ISRO Launch Vehicles ISRO LAUNCH VEHICLES SATELLITE LAUNCH VEHICLES SLV ISRO's four-stage Satellite Launch Vehicle (SLV) program was India's first indigenous leap into space, spearheaded by APJ Abdul Kalam. SLV-3 was the first successful launch, which placed Rohini satellite (RS-1) in orbit, on July 18, 1980. LAUNCH HISTORY SIZE CAPACITY Payload to 400 Km LEO: 40 Kg LAUNCH SITES Height: 22 metres (72 ft) TOTAL 4 LAUNCHES Diameter: 1 metre (3.3 ft) Mass: 17,000 kilograms (37,000 Ib) ENGINES 1 solid All four SLV launches occurred from the ENGINES 1 solid SLV Launch Pad at the Sriharikota High Altitude Range. THRUST 26.83 kilonewtons (6,030 lbf) 10 August 1979 17 April 1983 ENGINES 1 solid THRUST 90.7 kilonewtons. (20,400 lbf) THRUST ENGINES 1 solid SPECIFIC IMPULSE 267 kilonewtons. 283 sec (60,000 lbf) THRUST 502.6 kilonewtons (113,000 Ibf) SPECIFIC IMPULSE 277 sec SPECIFIC IMPULSE BURN TIME 33 seconds 267 sec ISRO SPECIFIC IMPULSE BURN TIME 45 seconds 253 sec BURN TIME 40 seconds BURN TIME 49 seconds FUEL Solid FUEL Solid FUEL Solid FUEL Solid SMALL CARRIER ROCKET AUGMENTED SATELLITE LAUNCH VEHICLE ASLV The low-cost five stage Augmented Satellite Launch Vehicle (ASLV) was developed by ISRO, with an objective of launching 150 kg satellites into 140 km LEO. The first successful launch was ASLV-D3, which placed 106 kg SROSS-C satellite into orbit, on May 20, 1992. LAUNCH HISTORY SIZE CAPACITY LAUNCH SITES Height: 24 metres (79 ft) Payload to 400km LEO 150 kilograms (330 lb) 4TOTAL LAUNCHES Diameter: 1 metre (3.3 ft) Mass: 41,000 kilograms (90,000 lb) ENGINES 1 solid All four ASLV launches occurred from the SLV Launch 1 42 %1 Pad at the Sriharikota High Altitude Range. The launch pad was converted to an ASLV launch complex after the closure of SLV launch programme. ENGINES 1 solid ENGINES 1 solid THRUST 35 kilonewtons 24 March 1987 4 May 1994 THRUST (7,900 lbf) 90.7 kilonewtons ENGINES 1 solid (20,400 lbf) THRUST 304 kilonewtons (68,000 lbf) SPECIFIC IMPULSE 281 sec ENGINES 2 solid THRUST 702.6 kilonewtons (158,000 Ibf) SPECIFIC IMPULSE 277 sec THRUST SPECIFIC IMPULSE 502.6 kilonewtons (113,000 Ibf) each BURN TIME 33 seconds 276 sec SPECIFIC IMPULSE BURN TIME 45 seconds ISRO 259 sec SPECIFIC IMPULSE BURN TIME 36 seconds 253 sec BURN TIME 45 seconds BURN TIME 49 seconds FUEL Solid FUEL Solid SMALL ÇARRIER ROCKET FUEL Solid FUEL Solid FUEL Solid PSLV is the most POLAR SATELLITE LAUNCH VEHICLE PSLV 96 successful satellite launch vehicle of India having 96% success rate. ISRO's expendable Polar Satellite Launch Vehicle (PSLV) can place 1050 kg satellites in geo-synchronous transfer orbits and 1600 kg satellites in 620 km polar orbit. The Mars Orbiter Mission (MOM) and Chandrayaan-1 lunar probe are two of the 70 payloads launched by it so far. LAUNCH HISTORY SIZE CAPACITY Height: 44 metres (144 ft) Payload to LEO 3,250 kilograms (7,170 lb) Payload to HCO 1,600 kilograms (3,500 lb) Payload to GTO 1,410 kilograms (3,110 Ib) LAUNCH SITES TOTAL 26 LĂUNCHES Diameter: 2.8 metres (9 ft 2 in) Mass: 294,000 kilograms (648,000 lb) 11 PSLV 9 PSLV-CA 5 PSLV-XL PSLV 20 September 1993 PSLV-CA 23 April 2007 PSLV-XL 22 October 2008 ENGINES Satish Dhawan I24 1 %1 All launches have occurred from the Satish Dhawan Space Centre, known before 2002 as the Sriharikota Range. 2 x PSLV-4 ENGINES 1x PSLV-3 ENGINES THRUST 90 crore($15M) 14 kilonewtons 1 x Vikas THRUST 328 kilonewtons. (74,000 Ibf) (3,100 lbf) ENGINES 1 x PSLV-1 THRUST 800 kilonewtons BOOSTERS SPECIFIC IMPULSE 308 seconds N° BOOSTERS 6 THRUST 4,860 kilonewtons (1,090,000 Ibf) SPECIFIC IMPULSE 294 seconds (180,000 lbf) ENGINES 1x SLV per booster SPECIFIC IMPULSE 293 seconds THRUST 502.600 kilonewtons (112,989 bn BURN TIME 425 seconds SPECIFIC IMPULSE BURN TIME 83 seconds 269 seconds ISRO SPECIFIC IMPULSE 262 seconds BURN TIME 158 seconds BURN TIME 105 seconds FUEL BURN TIME 44 seconds FUEL N,OJUDMH FUEL FUEL MMH/MON MEDIUM LIFT LAUNCH SYSTEM Solid НТРВ FUEL HTPB : PSLV-XL PSLV-XL is the uprated version of Polar Satellite Launch Vehicle in its standard configuration boosted by more powerful, stretched strap-on boosters. Weighing 320 tonnes at lift-off, the vehicle uses larger strap-on motors (PSOM-XL) to achieve higher payload capability. PSOM- XL uses larger 13.5m, 12 tonnes of solid propellants instead of 9 tonnes PSLV. On 29 December 2005. tested the improved version of strap-on booster for the PSLV. The first version of PSLV-XL was the launch of Chandrayaan-1 by PSLV-C11. The payload capability for this variant is 1800 kg compared to 1600 kg for the PSLV-HP (Under development / Proposed) As reported on the website of The New Indian Express newspaper (26 April 2007), PSLV project director N Narayanamoorthy spoke of another version being planned called the PSLV- PSLV PSLV-CA PSLV-3S (Under development/ Proposed) ISRO is also considering the development of a three-stage version of Equipped with six strap-on boosters, The PSLV-CA, CA meaning "Core Alone", model premiered on 23 April this is the standard 2007. The CA model does not include 2007) PSI four-stage PSLV version, which utilizes solid and liquid propulsion systems alternately. It is designed to put payloads weighing up to 1678 Kg into 622 Km Sun the six strap-on boosters used by the PSLV standard variant. Two small roll control modules and two first stage motor control injection tanks were still attached to the side of the first stage. The fourth stage of the CA variant has 400 kg less propellant when compared to its standard version. It currently has capability to launch 1,100 kg to 622 km sun synchronous orbit. used Lin the earlier confiquration the rocket without six HP, standing for 'high performance! It will have improved strap-ons motors, and the payload capability will be raised to 2000 kg. The HP version will be used to launch a constellation of seven navigation satellites strap-on boosters (with the second stage of the four-stage version of ISRO successfully removed) which will be capable of placing 500 kg to LEO. between 2010 and 2012. Among other things, the efficiency of the stage 4 engine will be improved in this version. other variants. Other launches include the RISAT Radar synchronous orbits. Imaging Satellite and GSAT-12. GEOSYNCHRONOUS SATELLITE LAUNCH VEHICLE GSLV Geosynchronous Satellite Launch Vehicle (GSLV) was launched as an expendable launch system by the Indian Space Research Organisation (ISRO). It granted India freedom from dependence on foreign rockets and providers. (GSLV Mk.I & GSLV Mk.II) LAUNCH HISTORY SIZE CAPACITY LAUNCH SITES Height: 49 metres (161 ft) Payload to LEO 5000 kg Payload to GTO 2,000 to 2,500 kilograms TOTAL LAUNCHES Diameter: 2.8 metres (9 ft 2 in) Mass: 402,000 kilograms (886,000 lb) (GSLV Mk.II)-CUS12 ENGINES (GSLV Mk.I)-12KRB 3 94 %1 GSIV Satish Dhawan Mk.I: 18 April 2001 1 CE-7.5 ENGINES 1 KVD-1 Mk.II: 15 April 2010 THRUST ENGINES 2.2 billion($36 million) 73.5 kilonewtons 1 GS2 Vikas 4 THRUST (16,500 lbf) ENGINES 1 S139 69 kilonewtons. (16,000 lbf) BOOSTERS THRUST 720 kilonewtons SPECIFIC IMPULSE N° BOOSTERS 4 454 seconds THRUST 4,700 kilonewtons (1,100,000 Ibf) (160,000 Ibf) ENGINES 1 L4OH Vikas 2 SPECIFIC IMPULSE 460 seconds SPECIFIC IMPULSE THRUST SPECIFIC IMPULSE 295 seconds BURN TIME 680 kilonewtons ISRO BURN TIME 720 seconds (610,000 b) 166 seconds 720 seconds BURN TIME 150 seconds SPECIFIC IMPULSE BURN TIME 100 seconds 262 seconds FUEL BURN TIME 160 seconds FUEL FUEL FUEL HTPB (Solid) LOX/LH2 MEDIUM LIFT LAUNCH SYSTEM N,0,JUDMH LOX/LH2 FUEL N204/UDMH GEOSYNCHRONOUS SATELLITE LAUNCH VEHICLE MARK III GSLV II The Geosynchronous Satellite Launch Vehicle Mark III (GSLV-III) is designed by ISRO to launch heavy satellites into geostationary orbit, and will reduce India's dependence upon foreign rockets for heavy lifting. The GSLV MK-3 will have an indigenous cryogenic stage with higher capacity than GSLV MK-2 and a passive cryogenic third stage. It is also designed to carry a crew module. SIZE CAPACITY LAUNCH SITES Height: 42.4 m Payload to LEO 5000 kg Payload to GTO 2,000 to 2,500 kilograms FIRST Diameter: 4.0 m LAUNCH GSLV Mass: 630,000 Kg C25 Satish Dhawan ENGINES SCHEDULED FOR 2014 L-110 1 CE-20 ENGINES BOOSTERS S-200 THRUST INDIA 2 Vikas 200 kN N° BOOSTERS 2 THRUST 1,600 kN. ENGINES 1 solid SPECIFIC IMPULSE 450 sec THRUST 5151 kN. SPECIFIC IMPULSE ISRO 300 sec BURN TIME 200 seconds BURN TIME 580 seconds FUEL Solid FUEL FUEL UDMH + N,0, BURN TIME LOX/LH2 MID-HEAVY LIFT LAUNCH SYSTEM 130 seconds (f(x) Function Space f @fspace314 STAGE 1 1 STAGE 4 1 STAGE 3 1 STAGE 4 1 STAGE 2 1 STAGE 4 1 STAGE 3 1 STAGE 3 1 STAGE 3 1 STAGE 3 1 STAGE 2 1 STAGE 2 1 STAGE 1 1 STAGE 2 1 SRIHARIKOTA SRIHARIKOTA STAGE 1 SRIHARIKOTA STAGE 1 1 SRIHARIKOTA STAGE 2 1 SRIHARIKOTA STAGE O 1 STAGE 1 1 STAGE 1 1 STAGE O ↑ STAGE O ↑ INDIA DECOMMISSIONED DECOMMISSIONED ACTIVE ACTIVE ACTIVE

ISRO Launch Vehicles

shared by apurvabhelke on Jul 30
The 100th mission of ISRO was successfully launched in 2012. The first flight correction man oeuvre is a significant achievement to the country and the organization that has completed more than 50 yea...


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