Consider a transfer from Earth to Jupiter that has a high-thrust mission AV of 14 km/s. Three different systems are being considered. Assume the structural mass is the same, M, = 300 kg, for each system. The payload mass is 500 kg. For each system determine the: burnout mass, the initial mass, and the propellant mass. For systems b) and c), use a mission AV of 28 km/s to account for the low-thrust trajectory, and also determine the thrust value. a) b) An advanced nuclear thermal rocket with a specific impulse of 1000 s and a tankage factor, TF, of 0.20. A small nuclear electric propulsion system using ion engines with a specific impulse of 5000 s, thrust efficiency of 0.70, a tankage factor of 0.05, a system power of 100 kW, and a power system specific mass of 30 kg/kW. A large nuclear electric propulsion system using ion engines with a specific impulse of 5000 s, thrust efficiency of 0.70, a tankage factor of 0.05, a system power of 1 MW, and a power system specific mass of 3 kg/kW.