Year milestone 1962

Cryogenic Rocket

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  A cryogenic rocket engine is a rocket engine that uses a cryogenic fuel or oxidizer, that is, its fuel or oxidizer (or both) are gases liquefied and stored at very low temperature.
  
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  A Cryogenic rocket stage is more efficient and provides more thrust for every kilogram of propellant it burns compared to solid and earth-storable liquid propellant rocket stages. Specific impulse achievable with cryogenic propellants (liquid Hydrogen and liquid Oxygen) is much higher compared to earth storable liquid and solid propellants, giving it a substantial payload advantage.
  
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  Oxygen liquefies at -183 deg C and Hydrogen at -253 deg C also entails complex ground support systems like propellant storage and filling systems, cryo engine and stage test facilities, transportation and handling of cryo fluids, and related safety aspects.
  

Difference Between PSLV & GSLV

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  First launch 1993
  
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  Can carry up to 1425 kg satellite in GTO
  
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  Can carry up to 1750 kg in LEO orbit
  
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  For launching Indian remote sensing satellites (IRS)
  
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  Used for Chandrayaan & Mars Mission
  
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  four stages propellant using solid and liquid propulsion systems alternately
  

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  First launch 2001
  
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  Can carry up to 2500 kg satellite in GTO orbit
  
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  Can carry up to 5000 kg satellite in LEO orbit
  
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  Developed mainly for launching Indian National satellites (INSAT)
  
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  The next version is GSLV MK-3
  
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  Three stages propellant using solid, liquid & cryogenic propulsion in order