GEO-SYNCHRONOUS SATELLITE LAUNCH VEHICLE
DATE : April 15, 2010
PLACE : Satish dhawan space centre
SPECIALITY : It was the first satellite
which was using INDIA
STATUS : Failure.
Propulsion system: The power Centre of a launcher.
Specific Impulse (Isp):
Index of efficiency of a propulsion system.
Isp= Thrust / Weight flow rate of propellants.
Traditionally expressed in seconds.
Ispof different propulsion systems (sea-level):
Solid propulsion –265 s
Earth-storable liquid propulsion –285 s
Cryogenic propulsion –450 s
Operating Cycle - Gas Generator.
Propellant Combination - LOX / LH2.
Thrust Nominal (Vacuum) - 200 kN.
Operating Thrust Range - 180 kN to 220 kN.
Chamber Pressure (Nom) - 6 MPa.
Engine Burn Duration (Nom) - 595 seconds.
Total Flow rate - 462 kg/s.
Nozzle Area ratio – 100.
Mass - 588 kg.
High Specific Impulse
Non-toxic and non-corrosive propellants
Non-hypergolic, improved ground safety
Low density of liquid Hydrogen –more structural mass
Low temperature of propellants -Complex storage &
transfer systems and operations
Hazards related to cryogens
Overall cost of propellants relatively high
Need for ignition system.
BECAUSE, SATELLITE ARE BECOMING HEAVIER….
INSAT 1A  –1150 kg
INSAT 2A  –1900 Kg
INSAT 3C  –2750 Kg
INSAT 4A  –3080 kg