1. 1. ISROS GEO-SYNCHRONOUS SATELLITE LAUNCH VEHICLE-MARK III (GSLV-MK III) - CREW MODULE ATMOSPHERIC RE-ENTRY EXPERIMENT (CARE)
2. 2. INTRODUCTION The GSLV-III or Geosynchronous Satellite Launch Vehicle Mark III is a launch vehicle under development by the Indian Space Research Organisation. It is intended to launch satellites into geostationary orbit and as a launcher for an Indian crew vehicle. The GSLV MK-3 will feature an Indian cryogenic third stage and a higher payload capacity than the current GSLV.
3. 3. HISTORY Development for the GSLV Mk III began in the early 2000s, with the first launch planned for 2009-2010. Several factors have delayed the program, including the 15 April 2010 failure of the ISRO-developed cryogenic upper stage on the GSLV Mk II. A suborbital flight test of the GSLV Mk3 launcher, without its cryogenic third stage, is planned by end of 2014, and will be used to test a crew module on a suborbital trajectory. The first orbital flight is planned to take place in 2016. The first flight with a crew on board would take place after 2020.
4. 4. DESCRIPTION Stage 1 - Solid boosters The GSLV-III will use two S-200 solid motors, also designated Large Solid Boosters (LSB). Each booster will have a diameter of 3.2 metres, a length of 25 metres, and will contain 200 tonnes of propellant. Stage 2 - Liquid motor The core stage, designated L-110, will be a 4-meter diameter liquid- fueled stage containing 110 tonnes of propellant. It will be the first Indian liquid engine cluster design, and will use two improved Vikas engines, each producing about 700 kilonewtons (70 tf) of thrust.
5. 5. S-200 MOTOR The S-200 motors (200 ton propellant, 25m) are the third largest solid propellant boosters in the world - after the US Space Shuttles booster (440 ton, 37.8m) and Europes Ariane (240 ton, 31.6m) They are being manufactured in a largely automated plant in Shreeharikota built by Indian engineers and industry. Measured in terms of diameter, the S-200 ranks second in the world with 3.2m, with the while Space Shuttle and Ariane measuring 3.6 m and 3.05 m respectively. The S-200 motors have a fuel burn time of 103 secs, against Ariane's 130 sec and Space Shuttle booster's 123 sec. The closely matched thrust levels required from the two S-200 motors is achieved by carefully controlling both the quality of the raw materials used and their subsequent processing. The S200s large nozzle has been equipped with a flex seal, allowing the nozzle to swivel to correct rocket orientation.
6. 6. CREW MODULE (CM) FLIGHT DETAILS DURING EXPERIMENTAL LAUNCH On December 18, 2014 ISRO will conduct an experimental launch of the GSLV Mk-3 launcher sans its C25 Cryogenic Upper Stage (CUS). The experimental flight, officially dubbed as LVM3-X, would be used to test the Crew Module (CM) that ISRO has developed under the ongoing technology development phase of India's Human Spaceflight Program (HSP). The sequence of events during the unmanned Crew Module Atmospheric Re-entry Experiment (CARE) would be as follows. LVM3-X would climb to an altitude of 125 km and achieve a velocity of 5.3 kps. The CM will then separate from the launcher and re-enter the earth's atmosphere. Six liquid-propellant thrusters on the CM will correct any perturbations caused by the separation and steer the spacecraft along the planned atmospheric re-entry flight path. A spacecraft in Earth orbit re-enters the Earth's atmosphere at a velocity of over 28,000-kph. During CARE the CM will re-enter the atmosphere at a much slower 19,000 kph.
7. 7. CONTD. During atmospheric descent the heat shield of the CM will experience temperatures of around 1,000 deg C. (Returning from orbit, because of higher speeds, temperatures could touch 1,600 deg C.) At an altitude of about 15 km, with the CM is travelling at 839 km per hour, a 2.5-m diameter pilot parachute will deploy to yank out a 6.5-m drogue parachute and slow the spacecraft to 180-kph. At an altitude of 5-km, three main parachutes would deploy, each a humongous 31- m in diameter. The CM is expected to splash down in the Bay of Bengal near the Andaman archipelago and will be recovered by Indian Coast Guard and ISRO personnel. The steeper descent during re-entry, as also lower atmospheric re-entry speed, are dictated by the need to keep the splashdown point of the CM within the Bay of Bengal following a sub-orbital trajectory. ISRO has successfully conducted a drop test of the full scale CM to assess its
8. 8. REFERENCES http://delightfultakes.blogspot.in/2014/12/crew-module-cm-of- isros-module.html https://plus.google.com/111762082825574187840/posts https://sites.google.com/site/indianspaceprojects/launchers/gslv- mk-3 http://www.isro.org/gslv-mkiii- x/Imagegallery/launchvehicle_images/gslv-mkiii-x-5.jpg http://d2yhexj5rb8c94.cloudfront.net/sites/default/files/styles/artic le_node_view/public/Rock.jpg
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