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)