Reactant propellant usage is the amount of reactant used to power the pump compared to the amount of propellant used to power the pump. A value of zero means that only propellant is being used to power the pump, for instance a steam engine powered pump.

The reactant propellant usage is usually balanced. Pumps are only used in the most expensive rockets, which by their nature will employ pure oxidizers and no additional propellant. Additional propellant is used only in the cheapest rockets, usually in solution with hydrogen peroxide. Reactant propellant usage is used along with the combustion ratio, exhaust molecular, fuel mass ratio, fuel molecular, oxidizer mass ratio, oxidizer molecular, propellant mass ratio, propellant molecular, propellant usage, pump efficiency and working temperature to calculate the pump energy which is in turn used to calculate the pump boost.

propellant energy = propellant usage * pump efficiency * working temperature * 8,314 J * K / kmol / 0.2

combustion exhaust = combustion ratio / exhaust molecular

uncombustion = 1.0 - combustion ratio

pump energy = propellant energy * propellant mass ratio / propellant molecular + propellant energy * reactant propellant usage * ( fuel mass ratio * ( uncombustion / fuel molecular + combustion exhaust ) + oxidizer mass ratio * ( uncombustion / oxidizer molecular + combustion exhaust ) )

pump boost = pump energy / pump need
 
 

This is used in pumped rocket and rocket cost.
 
 

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