Path: Propulsion/MultiStage
% Converts stage and payload masses to total masses and final masses.
1 2 3 4 ... payload
--------------------------------------------------------------------------
Form:
[m0, mF] = MS2M( mS, eS, mPayload )
--------------------------------------------------------------------------
------
Inputs
------
mS (1,:) Fully fueled mass of the stage
eS (1,:) Stage structural ratios
mpayload (1,1) Payload mass
-------
Outputs
-------
m0 (1,:) Total mass of each stage (including everything above)
mF (1,:) Final mass of each stage (including everything above)
pS (1,:) Stage payload ratios
mSP (1,:) Stage propellant mass
mSS (1,:) Stage structural mass
--------------------------------------------------------------------------
References: Wiesel, W. E., Spaceflight Dynamics, McGraw-Hill, 1988,
pp. 199-202.
--------------------------------------------------------------------------
Back to the Propulsion Module page