 created: 2026-02-28 author: "Wikipedia contributors" status: active scope: public tags: ["launch-vehicle-mark-3", "satish-dhawan-space-centre", "isro-space-launch-vehicles", "expendable-space-launch-systems", "vehicles-introduced-in-2014"] description: "Indian expendable medium-lift launch vehicle, developed by ISRO" topic_path: "general/launch-vehicle-mark-3" source: "https://en.wikipedia.org/wiki/LVM3" license: "CC BY-SA 4.0" wikipedia_page_id: 0 wikipedia_revision_id: 0

::summary Indian expendable medium-lift launch vehicle, developed by ISRO ::

::data[format=table title="Infobox rocket"]

Field	Value
image	LVM3 M6 with BlueBird-6 during Liftoff (3).webp
caption	LVM3 M6 during liftoff from SDSC SLP, carrying BlueBird Block 2 satellite for AST SpaceMobile
name	Launch Vehicle Mark-3
function	Medium-lift launch vehicle
manufacturer	ISRO
country-origin	India
pcost
cpl
height	43.43 m
diameter	4 m
mass	640000 kg
stages	3
location	LEO
kilos	10,000 kg
location	GTO
kilos	4,200 kg
location	TLI
kilos	3,000 kg
family	Geosynchronous Satellite Launch Vehicle
comparable	{{flatlist
status	Active
sites	Satish Dhawan SLP
launches	9
success	9
fail	0
partial	0
first	{{Plainlist
last	24 December 2025
payloads	{{ubl
type	stage
stageno	First
name	S200 Boosters
number	2
length	25 m
diameter	3.2 m
empty	31000 kg each
gross	236000 kg each
propmass	205000 kg each
engines	Solid S200
solid	yes
thrust	5150 kN
total	10300 kN
SI	274.5 isp (vacuum)
burntime	128 s
fuel	HTPB / AP
type	stage
stageno	Second
name	L110
length	21.39 m
diameter	4.0 m
empty	9000 kg
gross	125000 kg
propmass	116000 kg
engines	2 Vikas engines
thrust	1692 kN
SI	293 isp
burntime	203 s
fuel	UDMH / N2O4
type	stage
stageno	Third
name	C25
length	13.545 m
diameter	4.0 m
empty	5000 kg
gross	33000 kg
propmass	28000 kg
engines	1 CE-20
thrust	186.36 kN
SI	442 isp
burntime	643 s
fuel	LOX /
::

| image = LVM3 M6 with BlueBird-6 during Liftoff (3).webp | caption = LVM3 M6 during liftoff from SDSC SLP, carrying BlueBird Block 2 satellite for AST SpaceMobile | name = Launch Vehicle Mark-3 | function = Medium-lift launch vehicle | manufacturer = ISRO | country-origin = India | pcost = | cpl = | alt-cpl = | cpl-year = | height = 43.43 m | diameter = 4 m | mass = 640000 kg | stages = 3 | capacities = | location = LEO | kilos = 10,000 kg | location = GTO | kilos = 4,200 kg | location = TLI | kilos = 3,000 kg | family = Geosynchronous Satellite Launch Vehicle | comparable = {{flatlist|

• Angara
• Ariane 6
• Atlas V
• Falcon 9
• H3
• Long March 3B
• Long March 7
• Zenit | status = Active | sites = Satish Dhawan SLP | launches = 9 | success = 9 | fail = 0 | partial = 0 | first = {{Plainlist|
• 18 December 2014 (suborbital)
• 5 June 2017 (orbital) | last = 24 December 2025 | stage data = | payloads = {{ubl |CARE |GSAT |Chandrayaan-2/3 |OneWeb |Gaganyaan}} |type = stage |diff = |stageno = First |name = S200 Boosters |number = 2 |length = 25 m |diameter = 3.2 m |empty = 31000 kg each |gross = 236000 kg each |propmass = 205000 kg each |engines = Solid S200 |solid = yes |thrust = 5150 kN |total = 10300 kN |SI = 274.5 isp (vacuum) |burntime = 128 s |fuel = HTPB / AP |type = stage |diff = |stageno = Second |name = L110 |length = 21.39 m |diameter = 4.0 m |empty = 9000 kg |gross = 125000 kg |propmass = 116000 kg |engines = 2 Vikas engines |thrust = 1692 kN |SI = 293 isp |burntime = 203 s |fuel = UDMH / N2O4 |type = stage |diff = |stageno = Third |name = C25 |length = 13.545 m |diameter = 4.0 m |empty = 5000 kg |gross = 33000 kg |propmass = 28000 kg |engines = 1 CE-20 |thrust = 186.36 kN |SI = 442 isp |burntime = 643 s |fuel = LOX /

The Launch Vehicle Mark-3 or LVM3 (previously referred as the GSLV Mk III) is a three-stage medium-lift launch vehicle developed by the Indian Space Research Organisation (ISRO). Primarily designed to launch communication satellites into geostationary orbit, it is also due to launch crewed missions under the Indian Human Spaceflight Programme. LVM3 has a higher payload capacity than its predecessor, GSLV.

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 the Satish Dhawan Space Centre.

The total development cost of the project was . In June 2018, the Union Cabinet approved to build 10 LVM3 rockets over a five-year period.

The LVM3 has launched CARE, India's space capsule recovery experiment module, Chandrayaan-2 and Chandrayaan-3, India's second and third lunar missions, and will be used to carry Gaganyaan, the first crewed mission under Indian Human Spaceflight Programme. In March 2022, UK-based global communication satellite provider OneWeb entered into an agreement with ISRO to launch OneWeb satellites aboard the LVM3 along with the PSLV, due to the launch services from Roscosmos being cut off, caused by the Russian invasion of Ukraine. The first launch took place on 22 October 2022, injecting 36 satellites into Low Earth orbit.

History

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. Development of the LVM3 began in the early 2000s, with the first launch planned for 2009–2010. The unsuccessful launch of GSLV D3, due to failure in the cryogenic upper stage, delayed the LVM3 development program. 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). 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. 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.

Vehicle Description

::figure[src="https://upload.wikimedia.org/wikipedia/commons/7/7c/LVM3-X_Vehicle_Configuration.jpg" caption="LVM3-X Configuration"] ::

Specifications

::data[format=table]

Specification	First stage- 2 x S200 Strap-on	Second stage- L110	Third stage- C25 CUS	Length	Diameter	Nozzle Diameter	Propellant	Inert Mass	Propellant Mass	Launch Mass	Case / Tank Material	Segments	Engine(s)	Engine Type	Maximum Thrust (SL)	Avg. Thrust (SL)	Thrust (Vac.)	Specific Impulse (SL)	Specific Impulse (Vac.)	Maximum Pressure	Average Pressure	Engine Dry Weight	Altitude(?) Control	Area Ratio	Flex Nozzle Length	Throat Diameter	Thrust Vector Control	Vector Capability	Slew Rate	Actuator Load	Engine Diameter	Mixture Ratio	Turbopump Speed	Flow Rate	Guidance	Restart Capability	Burn Time	Ignition	Stage Separation	Separation Time
25.75 m	21.39 m	13.545 m
3.20 m	4.0 m	4.0 m
3.27 m	~1.80 m
Solid HTPB-based composite propellant	UH 25 (75% UDMH, 25% hydrazine) /
Nitrogen Tetroxide	Liquid Hydrogen / Liquid Oxygen
31,000 kg	9,000 kg	5,000 kg
205,000 kg	116,000 kg	28,000 kg
236,000 kg	125,000 kg	33,000 kg
M250 Maraging Steel	Aluminium Alloy
3	NA
S200 LSB	2 x Vikas Engine	1 x CE-20
Solid	Gas Generator
5,150 kN	1,588 kN	186.36 kN
3,578.2 kN
NA	756.5 kN	200 kN
227 sec	293 sec	NA
274.5 sec		443 sec
56.92 bar	58.5 bar	60 bar
39.90 bar	NA
NA	900 kg	588 kg
Flex Nozzle Gimbaling	Engine Gimbaling	2 Vernier Engines
12.1	13.99	100
3.474 m	NA
0.886 m	NA
Hydro-Pneumatic Pistons	NA
+/- 8°	NA
10°/sec	NA
294 kN	NA
	0.99 m
NA	1.7 (Ox/Fuel)	5.05 (Ox/Fuel)
NA	10,000 rmp
NA	275 kg/sec
		Inertial Platform, Closed Loop
NA	No	RCS for Coast Phase
130 sec	200 sec	643 sec
T+0 sec	T+110 sec
Pyrotechnic fasteners, Jettison Motors	Active/Passive Collets	NA
T+149 sec
::

S200 solid boosters

::figure[src="https://upload.wikimedia.org/wikipedia/commons/2/24/LVM3_M4_-_S200_Strap-on_thrusting_and_seperation,_onboard_camera_footage.webm" caption="S200 Strap-on: Onboard Camera Footage"] ::

::figure[src="https://upload.wikimedia.org/wikipedia/commons/7/7f/LVM3_M3,_OneWeb_India-2_campaign_04.webp" caption="S200 boosters being integrated prior to LVM3-M4 mission"] ::

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 m wide, 25 m long, and carries 207 t 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 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. The hydraulic fluid for operating these actuators is stored in an externally mounted cylindrical tank at the base of each booster. These boosters burn for 130 seconds and produce an average thrust of 3578.2 kN and a peak thrust of 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.

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 500 tf. 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. A third test, ST-03, was conducted on 14 June 2015 to validate the changes from the sub-orbital test flight data.

L110 liquid core stage

::figure[src="https://upload.wikimedia.org/wikipedia/commons/d/d0/L110_Liquid_Stage_at_Stage_Preparation_Facility.jpg" caption="L110 Stage at Stage Preparation Facility"] ::

The second stage, designated L110, is a liquid-fueled stage that is 21 m tall and 4 m wide, and contains 110 MT of unsymmetrical dimethylhydrazine (UDMH) and nitrogen tetroxide (). It is powered by two Vikas 2 engines, each generating 766 kN thrust, giving a total thrust of 1532 kN. 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. 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.

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. A second static fire test for the full duration was conducted on 8 September 2010.

C25 cryogenic upper stage

::figure[src="https://upload.wikimedia.org/wikipedia/commons/3/3c/C25_Cryogenic_Stage_at_Stage_Preparation_Facility.jpg" caption="C25 Stage at Stage Preparation Facility"] ::

The cryogenic upper stage, designated C25, is 4 m in diameter and 13.5 m long, and contains 28 MT of propellant LOX and LH2, pressurized by helium stored in submerged bottles. It is powered by a single CE-20 engine, producing 200 kN 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. 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. 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 consists of an S-Band system for telemetry downlink and a C-Band transponder that allows for 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. A second static fire test for the full in-flight duration of 640 seconds was completed on 17 February 2017. 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.

Payload fairing

::figure[src="https://upload.wikimedia.org/wikipedia/commons/3/33/LVM3_M2,_OneWeb_India-1_campaign_27.jpg" caption="OneWeb]] satellites"] ::

The CFRP composite payload fairing has a diameter of 5 m, a height of 10.75 m and a payload volume of 110 m3. It is manufactured by Coimbatore-based LMW Advanced Technology Centre. 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. 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 the 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, pushing the payload fairing halves laterally away from the launcher. The fairing is made of aluminum alloy featuring acoustic absorption blankets.

Variants and upgrades

Human-rating certification

Main article: Gaganyaan, CE-20

::figure[src="https://upload.wikimedia.org/wikipedia/commons/5/59/HLVM3.svg" caption="Representation of Human Rated LVM3."] ::

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 5 m diameter payload fairing was used to be able to accommodate large modules like space station segments.

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. 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.

Mating with semi-cryogenic stage

Main article: SE-2000

::figure[src="https://upload.wikimedia.org/wikipedia/commons/4/44/Power_Head_Test_Article_(PHTA)_for_SCE-200.jpg" caption="SE-2000 Power Head Test Article"] ::

The L110 core stage in the LVM3 is planned to be replaced by the SC120, a kerolox stage powered by the SE-2000 engine to increase its payload capacity to 7.5 MT to geostationary transfer orbit (GTO). 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 10 t to GTO. The first propellant tank for the SC120 was delivered in October 2021 by HAL.

The SC120 powered version of LVM3 will not be used for the crewed mission of the Gaganyaan spacecraft. In September 2019, in an interview by AstrotalkUK, S. Somanath, director of Vikram 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. The SE-2000 engine is reported to be based on the Ukrainian RD-810, which is itself proposed for use on the Mayak family of launch vehicles. In 2025, Russia has also offered to integrate the RD-191M engine on future variants of the LVM3.

Induction of upgraded cryogenic stage

The C25 stage with nearly 25 t propellant load will be replaced by the C32, with a higher propellant load of 32 t. The C32 stage will be re-startable and with uprated CE-20 engine. Total mass of avionics will be brought down by using miniaturised components. On 30 November 2020, Hindustan Aeronautics Limited delivered an aluminium alloy-based cryogenic tank to ISRO. The tank has a capacity of 5755 kg of fuel, and a volume of 89 m³.

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. 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. It is hoped that after introduction of this stage, GTO payload capacity can be raised to 6 tonnes.

Launch statistics

Gallery

Notes

References

References

1. "Unit cost of LVM3(Lead)".
2. "The first developmental flight of GSLV-Mk-III".
3. "LVM3".
4. "GSLV MkIII-M1 Successfully Launches Chandrayaan-2 spacecraft - ISRO". [[ISRO]].
5. "GSLV MKIII".
6. (13 November 2025). "Launch Service Requisition : Understanding Launch Demand".
7. "Direct Trans-Lunar injection(TLI) payloads capacity of GSLV Mk-3 is around 3000 kg.".
8. "LVM3".
9. (7 December 2009). "India to test world's third largest solid rocket booster". The Hindu News Paper.
10. "GSLV Mark III-D1 / GSAT-19 Brochure". IRSO.
11. (22 Jul 2019). "Space Launch Report: LVM3 (GSLV Mk 3)".
12. (2022-10-24). "ISRO GSLV Mark-III renamed as LVM-3".
13. (17 December 2014). "As it happened: ISRO successfully launches GSLV Mark-III". [[The Hindu]].
14. (2022-10-23). "ISRO renames GSLV Mark-III as LVM-3". The Hindu.
15. (15 November 2018). "'India masters rocket science': Here's why the new ISRO launch is special". Hindustan Times.
16. (18 October 2018). "Two international astronauts survive space scare. How well is India prepared?".
17. (29 April 2011). "Indian Space Research Organisation preparing for three more PSLV launches". [[The Hindu]].
18. Ramachandran, R.. (22 January 2014). "GSLV MkIII, the next milestone". [[Frontline (magazine).
19. Sengupta, Rudraneil. (5 June 2017). "Cryogenic rocket engine has been developed from scratch: Isro chief". LiveMint.
20. (5 June 2017). "India launches 'monster' rocket". [[BBC News]].
21. (16 June 2017). "India's 'Bahubali' GSLV Mk III lifts less luggage than lighter rockets". [[The Economic Times]].
22. (12 August 2015). "Government of India, Department of Space; Lok Sabha Unstarred Question no.3713; GSLV MK-III".
23. (7 June 2018). "Government approves Rs 10,000-crore continuation programmes for PSLV, GSLV".
24. "OneWeb Suspends Launches from Baikonur as Repercussions from Russia's Invasion of Ukraine Grow".
25. (11 October 2021). "OneWeb partners with Isro to launch satellites using GSLV-MKIII, PSLV".
26. "NSIL/ISRO and OneWeb to collaborate for taking Digital Connectivity to every Corner of the World".
27. [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.
28. "Lok Sabha Unstarred Question No.3713".
29. (2002-08-17). "Development of GSLV-Mk III approved". The Economic Times.
30. (4 April 2013). "India's GSLV Mk-3 First Flight Pushed Back to April 2014".
31. Pulakkat, Hari. "GSLV Mark III launch: Why ISRO's biggest challenge will be at the end of this month". The Economic Times.
32. (26 February 2017). "GSLV Mk-III to put India on top".
33. (19 January 2024). "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".
34. (2024-05-11). "ISRO commercial arm invites private players to build LVM3 rocket that delivered Chandrayaan mission".
35. Simhan, T. E. Raja. (2024-05-10). "NSIL releases RFQ document inviting industry players to productionalise ISRO's heavy lift launcher LVM3".
36. (2024-05-10). "India's NSIL partners with private sector to boost LVM3 production".
37. Dutt, Anonna. (2024-05-27). "LVM3 commercialisation is a big step forward, at right time for India, say experts".
38. "S200 solid booster development".
39. N. Gopal Raj. (3 December 2014). "GSLV Mark III faces its first experimental flight". The Hindu.
40. "LVM3-CARE mission brochure".
41. "GSLV Mk. III Launch Vehicle Overview".
42. "ISRO Press Release: S200 First Static Test (S-200-ST-01)".
43. "Successful static testing of Solid Propellant Booster Rocket Stage S200 for GSLV Mk III Launch Vehicle".
44. "Isro successfully tests world's 3rd largest solid booster". dna.
45. "Second Static Testing of Solid Propellant Booster Rocket Stage S200 for GSLV-Mk III Successfully Conducted".
46. (15 June 2015). "విజయవంతంగా భూస్థిర పరీక్ష". Sakshi.
47. Staff Reporter. (15 June 2015). "Static test of S200 motor successful". The Hindu.
48. (4 January 2010). "L110 test to follow S200".
49. [http://www.isro.org/launchers/lvm3 LVM3] {{webarchive. link. (25 December 2014 ISRO 23 December 2014)
50. "Nozzle closure system for gsLVM3 launch vehicle". ARMS 2008.
51. (8 September 2010). "ISRO successfully conducts static testing of new age rocket". The Hindu.
52. "ISRO Press Release:Successful Static Testing of L 110 Liquid Core Stage of GSLV - Mk III".
53. "Cryogenic Gas Bottle Development & Realization - Role of non-destructive evaluation".
54. "Why ISRO's New Engine and Mk III Rocket Are Reasons to Forget 1990 Cryogenic Scandal".
55. "ISRO's C25 cryogenic stage now sports white, ditches black; What's the science behind it?".
56. "ISRO Successfully Tests C25 Cryogenic Upper Stage of GSLV MkIII".
57. "ISRO Successfully Tests its Cryogenic Stage (C25) for GSLV MkIII for the Flight Duration".
58. . (2024-04-02). ["LMW ATC hands over payload to ISRO for GSLV MK - III"](https://www.thehindu.com/news/cities/Coimbatore/lmw-atc-hands-over-payload-to-isro-for-gslv-mk-iii/article68020688.ece). *The Hindu*.
59. "Outcome Budget 2016-17". Department of Space, Government of India.
60. (15 December 2015). "From Fishing Hamlet to Red Planet: India's Space Journey". HarperCollins Publishers India.
61. (11 August 2021). "PRL Ka Amrut Vyakhyaan-02, 'Reaching the sky: Indian Launch Vehicles'".
62. "CSIR NAL Annual Report 2020-21".
63. Rajwi, Tiki. (2 March 2015). "Semi-cryogenic Engine: ISRO Charting a Revised Plan".
64. (30 May 2015). "ISRO developing heavy lift launch vehicles".
65. "Ukraine to test components of a powerful Indian rocket engine".
66. (2021-10-07). "HAL delivers 'heaviest' Semi-Cryogenic propellant tank to ISRO". The Economic Times.
67. "The ISRO Tender Notice With Fascinating New Details of Gaganyaan".
68. Singh, Surendra. (28 January 2019). "GSLV Mk III: Isro eyes kerosene to boost GSLV Mk III's lifting power to 6 trillion".
69. (October 24, 2019). "Episode 90 – An update on ISRO's activities with S Somanath and R Umamaheshwaran". AstrotalkUK.
70. (19 September 2019). "ISRO moves on, gears up to test semi-cryogenic engine in Ukraine". [[The Hindu]].
71. "MSN".
72. "Report No. 362, Demands for Grants (2022-2023) of the Department of Space (Demand No. 95)".
73. (2021-09-17). "ISRO working on reusable GSLV Mk-III launch vehicle". The Hindu.
74. (2020-11-30). "HAL delivers biggest ever cryogenic propellant tank to ISRO". [[The Financial Express (India).
75. "HAL Delivers Biggest Ever Cryogenic Propellant Tank to ISRO".
76. (2022-11-09). "Successful CE20 uprated Engine Hot Test with 21.8 T vacuum thrust". Indian Space Research Organisation.
77. "Successful CE-20 Engine Hot Test with 20t off-nominal & 22.2t vacuum thrust".
78. Mohandas, Pradeep. (2024-07-13). "ISRO has a problem: too many rockets, too few satellites to launch {{!}} Analysis". The Hindu.

::callout[type=info title="Wikipedia Source"] This article was imported from Wikipedia and is available under the Creative Commons Attribution-ShareAlike 4.0 License. Content has been adapted to SurfDoc format. Original contributors can be found on the article history page. ::