At the instant represented in the figure, a small experimental satellite A is ejected from the shuttle orbiter with a velocity v_r = 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 v_a, perigee speed v_p, r_max, and r_min. Sketch the satellite orbit.

Transcribed Image Text:

A y ん レー-ズ