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 temperatures.
A cryogenic rocket engine reuires a high mass flow rate to produce more thrust.At room temperature and pressure, both are in gaseous state. Hypothetically, if propellants had been stored as pressurized gases, the size and mass of fuel tanks themselves would severely decrease rocket efficiency. Therefore, to get the required mass flow rate, the only option was to cool the propellants down to cryogenic temperatures (below -183 °C [90 K], -253 °C [20 K]), converting them to liquid form. Hence, all cryogenic rocket engines are also, by definition, either liquid-propellant rocket engines or hybrid rocket engines.
The combination of liquid hydrogen (LH2) fuel and the liquid oxygen (LOX) oxidizer is one of the most widely used.Methane and nitrogen are also used in cryogenics.This is used in upper stages of the rocket .The fuel is stored in very low temperatures and burn at plus hundred degrees few centimeters below.
India has two cryogenic engines developed by ISRO
CE-7.5 uses Staged combustion and produces 73KN thrust
CE-20 uses Gas-generator and produces 200KN thrust
The C25 stage is the most powerful upper stage developed by ISRO and uses Liquid Oxygen (LOX) and Liquid Hydrogen (LH2) propellant combination. The stage carries 27.8 tons of propellants loaded in two independent tanks.The cryogenic stage designated as C25 was tested for a flight duration of 640 seconds at ISRO Propulsion Complex (IPRC) in Mahendragiri.
The development of C25 cryogenic stage began with the approval of GSLV MKIII, the next generation launch vehicle of ISRO, capable of launching 4 ton class spacecraft in Geosynchronous Transfer Orbit (GTO). The vehicle consists of two solid strap-on motors (S200), one earth storable liquid core stage (L110) and the cryogenic stage upper stage (C25).
A cryogenic rocket engine reuires a high mass flow rate to produce more thrust.At room temperature and pressure, both are in gaseous state. Hypothetically, if propellants had been stored as pressurized gases, the size and mass of fuel tanks themselves would severely decrease rocket efficiency. Therefore, to get the required mass flow rate, the only option was to cool the propellants down to cryogenic temperatures (below -183 °C [90 K], -253 °C [20 K]), converting them to liquid form. Hence, all cryogenic rocket engines are also, by definition, either liquid-propellant rocket engines or hybrid rocket engines.
The combination of liquid hydrogen (LH2) fuel and the liquid oxygen (LOX) oxidizer is one of the most widely used.Methane and nitrogen are also used in cryogenics.This is used in upper stages of the rocket .The fuel is stored in very low temperatures and burn at plus hundred degrees few centimeters below.
India has two cryogenic engines developed by ISRO
CE-7.5 uses Staged combustion and produces 73KN thrust
CE-20 uses Gas-generator and produces 200KN thrust
The C25 stage is the most powerful upper stage developed by ISRO and uses Liquid Oxygen (LOX) and Liquid Hydrogen (LH2) propellant combination. The stage carries 27.8 tons of propellants loaded in two independent tanks.The cryogenic stage designated as C25 was tested for a flight duration of 640 seconds at ISRO Propulsion Complex (IPRC) in Mahendragiri.
The development of C25 cryogenic stage began with the approval of GSLV MKIII, the next generation launch vehicle of ISRO, capable of launching 4 ton class spacecraft in Geosynchronous Transfer Orbit (GTO). The vehicle consists of two solid strap-on motors (S200), one earth storable liquid core stage (L110) and the cryogenic stage upper stage (C25).
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