Calculate the propellant mass required to launch a 2000 kg spacecraft from a 180 km circular orbit on a hohmann transfer trajectory to saturn. calculate the time required for the mission. assume the propulsion system has a specific impulse of 300 s.

t = 12,105.96 sec

Explanation:

Given data:

weight of spacecraft is 2000 kg

circular orbit distance to saturn = 180 km

specific impulse = 300 sec

saturn orbit around the sun R_2 = 1.43 *10^9 km

earth orbit around the sun R_1= 149.6 * 10^ 6 km

time required for the mission is given as t

where

is gravitational parameter of sun =  1.32712 x 10^20 m^3 s^2.

t = 12,105.96 sec

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