What is the energy of rocket fuel?

Answer 1

enough

Answer 2

A liquid oxidizer commonly used liquid oxygen, nitrogen tetroxide, burning agent by the liquid hydrogen, UDMH, kerosene and so on. Modern liquid fuel rocket to engage the Americans out of Goddard: the first is the use of liquid oxygen - kerosene.

Satellite launch rocket fuel to small size, light weight, but the larger issue of heat, so as to reduce the weight of the rocket, the satellite into orbit quickly. Large liquid fuel energy released, the resulting thrust is also large; and easier to control the fuel, the burning time is longer, therefore, the satellite's rockets were powered by liquid fuel.

Liquid propellant rocket engine is a liquid chemical rocket engines. Oxidizer and burning agent must be stored in different storage box. Liquid rocket engine thrust chamber generally, the propellant supply system, engine control system. Liquid propellant thrust chamber is the chemical energy into propulsive force of the important components. It consists of propellant nozzle, the combustion chamber, the nozzle assemblies and other components. Propellant through the injector into the combustion chamber, the atomization, evaporation, mixing and combustion generated over into the combustion products at high speed (25O0 a 5000 m / s) generated from the nozzle thrust out. 2O0 combustion chamber pressures up to atmospheric pressure (about 20OMPa), temperature of 300O ~ 400O ℃, it needs cooling. Propellant supply system is a function of pressure and flow required to transport the propellant combustion chamber. By delivery in different ways, there are extruded (pressure type) and two types of compression pump supply system.Extrusion is the use of high-pressure gas supply system by the regulator after decompression (oxidizer, burning agent flow is determined by adjusting the pressure regulator control) into the oxidizer, burning agent tank, to squeeze into the combustion chamber, respectively, in. Extrusion supply system is only used for small thrust engines. High-thrust engines are supplied with a pump-type system, which is the propellant delivery pump. The function of the engine control system is the engine of the working procedures and operating parameters to regulate and control.Procedures, including engine start, work. Three stages of shutdown, this process is automatically carried out on schedule. Refers to the size of the main thrust of the working parameters, the propellant mixture ratio. The advantages of liquid rocket engine than ascribed (25O ~ 5OO seconds), thrust range (single thrust in a chocolate ~ 700 tonnes force), to repeatedly start, can control the thrust of size, longer working hours and so on.

Liquid rocket propellant, one of the more commonly used are: nitrogen tetroxide - hydrazine (unsymmetrical dimethyl hydrazine, monomethyl hydrazine, hydrazine), liquid oxygen - kerosene, liquid hydrogen - liquid oxygen and so on.

Nitrogen tetroxide - hydrazine propellant is widely used, and there is can be stored, and nitrogen tetroxide and hydrazine ignition after exposure to high reliability.Nitrogen tetroxide - Hydrazine was first used strategic missiles, space launch vehicles was also used.

Soviet SS-7, serving the SS-18, SS-19, the U.S. Hercules, 1,2,3 China's Long March rocket, the Russian Proton rocket, Ariane rockets are 1,2,3,4 In the following four levels of nitrous oxide use - hydrazine propellant.

Nitrogen tetroxide - hydrazine specific impulse can be, about 230 seconds, but the toxicity of propellants and combustion products are large, countries no longer use a new generation of launch vehicles.