Meriam, Kraige & Bolton — Kinetics of Particles: Problem 3_242

3/242 At the instant represented in the figure, a small experimental satellite \(A\) is ejected from the shuttle orbiter with a velocity \(v_r = 100\text{ m/s}\) relative to the shuttle, directed toward the center of the earth. The shuttle is in a circular orbit of altitude \(h = 200\text{ km}\). For the resulting elliptical orbit of the satellite, determine the semimajor axis \(a\) and its orientation, the period \(\tau\), eccentricity \(e\), apogee speed \(v_a\), perigee speed \(v_p\), \(r_{\max}\), and \(r_{\min}\). Sketch the satellite orbit.