Hello, :tiphat:
As I'm developping a rocket stage, I'm currently focusing to find realistic values that correlate the stage volume and the mass of the propellants.
So here are the raw data :
Fuel : H2 (liquid)
Oxydizer : O2 (liquid)
Stage dimensions : 4 x 30 meters (cylinder)
(it's a little more than that, but I kept several meters for intertank, tank shapes & engine).
Stage volume : 376.991 m3 (cubic meters) = 376,991 liters
And here are my results :
... based on data I found about the Space Shuttle ET, and using Wolfram Alpha :
LOX tank : 150 kPa ; 90.4°K
LH2 tank : 230 kPa ; 20.4°K
Using an oxidizer/fuel ratio of 6:1 I have :
62,831.833 liters of O2, or 71,642 kg
314,159.167 liters of H2, or 22,302 kg
Total mass of the propellants (LOX/LH2) : 93,944 kilograms.
But when I look at the Shuttle ET data, I feel that the proportions aren't the same... Where am I wrong ? :idk:
Thanks in advance,
As I'm developping a rocket stage, I'm currently focusing to find realistic values that correlate the stage volume and the mass of the propellants.
So here are the raw data :
Fuel : H2 (liquid)
Oxydizer : O2 (liquid)
Stage dimensions : 4 x 30 meters (cylinder)
(it's a little more than that, but I kept several meters for intertank, tank shapes & engine).
Stage volume : 376.991 m3 (cubic meters) = 376,991 liters
And here are my results :
... based on data I found about the Space Shuttle ET, and using Wolfram Alpha :
LOX tank : 150 kPa ; 90.4°K
LH2 tank : 230 kPa ; 20.4°K
Using an oxidizer/fuel ratio of 6:1 I have :
62,831.833 liters of O2, or 71,642 kg
314,159.167 liters of H2, or 22,302 kg
Total mass of the propellants (LOX/LH2) : 93,944 kilograms.
But when I look at the Shuttle ET data, I feel that the proportions aren't the same... Where am I wrong ? :idk:
Thanks in advance,