Geosynchronous Satellite Launch Vehicle
Template:Short description Template:Use Indian English Template:Use dmy dates Template:Infobox Rocket
Geosynchronous Satellite Launch Vehicle (GSLV) is a class of expendable launch systems operated by the Indian Space Research Organisation (ISRO). GSLV has been used in fifteen launches since 2001.
HistoryEdit
The Geosynchronous Satellite Launch Vehicle (GSLV) project was initiated in 1990 with the objective of acquiring an Indian launch capability for geosynchronous satellites.<ref>Template:Cite journal</ref><ref name=flGSLVQuest>Template:Cite news</ref>
GSLV uses major components that are already proven in the Polar Satellite Launch Vehicle (PSLV) launch vehicles 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 geostationary transfer orbit (GTO) the third stage was to be powered by a LOX/LH2 Cryogenic engine which at that time India did not possess or have the technological expertise to build. The aerodynamic characterization research was conducted at the National Aerospace Laboratories' 1.2m Trisonic Wind Tunnel Facility.<ref>{{#invoke:citation/CS1|citation |CitationClass=web }}</ref>
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, resulting in the rocket gaining the nickname "naughty boy".<ref name="Naughty">{{#invoke:citation/CS1|citation |CitationClass=web }}</ref><ref>{{#invoke:citation/CS1|citation |CitationClass=web }}</ref>
Cryogenic engine controversyEdit
The third stage was to be procured from Russian company Glavkosmos, including transfer of technology and design details of the engine based on an agreement signed in 1991.<ref name=flGSLVQuest/> Russia backed out of the deal after United States objected to the deal as in violation of the Missile Technology Control Regime (MTCR) in May 1992. As a result, ISRO initiated the Cryogenic Upper Stage Project in April 1994 and began developing its own cryogenic engine.<ref name=GSLVGopalRaj>Template:Cite news</ref> 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.<ref>Template:Cite news</ref> These engines were used for the initial flights and were named GSLV Mk I.<ref>{{#invoke:citation/CS1|citation |CitationClass=web }}</ref>
Vehicle descriptionEdit
The Template:Cvt tall GSLV, with a lift-off mass of Template:Cvt, is a three-stage vehicle with solid, liquid and cryogenic stages respectively. The payload fairing, which is Template:Cvt long and Template:Cvt 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 Template:Cvt.<ref name=isroGSLVF04>{{#invoke:citation/CS1|citation |CitationClass=web }}</ref>Template:Needs update
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 Template:Cvt into an easterly low Earth orbit (LEO) or Template:Cvt (for the Mk II version) into an 18° geostationary transfer orbit.
Liquid boostersEdit
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.<ref name=isroGSLVD2>{{#invoke:citation/CS1|citation |CitationClass=web }}</ref> 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 and N2O4). The propellants are stored in tandem in two independent tanks Template:Cvt diameter. The engine is pump-fed and generates Template:Cvt of thrust, with a burn time of 150 seconds.
First stageEdit
GSLV-D1 used the S125 stage which contained Template:Cvt of solid propellant and had a burn time of 100 seconds. All subsequent launches have used enhanced propellant loaded S139 stage.<ref name=isroGSLVD2/> The S139 stage is 2.8 m in diameter and has a nominal burn time of 100 seconds.<ref name=GSLVD3>{{#invoke:citation/CS1|citation |CitationClass=web }}</ref><ref>{{#invoke:citation/CS1|citation |CitationClass=web }}</ref>
Second stageEdit
The GS2 stage is powered by the Vikas engine. It has a diameter of Template:Cvt.<ref name=GSLVD3/>
Third stageEdit
The third stage of the GSLV Mark II is propelled by the Indian CE-7.5 cryogenic rocket engine while the older defunct Mark I is propelled using a Russian made KVD-1. It uses liquid hydrogen (LH2) and liquid oxygen (LOX)<ref>{{#invoke:citation/CS1|citation |CitationClass=web }}</ref> The Indian cryogenic engine was built at the Liquid Propulsion Systems Centre.<ref>{{#invoke:citation/CS1|citation |CitationClass=web }}</ref><ref name=hindu-gslvd3>Template:Cite news</ref> The engine has a default thrust of Template:Cvt but is capable of a maximum thrust of Template:Cvt. In GSLV-F14 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.<ref>{{#invoke:citation/CS1|citation |CitationClass=web }}</ref>
VariantsEdit
GSLV rockets using the Russian Cryogenic Stage (CS) are designated as the GSLV Mark I while versions using the indigenous Cryogenic Upper Stage (CUS) are designated the GSLV Mark II.<ref>{{#invoke:citation/CS1|citation |CitationClass=web }}</ref><ref name=GSLVD3brochure>{{#invoke:citation/CS1|citation |CitationClass=web }}</ref> All GSLV launches have been conducted from the Satish Dhawan Space Centre in Sriharikota.
GSLV Mark IEdit
The first developmental flight of GSLV Mark 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.<ref name="cursci-25jul01">Template:Cite journal</ref><ref name="cursci-10sep03">Template:Cite journal</ref> The fourth operational flight of GSLV Mark I, GSLV-F06, had a longer third stage called the C15 with 15 tonne propellant loading and also employed a Template:No break diameter payload fairing.<ref name=GSLVF06>{{#invoke:citation/CS1|citation |CitationClass=web }}</ref><ref>{{#invoke:citation/CS1|citation |CitationClass=web }}</ref>
GSLV Mark IIEdit
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 Mark I) have used Russian cryogenic engines.<ref>{{#invoke:citation/CS1|citation |CitationClass=web }}</ref>
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 was used for the four Vikas engines first stage boosters on future missions.<ref name=sfn-20180329>Template:Cite news</ref>
A 4m diameter Ogive payload fairing was developed and deployed for the first time in the EOS-03 launch on 12 August 2021, although this launch was a failure due to technical anomalies with the Cryogenic Upper Stage. This will allow GSLV vehicles to accommodate larger payloads.<ref>{{#invoke:citation/CS1|citation |CitationClass=web }}</ref>
As of October 2024, ISRO has stopped selling GSLV Mk II Rockets. Eight known launches are planned with NVS Missions, IDRSS Missions, NISAR Mission, etc.<ref>{{#invoke:citation/CS1|citation |CitationClass=web }}</ref><ref>{{#invoke:citation/CS1|citation |CitationClass=web }}</ref>
RLV-OREXEdit
The Reusable Launch Vehicle Technology Demonstration program, is a prototype spaceplane concept created by ISRO. For the Orbital return Flight experiment, a modified version of the GSLV Mk. II launcher, with the upper Cryogenic Stage replaced with the PS-4 stage from the PSLV is currently in development, as the RLV won't need all the excess energy produced by the CUS .<ref>{{#invoke:citation/CS1|citation |CitationClass=web }}</ref><ref>Template:Cite news</ref>
Launch statisticsEdit
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- Launch system status
Template:Legend Template:Legend
| Variant | Launches | Successes | Failures | Partial failures | |
|---|---|---|---|---|---|
| GSLV Mk. I | 6 | 2 | 2 | 2 | |
| GSLV Mk. II | 10 | 8 | 2 | 0 | |
| Total Template:As of<ref>{{#invoke:citation/CS1|citation | CitationClass=web
}}</ref> |
16 | 10 | 4 | 2 |
- Decade-wise summary of GSLV Launches
| Decade | Successful | Partial success | Failure | Total |
|---|---|---|---|---|
| 2000s | 2 | 2 | 1 | 5 |
| 2010s | 6 | 0 | 2 | 8 |
| 2020s | 2 | 0 | 1 | 3 |
| Total | 10 | 2 | 4 | 16 |
GalleryEdit
{{#invoke:Gallery|gallery}}
See alsoEdit
- SSLV
- Comparison of orbital launchers families
- Comparison of orbital launch systems
- PSLV
- LVM3
- NGLV
- ISRO
- ASLV
- SLV
ReferencesEdit
External linksEdit
Template:Expendable launch systems Template:Indian space programme