Assignment:
Calculate the force on a satellite due to drag and the mass of propellant needed to overcome the drag force.
Sun synchronous orbit alt = 700 km
Mass of satellite = 800 kg
Assume Cd = 2
Thruster Isp = 80 s
Propellant = N2 (Molecular Weight = 28, etc)
Propellant temperature = 280 K
Length of satellite = 4 m
Width (diameter) of satellite = 1 m
F = (1/2*m)*Cd*A*density*V^2 but how would you calculate the mass of propellant needed.
