An unmanned satellite orbits the earth with a perigee radius of 10,000 km and an apogee radius of 100,000 km. Calculate (a) the eccentricity of the orbit; (b) the semimajor axis of the orbit (kilometers); (c) the period of the orbit (hours); (d) the specic energy of the orbit (kilometers squared per seconds squared); (e) the true anomaly at which the altitude is 10,000 km (degrees); (f) vr and vt at the points found in part (e) (kilometers per second); and (g) the speed at perigee and apogee (kilometers per second). {Partial Ans.: (c) 35.66 h; (e) 82.26; (g) 8.513 km/s, 0.8513 km/s}