Bipropellantteihin

Bipropellantteihin refers to a type of rocket propellant system that utilizes two separate components, a fuel and an oxidizer, which are mixed and combusted in a rocket engine to produce thrust. This is in contrast to monopropellant systems, which use a single substance that decomposes or reacts to generate thrust. Bipropellant systems are widely used in rocketry due to their higher performance capabilities compared to monopropellants.

The two components of a bipropellant system are stored in separate tanks and are fed to the combustion chamber by a propellant feed system. Upon mixing and ignition, a chemical reaction occurs, releasing a large amount of energy and producing hot gases that are expelled through a nozzle at high velocity. This expulsion of mass creates the reactive force, or thrust, that propels the rocket.

Common bipropellant combinations include liquid hydrogen and liquid oxygen (LH2/LOX), which offer very high specific impulse but require cryogenic storage. Kerosene (RP-1) and liquid oxygen (LOX) are another popular choice, offering a good balance of performance and ease of handling. Hypergolic propellants, such as hydrazine and nitrogen tetroxide, are also bipropellants that ignite spontaneously upon contact, simplifying engine design and enabling rapid restarts. The choice of bipropellant depends on mission requirements, such as desired thrust, specific impulse, storability, and cost.