Srinivas
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then you guys should edit wiki page...
it says N2O4/UDMH as fuel which isnt cryogenic
India has developed two cryogenic engines until now
CE-15 and CE-20
CE-20
Propellant Combination - LOX / LH2
Regarding GSLV:
Liquid boosters
The GSLV uses four L40 liquid strap-on boosters derived from the L37.5 second stage, which are loaded with 40 tons of hypergolic propellants (UDMH & N2O4). The propellants are stored in tandem in two independent tanks 2.1 m diameter. The engine is pump-fed and generates 680 kN (150,000 lbf) of thrust.with burn time of 149sec.
First stage
S139 stage is 2.8 m in diameter and has a nominal burn time of 109sec.
Second stage
The second stage is powered by the Vikas engine. It has 2.8 m diameter.[2]
Third stage[edit]
CUS third stage of GSLV Mk.II D3
The third stage is propelled by a cryogenic rocket engine, 2.8 m in diameter and uses liquid hydrogen (LH2) and liquid oxygen (LOX) in two separate tanks of aluminium alloy interconnected by an inter-stage.[citation needed]
The indigenous cryogenic engine was built in Tamil Nadu, at the Liquid Propulsion Systems Centre at Mahendragiri near Nagercoil.
So cryogenic engine comes into picture at Third stage, The main obstacle in developing the Cryogenic engine is to simulate the space and low temperatures on earth.