mn is the last two digit of your student ID ( For example; if student ID = 110060109 mn=09) Note: =398600 km, RE = 6378km, g0 = = 9.807 Questions 1- An earth satellite is in an orbit with a perigee radius = 74mn km (for mn=09, rp = 7409) and an apogee radius ra = 14000 km. Calculate the true anomaly at 1 hours after perigee passage. (Note: Please do three iterations where E0 = ) 2- An 1000 kg earth satellite is in an orbit with a perigee radius rp = 74mn km (for mn=09, rp 7409) and an apogee radius ra = 14000 km. The satellite will be transferred to 115000 km. radius circular orbit with bielliptic Hohmann transfer ellipse. Let the apogee of the transfer ellipse be 300000 km. Please, find total delta-v, total transfer flight time in hours, and total required propellant if the specific impulse is 300 s.