1. The problem statement, all variables and given/known data A satellite is in an elliptical orbit about the Earth. The center of the earth is a focus of the elliptical orbit. The perigee (C) is the point in the orbit where the satellite is closest to the Earth's center (F). The perigee distance (P) is the distance from the perigee to the earth's center. The apogee (D) is the point furtheest from the earth's center. The apogee distance (A) is the distance from the apogee to the earth's center. Show that the eccentricity of the orbit in terms of A and P is e=(A-p)/(A+P). 3. The attempt at a solution Not sure where to begin, i know the distance from the center of the orbit to F is sqrt(a^2 - b^2), where a is the semi-major axis and b is the semi-minor axis.