An unmanned satellite orbits the earth with a perigee radius of 7000km and an apogee radius of 70,000km. Calculate:
a) the eccentricity of the orbit
b) the semimajor axis of the orbit(km)
c) the period of the orbit(hours)
d) the specific energy of the orbit(km^2/s^2)
e) the true anomaly at which the altitude is 1000km (degrees)
f) Vr and V(perpendicular) at the points found in part (e) (km/s)
g) the speed at the perigee and apogee (km/s)