At the instant represented in the figure, a small experimental satellite A is ejected from the shuttle orbiter with a velocity vr = 100 m/s relative to the shuttle, directed toward the center of the earth. The shuttle is in a circular orbit of altitude h = 200 km. For the resulting elliptical orbit of the satellite, determine the semimajor axis a and its orientation, the period τ, eccentricity e, apogee speed va, perigee speed vp, rmax, and rmin. Sketch the satellite orbit.
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