An ion engine has an initial thrust to weight ratio (T/W) of 0.0001 and a specific impulse of 900 seconds. It adds a free space equivalent velocity (AU) of 150 m/s to a satellite. a) Calculate the propellant mass required if the nuclear reactor on board provides P = 200 kW of power. Thrust and mass flow rates are constant in time. In class we derive the formulas that are in your textbook: P= 1 m U.2 m = mass flow rate, Ue = exhaust velocity, flight time to = (Mo ge Isp/T) [1 - exp(-AU/U.)] where T is thrust. b) For a chemical rocket in outer space (no drag, no gravity) if you add more and more propellant the final velocity increase indefinitely. For this nuclear powered ion engine, will adding more propellant cause the final velocity to increase indefinitely ? Use the above equations to explain. Assume that initial thrust to weight ratio is not changed, and that power (P) and specific impulse do not change