What is the ratio...?

Question

A sattelite is orbiting on an elliptical trajectory around the Earth, which is situated in one of the focuses. If the radius of the planet is R, the height of the satellite at apogee is h(max) and at perigee is h(min), what is the ratio between the minimum orbital velocity, v(min), and the maximum orbital velocity, v(max), of the satellite ?

Answer 1

EDITED.

The semi-major axis of the orbit is [r(min) + r(max)]/2 where r(min) = R+h(min) and r(max) = R+h(max)

The orbital speed is given by v = √[µ(2/r - 1/a)]

The derivation (corrected) is here: http://img528.imageshack.us/img528/3205/ellipticalorbitalvelocics5.png

(I hope I got it right this time.)