See attached image for problem description and diagram. I am confused as to how to solve this problem (part A) because of the following. I know the altitude, and hence, radius of the circular orbit that both satellites are initially in. Since we know the radius, we can calculate the period of the circular orbit at r=6778.14 km. Also, we know the velocity via the vis-viva relation. Calculating, I get an orbital period of 5553.631036 seconds and a velocity of 7.668552229 km/s. I left so many significant figures because I don't know how precise I will need to be yet. Now, the satellite T is 4 n.mi or 7.408 km (1 n.mi = 1.852 km) ahead of A. If the two satellites are to dock at point P after A makes one full orbit on its new trajectory, then satellite T will arrive at P in [(2*pi*R)-7.408 km]/[7.668552229 km/s] = 5552.666626 seconds from the time of the maneuver at P to put satellite A on its new trajectory that will ultimately meet with satellite A at point P. The problem for me is How can we calculate the change in velocity required for satellite A from its original velocity on the circular orbit if we do not have any information about the new orbit's radius, or even if it is circular or not? I just can't seem to figure out how we'd find the new velocity of A. Additionally, we are told that satellite A's velocity needs to decrease to put it in the new orbit. But how do we find this velocity?