In an elliptical orbit, both the speed and the distance of the satellite from the centre of the earth change. We have,

\[K.E.=\frac{1}{2}mv^2\;\;\text{and}\;\;P.E.=-\frac{GMm}{r}\]

When the satellite is closest to the earth, the speed of the satellite $(v)$ is more and the distance of the satellite $(r)$ is less. So, K.E. will be more and P.E. will be less at this point.

When the satellite is farthest from the earth, the speed of the satellite $(v)$ is less and the distance of the satellite $(r)$ is more. So, K.E. will be less and P.E. will be more at this point.

[**Read:** Gravitational Field]