The Polar Satellite Launch Vehicle was developed in the decade of the 80s and launched for the first time in 1993, designed to launch medium satellites into orbit. It was at the time the most capable rocket designed by ISRO. It stands out for its very low cost ($18 or 28 Million) and its reliability. It is launched from the Satish Dhawan Space Centre in India.

Height: 44 m

Diameter: 2.8 m

Stages: 4

Mass: 710,000 kg

LEO: 3,800 kg

GTO: 1,200 kg

First Flight: 20 September 1993

Launches: 50

Successes: 47

Partial Failures: 1

Failures: 2

Success Rate: 94%

Reusability: None

Booster

Engine: L40 H Vikas

Engine Number: 2-4-6

Thrust (Sea Level): 3,040 kN

Burn Time: 154 s

Specific Impulse: 262 s (sea level)

Fuel: N₂O₄/UDMH

Height: 12 m

Diameter: 1 m

Mass: 42,700 kg

First Stage

Engine: S200

Engine Number: 1

Thrust (Sea Level): 5,150 kN

Burn Time: 128 s

Specific Impulse: 274 s (sea level)

Fuel: HTPB

Height: 25 m

Diameter: 3,2 m

Mass: 236,000 kg

Second Stage

Engine: Vikas

Engine Number: 2

Thrust: 1,598 kN (vacuum)

Burn Time: 203 s

Specific Impulse: 293 s (sea level)

Fuel: N₂O₄/UDMH

Height: 21,39 m

Diameter: 4 m

Mass: 125,000 kg

Third Stage

Engine: CE-20

Engine Number: 1

Thrust (Sea Level): 200 kN (vacuum)

Burn Time: 643 s

Specific Impulse: 443 s (sea level)

Fuel: Liquid Hydrogen / Liquid Oxygen

Height: 13,54 m

Diameter: 4 m

Mass: 33,000 kg

Launch Cost: $51 Million

The Geosynchronous Satellite Launch Vehicle was launched for the first time in 2001 and is a medium lift launcher that can deliver payloads to geostationary orbit. The project began in 1990, in order to develop a rocket that allowed India to launch satellites into geostationary orbit, without having to rely on other countries. It shares many components and designs from the PSLV rocket.

Height: 49.13 m

Diameter: 2.8 m

Stages: 3

Mass: 414,000 kg

LEO: 5,000 kg

GTO: 2,700 kg

Launches: 13

Successes: 8

Partial Failures: 2

Failures: 3

Success Rate: 61.5%

First Flight: 18 April 2001

Reusability: None

Booster

Engine: L40 H Vikas

Engine Number: 4

Thrust (Sea Level): 3,040 kN

Burn Time: 154 s

Specific Impulse: 262 s (sea level)

Fuel: N₂O₄/UDMH

Height: 19.7 m

Diameter: 2.1 m

Mass: 42,700 kg

First Stage

Engine: S139

Engine Number: 1

Thrust (Sea Level): 4,846 kN

Burn Time: 100 s

Specific Impulse: 237 s (sea level)

Fuel: HTPB

Height: 20.2 m

Diameter: 2.8 m

Mass: 138,000 kg

Second Stage

Engine: GS2 Vikas 4

Engine Number: 1

Thrust: 846 kN (vacuum)

Burn Time: 139 s

Specific Impulse: 295 s (sea level)

Fuel: N₂O₄/UDMH

Height: 11.6 m

Diameter: 2.8 m

Mass: 39,500 kg

Third Stage

Engine: CE-7,5

Engine Number: 1

Thrust (Sea Level): 75 kN (vacuum)

Burn Time: 718 s

Specific Impulse: 454 s (sea level)

Fuel: Liquid Hydrogen / Liquid Oxygen

Height: 8.7 m

Diameter: 2.8 m

Mass: 12,800 kg

Launch Cost: $47 Million

This is a medium lift rocket developed by ISRO that launched for the first time in 2014 (suborbitally) and then in 2017 (reaching orbit). It launched India´s first scientific mission to the moon and it is expected that it will launch the country´s first manned mission to orbit.

Height: 43,4 m

Diameter: 4 m

Stages: 3

Mass: 640,000 kg

LEO: 10,000 kg

GTO: 4,000 kg

Launches: 4

Successes: 4

Partial Failures: 0

Failures: 0

Success Rate: 100%

First Orbital Flight: 5 June 2017

Reusability: None

First Stage

Engine: S200

Engine Number: 1

Thrust (Sea Level): 5,150 kN

Burn Time: 128 s

Specific Impulse: 274 s (sea level)

Fuel: HTPB

Height: 25 m

Diameter: 3,2 m

Mass: 236,000 kg

Second Stage

Engine: Vikas

Engine Number: 2

Thrust: 1,598 kN (vacuum)

Burn Time: 203 s

Specific Impulse: 293 s (sea level)

Fuel: N₂O₄/UDMH

Height: 21,39 m

Diameter: 4 m

Mass: 125,000 kg

Third Stage

Engine: CE-20

Engine Number: 1

Thrust (Sea Level): 200 kN (vacuum)

Burn Time: 643 s

Specific Impulse: 443 s (sea level)

Fuel: Liquid Hydrogen / Liquid Oxygen

Height: 13,54 m

Diameter: 4 m

Mass: 33,000 kg

Launch Cost: $51 Million