Amission under study desires to deliver a 800-kg payload through 8 km/s of av. the spacecraft has 3 kw of electric power available for propulsion. the mission planners want to understand the trade-offs for different thrusters and operating conditions, and they want you to make plots of propellant mass and trip time required versus specific impulse for the following cases. assume xenon is the propellant. a. ion thruster case: the ion thruster can run at full power from 1 kv to 2 kv. for all throttle conditions, assume the following parameters are constant: total efficiency of 55 propellant utilization of 85% beam divergence angle of 12 deg, and double-to-single ion current ratio of 10%. b. hall thruster case: the hall thruster can run at full power from 300 v to 400 v. for all throttle conditions, assume the following parameters are constant: total efficiency of 45%, propellant utilization of 85% beam divergence angle of 25 deg, and double-to-single ion current ratio of 15%.