The range rate of a satellite that is in an elliptical orbit with respect to a central body can be determined by r = r (2.1) where (r) is the satellite's range rate, (r) is the satellite's range with respect to the central body, () is the satellite's position with respect to the central body, and (v) is the satellite's velocity with respect to the central body. Beginning with Bernoulli's solution of the relative two-body problem: A. Determine the true anomaly within the elliptical orbit where the magnitude of the range rate is maximized. B. What is the magnitude of the maximum range rate? Your answer should be in terms of the satellite's eccentricity, specific angular momentum, and semilatus rectum.