Geosynchronous Satellite Launch Vehicle

Geosynchronous Satellite Launch Vehicle

GSLV-F16 during Liftoff carrying NISAR for NASA and ISRO
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)
Payload to Venus
Mass	247 kg (545 lb) to 1,346 kg (2,967 lb) (direct transfer)
Payload to Mars
Mass	350 kg (770 lb) to 1,390 kg (3,060 lb) (direct transfer)
Launch history
Status	Mk I: Retired Mk II: Active
Launch sites	Satish Dhawan Space Centre
Total launches	19
Success(es)	13
Failure	4
Partial failure	2
First flight	Mk.I: 18 April 2001 Mk.II: 15 April 2010
Last flight	Mk.I: 25 December 2010 Mk.II: 3 September 2026
Carries passengers or cargo	INSAT GSAT (South Asia Satellite) GISAT NVS NISAR
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 Vikas-1+
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
Maximum thrust	4,846.9 kN (1,089,600 lbf)
Specific impulse	237 s (2.32 km/s)
Burn time	100 seconds
Propellant	HTPB
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 Vikas-2B
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 Vikas-2B
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

Geosynchronous Satellite Launch Vehicle (GSLV) is a class of expendable launch systems operated by ISRO. GSLV has been used in eighteen launches since 2001.