How do the K.E. and P.E. of a satellite change when it moves around the earth in elliptical orbit?

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]