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A bipropellant rocket is a rocket, which uses two liquid or gasous chemicals for propulsion. One component is called typically fuel, the other oxidizer (even when it, in the case of Flour, does not contain oxygen). The propellant combinations of bipropellant rockets are further classified by the storage temperatures, toxicity and  ignition behavior. Propellants which require cooling below -50°C to stay liquid are called cryogen. They can only get filled into the rocket tanks shortly before launch and can't stay liquid for long once inside the tanks. The amount of propellants, which turn to gaseous form and need to be vented outside the tanks is called ''boil-off''.
 
A bipropellant rocket is a rocket, which uses two liquid or gasous chemicals for propulsion. One component is called typically fuel, the other oxidizer (even when it, in the case of Flour, does not contain oxygen). The propellant combinations of bipropellant rockets are further classified by the storage temperatures, toxicity and  ignition behavior. Propellants which require cooling below -50°C to stay liquid are called cryogen. They can only get filled into the rocket tanks shortly before launch and can't stay liquid for long once inside the tanks. The amount of propellants, which turn to gaseous form and need to be vented outside the tanks is called ''boil-off''.
 
A common problem of all liquid fueled rockets are the movements of the liquid propellants inside the tanks, called sloshing. It requires careful design of the tank walls to increase the resistance and also has to be considered inside the control loop design.
 
  
 
Typical fuel combinations are liquid hydrogen and oxygen (called hydrolox) and kerosine plus liquid oxygen (kerolox).
 
Typical fuel combinations are liquid hydrogen and oxygen (called hydrolox) and kerosine plus liquid oxygen (kerolox).
 
===Solid rocket===
 
[[Image:SolidRocket.png|thumb|left|100px|Solid rocket]]
 
 
A solid rocket or solid rocket motor stores all the propellants in solid form inside the [[Combustion chamber|combustion chamber]]. Their advantage is, that, once ignited, they don't shutdown. They are also very simple in design and construction and can deliver very high thrust. Their main disadvantage are their low [[specific impulse]].
 
 
 
Once ignited, thrust can only be terminated by thrust termination devices, which for example lower the chamber pressure below the threshold required for sustaining combustion. This is usually destructive.
 
 
[[Category: Articles]]
 
[[Category:Glossary]]
 

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