GSLV - Credit: ISRC. 7,820 bytes. 98 x 384 pixels.

Indian launcher for geosynchronous satellites using a Lox/LH2 upper stage developed from Russian technology.

LEO Payload: 5,000 kg. to: 200 km Orbit. at: 45.0 degrees. Payload: 2,500 kg. to a: Geosynchronous transfer trajectory. Liftoff Thrust: 694,000 kgf. Total Mass: 402,000 kg. Core Diameter: 2.8 m. Total Length: 49.0 m. Development Cost $: 500.00 million. Launch Price $: 45.00 million. in 1999 price dollars. Flyaway Unit Cost $: 4.00 million. in 1985 unit dollars.

• Stage Number: 0. 2 x GSLV-0 Gross Mass: 45,600 kg. Empty Mass: 5,600 kg. Thrust (vac): 74,950 kgf. Isp: 281 sec. Burn time: 159 sec. Isp(sl): 240 sec. Diameter: 2.1 m. Span: 2.1 m. Length: 19.7 m. Propellants: N2O4/UDMH No Engines: 1. Viking 2

• Stage Number: 1. 1 x GSLV-1 Gross Mass: 157,300 kg. Empty Mass: 28,300 kg. Thrust (vac): 495,590 kgf. Isp: 266 sec. Burn time: 93 sec. Isp(sl): 237 sec. Diameter: 2.8 m. Span: 2.8 m. Length: 20.3 m. Propellants: Solid No Engines: 1. PSLV-1

• Stage Number: 2. 1 x GSLV-2 Gross Mass: 42,900 kg. Empty Mass: 5,400 kg. Thrust (vac): 73,931 kgf. Isp: 295 sec. Burn time: 149 sec. Isp(sl): 200 sec. Diameter: 2.8 m. Span: 2.8 m. Length: 11.6 m. Propellants: N2O4/UDMH No Engines: 1. Viking 4

• Stage Number: 3. 1 x GSLV-3 Gross Mass: 14,600 kg. Empty Mass: 2,200 kg. Thrust (vac): 7,653 kgf. Isp: 460 sec. Burn time: 675 sec. Diameter: 2.8 m. Span: 2.8 m. Length: 8.7 m. Propellants: Lox/LH2 No Engines: 1. RD-56M

• 42 - Isakowitz, Steven J,, International Reference to Space Launch Systems Second Edition, AIAA, Washington DC, 1991.
• 61 - Wilson, Andrew, editor,, Jane's/Interavia Space Directory, Jane's Information Group, Coulsdon, Surrey, 1992 et al.
• 455 - Isakowitz, Steven J,, International Reference to Space Launch Systems Third Edition, AIAA, Washington DC, 2000.