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India’s First Cryogenic GSLV-D3 2010 Mission
Felt bad when I saw this. I dont know why this happened, but I am sure we will make it next time
I was thinking what is this Cryogenic technology, that makes it so complex for us ?
A cryogenic rocket engine is a rocket engine that uses a cryogenic fuel and/or oxidizer, that is, its fuel and/or oxidizer are gasses liquified at cryogenic temperatures.
The use of liquid fuel rocket engines was first considered by the German, American and Soviet engineers independently, and all discovered that rocket engines need high mass flow rate for both liquid oxidizer and fuel, for generating the necessary thrust. Higher thrust levels were achieved when liquid oxygen (LOX) and liquid hydrocarbon were used as fuel. At room temperature and pressure, oxygen and low molecular weight hydrocarbons are in gaseous state. To get the required mass flow rate, the only option is to feed them to the engine in liquid form. Therefore, they are converted to liquid form by cooling them down, and are stored in the rocket’s fuel tanks at very low temperatures. Hence engines that use these fuels are called cryogenic rocket engines.
Various cryogenic fuel-oxidizer combinations have been tried, but the liquid oxygen (LOX) oxidizer and liquid hydrogen (LH2) fuel combination is one of the most widely used. Both components are easily and cheaply available, bio-friendly, non-corrosive and when burned have the highest entropy release by combustion, among all non-toxic pairs. Liquefaction temperature of oxygen is 89 kelvins and at this temperature LOX achieves a density of 1,140 kg/m3 (1.14 g/cm3). And, for hydrogen it is 20 kelvins, a few kelvins above absolute zero, and gains a density of 70 kg/m3 (70 mg/cm3). All cryogenic rocket engines work on expander cycle or gas-generator cycle or staged combustion cycle depending on thrust requirement, since the oxidizer and fuel are at sub-zero temperatures. LOX LH2 cryogenic rocket engines produce specific impulse up to 450 s (4.4 kN·s/kg).





