A satellite is in an initial elliptical orbit about the Earth ( rE = 6378 km) with perigee altitude hpi = 325 km and apogee altitude hai = 1560 km. The final elliptical orbit has perigee altitude hpf = 950 km and apogee altitude haf = 9600 km. The objective is to design a transfer from apogee of initial orbit to perigee of final orbit. (Use km and seconds in your work).
a. Find E, H, Vp, Va, P for the initial orbit
b. Find E, H, Vp, Va, P for the final orbit
c. Find E, H, Vp, Va, ?t1 for the transfer trajectory
d. Find the time of flight for the transfer trajectory and ?V1, ?V2, ?VT
e. Use MATLAB to draw in one diagram a circle representing the Earth ( rE = 6378 km), initial orbit, transfer trajectory and final orbit. The diagram must be to scale. Draw the Earth center at the origin and remember the Earth center is the primary focus for the orbits. Refer to Figures 2-5-1 and 2-5-2 of book.