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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 temperatures.[1] Notably, these engines were one of the main factors of the ultimate success in reaching the Moon by the Saturn V rocket.[1]
During World War II, when powerful rocket engines were first considered by the German, American and Soviet engineers independently, all discovered that rocket engines need high mass flow rate of both oxidizer and fuel to generate a sufficient thrust. At that time oxygen and low molecular weight hydrocarbons were used as oxidizer and fuel pair. 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 −150 °C, −238 °F), converting them to liquid form. Hence, all cryogenic rocket engines are also, by definition, either liquid-propellant rocket engines or hybrid rocket engines[2].
Various cryogenic fuel-oxidizer combinations have been tried, but the combination of liquid hydrogen (LH2) fuel and the liquid oxygen (LOX) oxidizer is one of the most widely used.[1][3] Both components are easily and cheaply available, and when burned have one of the highest entropy releases by combustion,[4] producing specific impulse up to 450 s (effective exhaust velocity 4.4 km/s).
CONSTRUCTION
The major components of a cryogenic rocket engine are the combustion chamber (thrust chamber), pyrotechnic igniter, fuel injector, fuel cryopumps, oxidizer cryopumps, gas turbine, cryo valves, regulators, the fuel tanks, androcket engine nozzle. In terms of feeding propellants to combustion chamber, cryogenic rocket engines (or, generally, all liquid-propellant engines) work in either an expander cycle, a gas-generator cycle, a staged combustion cycle, or the simplest pressure-fed cycle.
The cryopumps are always turbopumps powered by a flow of fuel through gas turbines. Looking at this aspect, engines can be differentiated into a main flow or a bypass flow configuration. In the main flow design, all the pumped fuel is fed through the gas turbines, and in the end injected to the combustion chamber. In the bypass configuration, the fuel flow is split; the main part goes directly to the combustion chamber to generate thrust, while only a small amount of the fuel goes to the turbine
300 N CRYOGENIC ROCKET ENGINE.
A compact, re-ignitable, pressure fed cryogenic engine with an Isp of 415 sec.
300 N Rocket Engine
This 300 N cryogenic propellant engine has a vacuum Isp of 415 seconds - the highestvalue ever achieved in Europe for an engine of such small size.
Being pressure-fed, the engine assembly is relatively simple and avoids the need for a turbo-pump. The thrust chamber and throat region of the engine are regeneratively cooled using hydrogen propellant. The nozzle extension is radiation cooled.
The engine incorporates a splash-plate injector having a star shaped configuration. Ignition and subsequent re-ignition is achieved using Triethylaluminium (TEA) - which is hypergolic with the oxygen propellant. The number of re-ignitions is a function of the volume of Triethylaluminium accommodated. The engine nominally provides for 1 ignition and 3 re-ignitions using just 1.5 cc of Triethylaluminium. The use of a chemical ignition system enables a very compact design.
The engine needs no pre-cooling prior to ignition. Only the propellant feed lines to the engine propellant valves need be pre-cooled.
Engine construction materials are mainly stainless steel, Nimonic 75 (Chromium-Nickel Alloy) and copper.
The engine has the status of a flight prototype and is available for flight qualification. Currently, 5 prototype engines have been manufactured.
APPLICATIONS
• The 300 N cryogenic engine enables the simplicity of a pressure fed propulsion system whilst offering the performance of a turbo-pump propulsion system.
• Being pressure fed, the engine does not require an additional turbo-pump, with its associated complexity.
• The 300 N cryogenic engine may be used as a main engine in dedicated stages for orbital insertion, orbital transfer, orbital, and interplanetary applications, including:
Upper stages
Kick stages.
Vernier stages.
Transfer stages.
The 300 N cryogenic engine may also be used as a thruster, or thruster cluster with existing cryogenic turbo-pump propulsion systems and stages for such applications as performance augmentation, upgrades, roll control