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Geosynchronous Satellite Launch Vehicle
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<h2 id="history">History</h2> <p>The Geosynchronous Satellite Launch Vehicle (GSLV) project was initiated in 1990 with the objective of acquiring an Indian launch capability for <a href="/facts/Geosynchronous_satellite/xWRv8lAL">geosynchronous satellites</a>.<a class="footnote-ref" id="fnref:1" href="#fn:1"><sup>1</sup></a><a class="footnote-ref" id="fnref:2" href="#fn:2"><sup>2</sup></a> </p><p>GSLV uses major components that are already proven in the <a href="/facts/Polar_Satellite_Launch_Vehicle/KantsJM7">Polar Satellite Launch Vehicle</a> (PSLV) launch vehicles in the form of the S125/S139 <a href="/facts/Solid_rocket_booster/Fw48fMUf">solid rocket booster</a> and the <a href="/facts/Liquid-propellant_rocket/TAonrVDn">liquid-fueled</a> <a href="/facts/Vikas_(rocket_engine)/lSKcTgRE">Vikas engine</a>. Due to the thrust required for injecting the satellite in a <a href="/facts/Geostationary_transfer_orbit/1WwL0SPz">geostationary transfer orbit</a> (GTO) the third stage was to be powered by a <a href="/facts/LOX/qnI0KDTb">LOX</a>/<a href="/facts/LH2/Vpk3Gb8P">LH2</a> 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 <a href="/facts/National_Aerospace_Laboratories/f9qdpYvP">National Aerospace Laboratories</a>' 1.2m Trisonic Wind Tunnel Facility.<a class="footnote-ref" id="fnref:3" href="#fn:3"><sup>3</sup></a> </p> <p>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 <a href="/facts/GSAT-2/mTt2cRHG">GSAT-2</a> 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".<a class="footnote-ref" id="fnref:4" href="#fn:4"><sup>4</sup></a><a class="footnote-ref" id="fnref:5" href="#fn:5"><sup>5</sup></a> </p> <h3>Cryogenic engine controversy</h3> <p>The third stage was to be procured from Russian company <a href="/facts/Glavkosmos/Yf5qRehv">Glavkosmos</a>, including transfer of technology and design details of the engine based on an agreement signed in 1991.<a class="footnote-ref" id="fnref:6" href="#fn:6"><sup>6</sup></a> Russia backed out of the deal after United States objected to the deal as in violation of the <a href="/facts/Missile_Technology_Control_Regime/M6RoEAtU">Missile Technology Control Regime</a> (MTCR) in May 1992. As a result, ISRO initiated the Cryogenic Upper Stage Project in April 1994 and began developing its own cryogenic engine.<a class="footnote-ref" id="fnref:7" href="#fn:7"><sup>7</sup></a> A new agreement was signed with Russia for 7 <a href="/facts/KVD-1/76eMRN7K">KVD-1</a> 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.<a class="footnote-ref" id="fnref:8" href="#fn:8"><sup>8</sup></a> These engines were used for the initial flights and were named GSLV Mk I.<a class="footnote-ref" id="fnref:9" href="#fn:9"><sup>9</sup></a> </p> <h2 id="vehicle-description">Vehicle description</h2> <p>The 49 m (161 ft) tall GSLV, with a lift-off mass of 415 t (408 long tons; 457 short tons), is a three-stage vehicle with solid, liquid and cryogenic stages respectively. The payload fairing, which is 7.8 m (26 ft) long and 3.4 m (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 (71 mi).<a class="footnote-ref" id="fnref:10" href="#fn:10"><sup>10</sup></a>[<i>needs update</i>] </p><p>GSLV employs <a href="/facts/S_band/MF3nveB7">S-band</a> telemetry and <a href="/facts/C_band_(IEEE)/vLddLTc2">C-band</a> 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. </p><p>The GSLV can place approximately 5,000 kg (11,000 lb) into an easterly <a href="/facts/Low_Earth_orbit/rq1TwayJ">low Earth orbit</a> (LEO) or 2,500 kg (5,500 lb) (for the Mk II version) into an 18° <a href="/facts/Geostationary_transfer_orbit/1WwL0SPz">geostationary transfer orbit</a>. </p> <h3>Liquid boosters</h3> <p>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.<a class="footnote-ref" id="fnref:11" href="#fn:11"><sup>11</sup></a> The GSLV uses four L40H <a href="/facts/Liquid_rocket_booster/4xKL8mb5">liquid strap-on boosters</a> derived from the L37.5 second stage, which are loaded with 42.6 tons of <a href="/facts/Hypergolic/p0Goa3rn">hypergolic</a> propellants (<a href="/facts/Unsymmetrical_dimethylhydrazine/g08Fzo2D">UDMH</a> and <a href="/facts/Dinitrogen_tetroxide/01WfnHJh">N2O4</a>). The propellants are stored in tandem in two independent tanks 2.1 m (6 ft 11 in) diameter. The engine is <a href="/facts/Pump-fed_engine/TAonrVDn">pump-fed</a> and generates 760 kN (170,000 lbf) of thrust, with a burn time of 150 seconds. </p> <h3>First stage</h3> <p>GSLV-D1 used the S125 stage which contained 125 t (123 long tons; 138 short tons) of solid propellant and had a burn time of 100 seconds. All subsequent launches have used enhanced propellant loaded S139 stage.<a class="footnote-ref" id="fnref:12" href="#fn:12"><sup>12</sup></a> The S139 stage is 2.8 m in diameter and has a nominal burn time of 100 seconds.<a class="footnote-ref" id="fnref:13" href="#fn:13"><sup>13</sup></a><a class="footnote-ref" id="fnref:14" href="#fn:14"><sup>14</sup></a> </p> <h3>Second stage</h3> <p>The GS2 stage is powered by the <a href="/facts/Vikas_(rocket_engine)/lSKcTgRE">Vikas engine</a>. It has a diameter of 2.8 m (9 ft 2 in).<a class="footnote-ref" id="fnref:15" href="#fn:15"><sup>15</sup></a> </p> <h3>Third stage</h3> <p>The third stage of the GSLV Mark II is propelled by the Indian <a href="/facts/CE-7.5/BhNXKT7y">CE-7.5</a> <a href="/facts/Cryogenic_rocket_engine/MCUrNQ51">cryogenic rocket engine</a> while the older defunct Mark I is propelled using a Russian made <a href="/facts/KVD-1/76eMRN7K">KVD-1</a>. It uses liquid hydrogen (LH2) and liquid oxygen (LOX)<a class="footnote-ref" id="fnref:16" href="#fn:16"><sup>16</sup></a> The Indian cryogenic engine was built at the <a href="/facts/Liquid_Propulsion_Systems_Centre/WJsn3f3P">Liquid Propulsion Systems Centre</a>.<a class="footnote-ref" id="fnref:17" href="#fn:17"><sup>17</sup></a><a class="footnote-ref" id="fnref:18" href="#fn:18"><sup>18</sup></a> The engine has a default thrust of 75 kN (17,000 lbf) but is capable of a maximum thrust of 93.1 kN (20,900 lbf). 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.<a class="footnote-ref" id="fnref:19" href="#fn:19"><sup>19</sup></a> </p> <h2 id="variants">Variants</h2> <p>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.<a class="footnote-ref" id="fnref:20" href="#fn:20"><sup>20</sup></a><a class="footnote-ref" id="fnref:21" href="#fn:21"><sup>21</sup></a> All GSLV launches have been conducted from the <a href="/facts/Satish_Dhawan_Space_Centre/GkXD3tL3">Satish Dhawan Space Centre</a> in <a href="/facts/Sriharikota/xplNcm07">Sriharikota</a>. </p> <h3>GSLV Mark I</h3> <p>The first developmental flight of GSLV Mark I had a 129 tonne (S125) first stage and was capable of launching around 1500 kg into <a href="/facts/Geostationary_transfer_orbit/1WwL0SPz">geostationary transfer orbit</a>. 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.<a class="footnote-ref" id="fnref:22" href="#fn:22"><sup>22</sup></a><a class="footnote-ref" id="fnref:23" href="#fn:23"><sup>23</sup></a> 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 4 meter diameter payload fairing.<a class="footnote-ref" id="fnref:24" href="#fn:24"><sup>24</sup></a><a class="footnote-ref" id="fnref:25" href="#fn:25"><sup>25</sup></a> </p> <h3>GSLV Mark II</h3> <p>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.<a class="footnote-ref" id="fnref:26" href="#fn:26"><sup>26</sup></a> </p><p>For launches from 2018, a 6% increased thrust version of the Vikas engine was developed. It was demonstrated on 29 March 2018 in the <a href="/facts/GSAT-6A/mLY71ywT">GSAT-6A</a> launch second stage. It was used for the four Vikas engines first stage boosters on future missions.<a class="footnote-ref" id="fnref:27" href="#fn:27"><sup>27</sup></a> </p><p>A 4m diameter Ogive payload fairing was developed and deployed for the first time in the <a href="/facts/GEO_Imaging_Satellite/fdzMrNzd">EOS-03</a> 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.<a class="footnote-ref" id="fnref:28" href="#fn:28"><sup>28</sup></a> </p><p>As of October 2024, ISRO has stopped selling GSLV Mk II Rockets. Eight known launches are planned with <a href="/facts/IRNSS/k3JM5NBx">NVS</a> Missions, <a href="/facts/Indian_Data_Relay_Satellite_System/GVpdBcUk">IDRSS</a> Missions, <a href="/facts/NISAR/mwTIRBWq">NISAR</a> Mission, etc.<a class="footnote-ref" id="fnref:29" href="#fn:29"><sup>29</sup></a> </p> <h3>RLV-OREX</h3> <p>The <a href="/facts/RLV_Technology_Demonstration_Programme/aHQMPH1P">Reusable Launch Vehicle Technology Demonstration program</a>, is a prototype <a href="/facts/Spaceplane/oMJNJPy7">spaceplane</a> 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 .<a class="footnote-ref" id="fnref:30" href="#fn:30"><sup>30</sup></a><a class="footnote-ref" id="fnref:31" href="#fn:31"><sup>31</sup></a> </p> <h2 id="launch-statistics">Launch statistics</h2> <p class="note">Main article: <a href="/facts/List_of_GSLV_launches/zXUEnHyu">List of GSLV launches</a></p> Launch system status Active Retired <table><tbody><tr><th>Variant</th><th>Launches</th><th>Successes</th><th>Failures</th><th>Partial failures</th></tr><tr><td>GSLV Mk. I</td><td>6</td><td>2</td><td>2</td><td>2</td></tr><tr><td>GSLV Mk. II</td><td>10</td><td>8</td><td>2</td><td>0</td></tr><tr><td>Total as of February 2024<a href="https://en.wikipedia.org/w/index.php?title=Geosynchronous_Satellite_Launch_Vehicle&action=edit">[update]</a><a class="footnote-ref" id="fnref:32" href="#fn:32"><sup>32</sup></a></td><td>16</td><td>10</td><td>4</td><td>2</td></tr></tbody></table> Decade-wise summary of GSLV Launches <table><tbody><tr><th>Decade</th><th>Successful</th><th>Partial success</th><th>Failure</th><th>Total</th></tr><tr><td>2000s</td><td>2</td><td>2</td><td>1</td><td>5</td></tr><tr><td>2010s</td><td>6</td><td>0</td><td>2</td><td>8</td></tr><tr><td>2020s</td><td>2</td><td>0</td><td>1</td><td>3</td></tr><tr><td>Total</td><td>10</td><td>2</td><td>4</td><td>16</td></tr></tbody></table> <h2 id="gallery">Gallery</h2> <h2 id="see-also">See also</h2> <ul> <li>India portal</li><li>Rocketry portal</li><li>Spaceflight portal</li></ul> <ul><li><a href="/facts/Small_Satellite_Launch_Vehicle/Wxsr06H0">SSLV</a></li> <li><a href="/facts/Comparison_of_orbital_launchers_families/w5HG4Juq">Comparison of orbital launchers families</a></li> <li><a href="/facts/Comparison_of_orbital_launch_systems/lSEHGfUx">Comparison of orbital launch systems</a></li> <li><a href="/facts/Polar_Satellite_Launch_Vehicle/KantsJM7">PSLV</a></li> <li><a href="/facts/LVM3/BHqVWNrW">LVM3</a></li> <li><a href="/facts/Next_Generation_Launch_Vehicle/jSAGVXkP">NGLV</a></li> <li><a href="/facts/Indian_Space_Research_Organisation/CdAoFQTL">ISRO</a></li> <li><a href="/facts/Augmented_Satellite_Launch_Vehicle/FnryGps5">ASLV</a></li> <li><a href="/facts/Satellite_Launch_Vehicle/dnXfRelf">SLV</a></li></ul> <h2 id="external-links">External links</h2> Wikimedia Commons has media related to Geosynchronous Satellite Launch Vehicle. <ul><li><a href="https://web.archive.org/web/20110824113407/http://www.isro.org/launchvehicles/gslv/gslv.aspx">ISRO GSLV Page</a></li> <li><a href="https://web.archive.org/web/20091027103917/http://geocities.com/hari_ghk/gslv.htm">INDIA in Space – GSLV Page</a></li> <li><a href="https://web.archive.org/web/20070301125317/http://www.khrunichev.ru/khrunichev_eng/live/full_razg.asp?id=13182">12KRB (KVD-1) Upper Stage at Khrunichev Space Center</a></li></ul> <h2 id="references">References</h2> <ol> <li id="fn:1"><p>"GSLV Launched Successfully" (PDF). Current Science. 80 (10): 1256. May 2001. Retrieved 12 December 2013. <a href="http://www.iisc.ernet.in/currsci/may252001/1254.pdf" target="_blank">http://www.iisc.ernet.in/currsci/may252001/1254.pdf</a> <a href="#fnref:1" class="footnote-back-ref">↩</a></p></li> <li id="fn:2"><p>Subramanian, T. S. (17–31 March 2001). "The GSLV Quest". Frontline. Retrieved 12 December 2013. <a href="http://www.frontline.in/navigation/?type=static&page=flonnet&rdurl=fl1806/18060820.htm" target="_blank">http://www.frontline.in/navigation/?type=static&page=flonnet&rdurl=fl1806/18060820.htm</a> <a href="#fnref:2" class="footnote-back-ref">↩</a></p></li> <li id="fn:3"><p>"Bengaluru: 1.2m trisonic wind tunnel at National Aerospace Laboratories completes 55 years of service". ANI. 6 June 2022. 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