The 3-stage Saturn V rocket that launched the Apollo spacecraft to the moon has the following characteristics: Stage Propellant Weight [t] Structure Weight [t] Thrust Burn Propellant [t] Time [s] 1st 2160 140 3400 150 Kerosene/LO 2nd 420 35 450 390 LH/LO 3rd 100 10 90 480 LH/LO Assuming negligible gravity and drag effects and assuming a constant propellant consumption rate for each stage: Use Matlab or Excel to plot the maximum (final) velocity reached by the entire rocket as a function of the payload weight. (Vary the payload weight between 10 tonnes and 150 tonnes) Note that in general (in the absence of gravity and drag): Thrust[tonnes] = w[tonnes/s] g[m/s] Ueq[m/s] = m Ucq where g=9.81 [m/s] is needed to convert weight to mass, and where W, is the propellant consumption rate.