I have bolded the part that I am most interested in checking, because I am not sure if the formula is valid.
I have been using Excel to find the thrust, power, etc for a NEP mission. I have been using a delta-V map I found online which states that for low thrust, I should multiply by 1.5. So, in SI units:
Required deltaV = 1.5x stated on chart Required thrust time = Hohmann transfer time Wet mass (kg) is payload+reactor+structure+propellant Propellant (kg) is determined by Isp and rocket equation
Thrust in N is determined as (wet mass + dry mass)/2 x delta V / thrust time
Power in kW is thrust x Isp / 125 (based on VASIMR needing 200kW for 5N, 5000s) Structure (kg) = 1/10 x propellant Reactor mass (kg) = 1500 + 12.5 x power Solver in Excel optimizes Isp for maximum payload and wet mass is 8300 kg based on Falcon 9 to GTO. (I am calling GTO and Earth Escape close enough to the same.)
So am I on track or am I completely off?