A manned orbiter is on a known circular orbit of radius R. At time t=0, the orbiter deploys a tethered satellite from a known initial position r = rxi + ryj + rzk and velocity vo = vxi + vyj + vzk in a reference coordinate frame relative to the orbiter. Outline in detail a strategy to find the distance and speed of the satellite relative to the orbiter after a given time has elapsed. Include the equations to be solved and the initial conditions.