Launching vehicle of Chandrayaan 2
The launching vehicle used for Chandrayaan2 mission is GSLV -MK III (Geosynchronous Satellite Launch Vehicle mark-III). It is for payloads to GTO (Geostationary transfer orbit). It is three-stage medium-lift launch vehicle It can lift loads of four ton class of satellite into a geostationary transfer orbit. The vehicle has two solid strap-ons, a core liquid booster and a cryogenic upper stage.
A strap on the motor is a booster that is attached to the side of the main stage of a rocket. A core liquid booster consists of liquid fuel and oxidiser as a booster to give hybrid rocket an extra boost at take off. A Cryogenic rocket stage is more efficient and provides more thrust for every kilogram of propellant.
Geosynchronous Satellite is a satellite in a geosynchronous orbit with an orbital period( Orbital period is the time taken by the astronomical object to make one complete orbit around another astronomical object) which is same as the earth rotational period that means 23 hours 56 minutes 4 seconds.
Height – 43.43 m
Vehicle Diameter – 4.0 m
Heat Shield (Payload Fairing) Diameter – 5.0 m
Number of Stages – 3
Lift Off Mass – 640 tonnes
First Stage
First stage consists of two S200 boosters-
| Length | 25 m (82 ft) |
| Diameter | 3.2 m (10 ft) |
| Empty mass | 31,000 kg (68,000 lb) each |
| Gross mass | 236,000 kg (520,000 lb) each |
| Propellant mass ( Propellant is the chemical substance Produces energy or Pressurised gas) | 205,000 kg (452,000 lb) each |
| Motor |
Solid S200 |
| Thrust | 5,150 kN (525 tf) each |
| Specific impulse (Specific impulse is of measure how effectively rocket uses propellant) | 274.5 (vacuum) |
| Burn time | 128 sec |
| Fuel | HTPB (Hydroxyl terminated poly butadiene) |
Second Stage
| Length | 21.39 m (70.2 ft) |
| Diameter | 4.0 m (13.1 ft) |
| Empty mass | 9,000 kg (20,000 lb) |
| Gross mass | 125,000 kg (276,000 lb) |
| Propellant mass | 116,000 kg (256,000 lb) |
| Engines | 2 Vikas engines |
| Thrust | 1,598 kN (163.0 tf) |
| Specific inpulse | 293 sec |
| Burn time | 203 sec |
| Fuel | Unsymetrical dimethyle hydrazine /N2 O4 |
Third Stage
Third stage contains C25-
| Length | 13.545 m (44.44 ft) |
| Diameter | 4.0 m (13.1 ft) |
| Empty mass | 5,000 kg (11,000 lb) |
| Gross mass | 33,000 kg (73,000 lb) |
| Propellant mass | 28,000 kg (62,000 lb) |
| Engines | 1 CE-20 |
| Thrust | 200 kN (20 tf) |
| Specific impulse | 443 sec |
| Burn time | 643 sec |
| Fuel | LOX/LH2(Liquid oxygen Or liquid hydrogen) |
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