I’ve been trying to calculate how much propellant a spaceship from Earth /LEO/ to Mars /LMO/ at constant acceleration of 1g would need. Here’s the data given: dry mass mf=100 t; g=9,81 m/s^2; Isp=10000 s /ion thruster/; trip duration Earth to Mars at constant acceleration of 1g, decelerating halfway 1d 21h 13m1s = 162781 s, according to this source; Delta V from LEO to LMO = 6,6 km/s, according to this source.
Initial total mass with propellant mo=? Mpropellant=?
From the Isp=10000 s I get the exhaust velocity: Isp=ve/go; ve=Isp x go=10000s x 9,81m/s^2=98100 m/s.
The mass of the propellant /6,9 tons/ and the mass flow rate seem to be too low – are the calculations correct or am I missing something? Also, the only connection to the constant acceleration of 1g was the duration of the trip – should the acceleration be considered in a different equation?
Thank you in advance.