ISProgram
SketchUp Orbinaut
I've been calculating realistic data for a few rocket concepts I've been working for a while now. Only recently, a problem popped up…
Out of the total volume that a typical rocket tank has, how much of it actually has usable fuel in it? How much is "ullage gas"? How much of that propellant is “reserve” (residual) propellant?
I’m also assuming that different liquid fuels have different ratios/calculations. The chief ones I am actually focusing on are LH2, LOX, and Kerosene/RP-1.
I would also like to note that this is meant to imply that the complete (potential) volume of a rocket tank is known.
Does anyone have any input/documentation about this?
Out of the total volume that a typical rocket tank has, how much of it actually has usable fuel in it? How much is "ullage gas"? How much of that propellant is “reserve” (residual) propellant?
I’m also assuming that different liquid fuels have different ratios/calculations. The chief ones I am actually focusing on are LH2, LOX, and Kerosene/RP-1.
I would also like to note that this is meant to imply that the complete (potential) volume of a rocket tank is known.
Does anyone have any input/documentation about this?
