Maximum orbital speed in satellite's motion

Question

Hey guys, I tried many different approaches in order to solve this problem and I didn't manage to. Hopefully some of you would be able to help me figure this out I post the problem here:
A research satellite circularizes orbits in an elliptical course a planet with the mass of M. When the satellite reaches its closest position in its orbit to the star M we know that the tangential velocity is V1 and the vector-radius is R1. What is the satellite tangential speed in its most far position in its orbit?

Comments

you don't provide enough data. Start from wiki