Geosynchronous Satellite Launch Vehicle :
Geosynchronous Satellite Launch Vehicle (GSLV), is an expendable launch system operated by the Indian Space Research Organisation (ISRO). GSLV was used in thirteen launches from 2001 to 2018, with more launches planned. Even though GSLV Mk III shares the name, it is an entirely different launcher.
History :
The Geosynchronous Satellite Launch Vehicle (GSLV) project was initiated in 1990 with the objective of acquiring an Indian launch capability for geosynchronous satellites.
GSLV uses major components that are already proven in the Polar Satellite Launch Vehicle (PSLV) launchers in the form of the S125/S139 solid rocket booster and the liquid-fueled Vikas engine. Due to the thrust required for injecting the satellite in a GTO orbit the third stage was to be powered by a LOX/LH2 Cryogenic engine which at that time India did not possess or had the technology know-how to build one.
The first development flight of the GSLV (Mk.I configuration) was launched on 18 April 2001 was a failure as the payload failed to reach the intended orbit parameters. The launcher was declared operational after the second development flight successfully launched the GSAT-2 satellite. During the initial years from the initial launch to 2014 the launcher had a checkered history with only 2 successful launches out of 7.
Cryogenic Engine Controversy :
The third stage was to be procured from Russian company Glavcosmos, including transfer of technology and design details of the engine based on an agreement signed in 1991. Russia backed out of the deal after US objected to the deal as in violation of the Missile Technology Control Regime (MTCR) May 1992. As a result, ISRO initiated the Cryogenic Upper Stage Project in April 1994 and began developing its own cryogenic engine.[11] A new agreement was signed with Russia for 7 KVD-1 cryogenic stages and 1 ground mock-up stage with no technology transfer, instead of 5 cryogenic stages along with the technology and design as per the earlier agreement. These engines were used for the initial flights and were named GSLV Mk.1.
Vehicle description :
The 49 metres (161 ft) tall GSLV, with a lift-off mass of 415 metric tons (915,000 lb), is a three-stage vehicle with solid, liquid and cryogenic stages respectively. The payload fairing, which is 7.8 metres (26 ft) long and 3.4 metres (11 ft) in diameter, protects the vehicle electronics and the spacecraft during its ascent through the atmosphere. It is discarded when the vehicle reaches an altitude of about 115 km.
GSLV employs S-band telemetry and C-band transponders for enabling vehicle performance monitoring, tracking, range safety / flight safety and preliminary orbit determination. The Redundant Strap Down Inertial Navigation System/Inertial Guidance System of GSLV housed in its equipment bay guides the vehicle from lift-off to spacecraft injection. The digital auto-pilot and closed loop guidance scheme ensure the required altitude maneuver and guide injection of the spacecraft to the specified orbit.
The GSLV can place approximately 5,000 kg (11,000 lb) into an easterly Low Earth orbit or 2,500 kg (5,500 lb)(for the Mk. II version) into an 18° geostationary transfer orbit.
Liquid boosters :
The first GSLV flight, GSLV-D1 used the L40 stage. Subsequent flights of the GSLV used high pressure engines in the strap-on boosters called the L40H. The GSLV uses four L40H liquid strap-on boosters derived from the L37.5 second stage, which are loaded with 42.6 tons of hypergolic propellants (UDMH & N2O4). The propellants are stored in tandem in two independent tanks 2.1 metres (6 ft 11 in) diameter. The engine is pump-fed and generates 760 kilonewtons (170,000 lbf) of thrust, with a burn time of 150 seconds.
First stage :
GSLV-D1 used the S125 stage which contained 125 metric tons (276,000 lb) of solid propellant and had a burn time of 100 seconds. All subsequent launches have used enhanced propellant loaded S139 stage. The S139 stage is 2.8 m in diameter and has a nominal burn time of 109 seconds. The stage generates a maximum thrust of 4700 kN.
Second stage :
The GS2 stage is powered by the Vikas engine. It has a diameter of 2.8 metres (9 ft 2 in).
Third stage :
The third stage of the GSLV Mk.II is propelled by the Indian CE-7.5 cryogenic rocket engine while the older defunct Mk.I is propelled using a Russian made KVD-1. It uses liquid hydrogen (LH2) and liquid oxygen (LOX) The Indian cryogenic engine was built at the Liquid Propulsion Systems Centre The engine has a default thrust of 75 kilonewtons (17,000 lbf) but is capable of a maximum thrust of 93.1 kilonewtons (20,900 lbf).
Variants :
GSLV rockets using the Russian Cryogenic Stage (CS) are designated as the GSLV Mk I while versions using the indigenous Cryogenic Upper Stage (CUS) are designated the GSLV Mk II. All GSLV launches have been conducted from the Satish Dhawan Space Centre in Sriharikota.
GSLV Mk I :
The first developmental flight of GSLV Mk I had a 129 tonne (S125) first stage and was capable of launching around 1500 kg into geostationary transfer orbit. The second developmental flight replaced the S125 stage with S139. It used the same solid motor with 138 tonne propellant loading. The chamber pressure in all liquid engines were enhanced, enabling a higher propellant mass and burn time. These improvements allowed GSLV to carry an additional 300 kg of payload. The fourth operational flight of GSLV Mk I, GSLV-F06, has a 15 tonne propellant loading in the third stage, called the C-15.
GSLV Mk II :
This variant uses an Indian cryogenic engine, the CE-7.5, and is capable of launching 2500 kg into geostationary transfer orbit. Previous GSLV vehicles (GSLV Mk.I) have used Russian cryogenic engines.[25]
For launches from 2018 a 6% increased thrust version of the Vikas engine was developed. It was demonstrated on 29 March 2018 in the GSAT 6A launch second stage. It will be used for the four Vikas engines first stage boosters on future missions.
Launch statistics :
Launch history :
GSLV Mk I (mobile users may switch to landescape mode for better visual ) :
| Flight No. | Date / time (UTC) | Rocket, Configuration | Launch site | Payload | Payload mass | Orbit | User | Launch outcome |
|---|---|---|---|---|---|---|---|---|
| D1 | 18 April 2001 10:13 | Mk I | First Launch Pad | GSAT-1 | 1540 kg | GTO | INSAT | Partial failure |
| Developmental flight, payload placed into lower than planned orbit, and did not have sufficient fuel to reach a usable orbit.[27] 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. | ||||||||
| D2 | 8 May 2003 11:28 | Mk I | First Launch Pad | GSAT-2 | 1825 kg | GTO | INSAT | Success |
| Developmental flight. | ||||||||
| F01 | 20 September 2004 10:31 | Mk I | First Launch Pad | GSAT-3 | 1950 kg | GTO | INSAT | Success |
| First operational flight. | ||||||||
| F02 | 10 July 2006 12:08 | Mk I | Second Launch Pad | INSAT-4C | 2168 kg | GTO | INSAT | Failure |
| Both rocket and satellite had to be destroyed over the Bay of Bengal after the rocket’s trajectory veered outside permitted limits. | ||||||||
| F04 | 2 September 2007 12:51 | Mk I | Second Launch Pad | INSAT-4CR | 2160 kg | GTO | INSAT | Partial failure |
| Apogee lower and inclination higher than expected, due to an error in the guidance subsystem. Eventually the 2160 kg payload reached the designated geostationary transfer orbit. Minor error in orbit inclination corrected by satellite mission operators. Satellite is fully operational and full design life of ten years will be achieved. It completed 6 years in orbit successfully. ISRO claims this GSLV flight to be successful. | ||||||||
| F06 | 25 December 2010 10:34 | Mk I | Second Launch Pad | GSAT-5P | 2310 kg | GTO | INSAT | Failure |
| First flight of GSLV Mk.I (c). Destroyed by range safety officer after loss of control over liquid-fueled boosters.[38] |
GSLV Mk II
| Flight No. | Date / time (UTC) | Rocket, Configuration | Launch site | Payload | Payload mass | Orbit | User | Launch outcome |
|---|---|---|---|---|---|---|---|---|
| D3 | 15 April 2010 10:57 | Mk II | Second Launch Pad | GSAT-4 | 2220 kg | GTO | INSAT | Failure |
| 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. | ||||||||
| D5 | 5 January 2014 10:48 | Mk II | Second Launch Pad | GSAT-14 | 1980 kg | GTO | INSAT | Success |
| 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 metres (130 ft). All the three stages performed successfully.This was the first successful flight of the cryogenic stage which was developed indigenously in India. | ||||||||
| D6 | 27 August 2015 11:22 | Mk II | Second Launch Pad | GSAT-6 | 2117 kg | GTO | INSAT | Success |
| 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 degree 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. | ||||||||
| F05 | 8 September 2016 11:20 | MK II | Second Launch Pad | INSAT-3DR | 2211 kg | GTO | INSAT | Success |
| 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 | ||||||||
| F09 | 5 May 2017 11:27 | Mk II | Second Launch Pad | GSAT-9 / South Asia Satellite | 2230 kg | GTO | INSAT | Success |
| South Asia Satellite was previously named as SAARC Satellite. | ||||||||
| F08 | 29 March 2018 11:26 | Mk II | Second Launch Pad | GSAT-6A | 2140 kg | GTO | INSAT | Success |
| 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. Even though the launch was a success, communication was lost with the satellite 48 hours after launch. | ||||||||
| F11 | 19 December 2018 10:40 | Mk II | Second Launch Pad | GSAT-7A | 2250 kg | GTO | INSAT | Success |
| Used an enhanced version of the Vikas engine called High Thrust Vikas Engine(HTVE) along with uprated cryogenic engine C15. |
Planned launches :
| Date / time (UTC) | Rocket, Configuration | Launch site | Payload | User |
|---|---|---|---|---|
| Late January 2020 | Mk II | Second Launch Pad | GISAT 1 | ISRO |
| 2275 kg | ||||
| July 2020 | Mk II | Second Launch Pad | GISAT 2 | ISRO |
| 2300 kg | ||||
| February 2020 | Mk II | Second Launch Pad | GSAT-32 | ISRO |
| 2020 | Mk II | Second Launch Pad | GSAT-7C | ISRO |
| November 2020 | Mk II | Second Launch Pad | Chandrayaan-3 | ISRO |
| September 2022 | Mk II | Second Launch Pad | NISAR | NASA / ISRO |
| NASA / ISRO collaboration | ||||
| 2022 | Mk II | Second Launch Pad | Insat 3DS | ISRO |
GSLV mk III :
The Geosynchronous Satellite Launch Vehicle Mark III (GSLV Mk III), also referred to as the Launch Vehicle Mark 3 (LVM3), 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 identified as launch vehicle for crewed missions under the Indian Human Spaceflight Programme and dedicated science missions like Chandrayaan-2. The GSLV Mk III has a higher payload capacity than the similarly named GSLV Mk II.
After several delays and a sub-orbital test flight on 18 December 2014, ISRO successfully conducted the first orbital test launch of GSLV Mk III on 5 June 2017 from the Satish Dhawan Space Centre, Andhra Pradesh.
In June 2018, the Union Cabinet approved ₹43.38 billion (US$610 million) to build 10 GSLV Mk III rockets over a five-year period.
GSLV Mk III launched CARE, India’s space capsule recovery experiment module, Chandrayaan-2, India’s second lunar mission and will be used to carry Gaganyaan, the first crewed mission under Indian Human Spaceflight Programme.
History :
Development :
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, future interplanetary exploration and will be human rated to launch crewed missions. Development of the GSLV Mk III began in the early 2000s, with the first launch planned for 2009–2010. The unsuccessful launch of GSLV D3, due to a failure in the cryogenic upper stage, delayed the GSLV Mk III development program. The GSLV Mk III, while sharing a name with the GSLV, it features different systems and components.
S200 static fire tests :
The first static fire test of the S-200 solid rocket booster, ST-01, was conducted on 24 January 2010. The booster fired for 130 seconds and had nominal performance. It generated a peak thrust of about 4,900 kN (1,100,000 lbf). A second static fire test, ST-02, was conducted on 4 September 2011. The booster fired for 140 seconds and had nominal performance. A third test, ST-03, was conducted on 14 June 2015 to validate the changes from the sub-orbital test flight data.
L110 static fire tests :
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 stage tests :
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 was tested for a duration of 50 seconds and had nominal performance.
A second static fire test for the full in-flight duration of 640 seconds was completed on 17 February 2017. This test demonstrated the repeatability of the engine performance along with its sub-systems, including the thrust chamber, gas generator, turbopumps and control components for the full duration. All of the engine parameters had nominal performance.
Redesigns :
After the suborbital test flight of GSLV Mk III, modifications were made to the vehicle to improve performance. The propellant grain geometry of head end segment was changed to a 13-lobed star configuration from a 10-lobed slotted configuration and propellant load was reduced to 205 tonnes (452,000 lb) to improve performance during transsonic flights. The payload fairing was modified to an ogive shape, and the S200 booster nosecones were slanted to improve aerodynamic performance. The inter-tank structure of the C25 cryogenic stage was redesigned for density.
INDIAN SPACE RESEARCH ORGANISATION 