Question

An artificial Earth satellite, of mass 3.00 × 10^3 kg, has an elliptical orbit, with a mean altitude of 500 km.
(a) What is its mean value of gravitational potential energy while in orbit?
(b) What is its mean value of orbital kinetic energy?
(c) What is its total energy while in orbit?
(d) If its perigee is 150 km, what is its orbital velocity at perigee?
http://www.pha.jhu.edu/~broholm/l24/node1.html
See the post just before this one.

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