Geosynchronous Satellite Launch Vehicle
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.
GSLV-F14 carrying INSAT-3DS at the Satish Dhawan Space Centre Second Launch Pad | |
| Function | Medium-lift Launch System |
|---|---|
| Manufacturer | ISRO |
| Country of origin | India |
| Cost per launch | US$47 million |
| Size | |
| Height | 49.13 m (161.2 ft) |
| Diameter | 2.8 m (9 ft 2 in) |
| Mass | 414,750 kg (914,370 lb) |
| Stages | 3 |
| Capacity | |
| Payload to LEO | |
| Mass | 6,000 kg (13,000 lb) |
| Payload to SSO | |
| Mass | 3,000 kg (6,600 lb) |
| Payload to GTO | |
| Mass | 2,500 kg (5,500 lb) |
| Launch history | |
| Status |
|
| Launch sites | Satish Dhawan Space Centre |
| Total launches | 15 |
| Success(es) | 9 |
| Failure(s) | 4 |
| Partial failure(s) | 2 |
| First flight |
|
| Last flight |
|
| Type of passengers/cargo | South Asia Satellite, NavIC |
| Boosters | |
| No. boosters | 4 L40 Hs |
| Height | 19.7 m (65 ft) |
| Diameter | 2.1 m (6 ft 11 in) |
| Propellant mass | 42,700 kg (94,100 lb) each |
| Powered by | 1 L40H Vikas 2 |
| Maximum thrust | 760 kN (170,000 lbf) |
| Total thrust | 3,040 kN (680,000 lbf) |
| Specific impulse | 262 s (2.57 km/s) |
| Burn time | 154 seconds |
| Propellant | N2O4 / UDMH |
| First stage | |
| Height | 20.2 m (66 ft) |
| Diameter | 2.8 m (9 ft 2 in) |
| Propellant mass | 138,200 kg (304,700 lb) |
| Powered by | 1 S139 Booster |
| Maximum thrust | 4,846.9 kN (1,089,600 lbf) |
| Specific impulse | 237 s (2.32 km/s) |
| Burn time | 100 seconds |
| Propellant | HTPB (solid) |
| Second stage | |
| Height | 11.6 m (38 ft) |
| Diameter | 2.8 m (9 ft 2 in) |
| Propellant mass | 39,500 kg (87,100 lb) |
| Powered by | 1 GS2 Vikas 4 |
| Maximum thrust | 846.8 kN (190,400 lbf) |
| Specific impulse | 295 s (2.89 km/s) |
| Burn time | 139 seconds |
| Propellant | N2O4 / UDMH |
| Second GS2 (GL40) stage | |
| Height | 11.9 m (39 ft) |
| Diameter | 2.8 m (9 ft 2 in) |
| Propellant mass | 42,500 kg (93,700 lb) |
| Powered by | 1 GS2 Vikas 4 |
| Maximum thrust | 846.8 kN (190,400 lbf) |
| Specific impulse | 295 s (2.89 km/s) |
| Burn time | 149 seconds |
| Propellant | N2O4 / UDMH |
| Third stage (GSLV Mk I) – CUS | |
| Height | N/A |
| Diameter | 2.8 m (9 ft 2 in) |
| Propellant mass | N/A |
| Powered by | 1 KVD-1 |
| Maximum thrust | 70 kN (16,000 lbf) |
| Specific impulse | 462 s (4.53 km/s) |
| Burn time | N/A |
| Propellant | LOX / LH2 |
| Third stage (GSLV Mk II) – CUS12 | |
| Height | 8.7 m (29 ft) |
| Diameter | 2.8 m (9 ft 2 in) |
| Propellant mass | 12,800 kg (28,200 lb) |
| Powered by | 1 CE-7.5 |
| Maximum thrust | 75 kN (17,000 lbf) |
| Specific impulse | 454 s (4.45 km/s) |
| Burn time | 718 seconds |
| Propellant | LOX / LH2 |
| Third stage (GSLV Mk II) – CUS15 | |
| Height | 9.9 m (32 ft) |
| Diameter | 2.8 m (9 ft 2 in) |
| Propellant mass | 15,000 kg (33,000 lb) |
| Powered by | 1 CE-7.5 |
| Maximum thrust | 75 kN (17,000 lbf) |
| Specific impulse | 454 s (4.45 km/s) |
| Burn time | 846 seconds |
| Propellant | LOX / LH2 |
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