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.

Geosynchronous satellite for chandrayaan 2
Geosynchronous Satellite Launch Vehicle Mark-III

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
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 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 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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