Elliptical Orbit Speed at Perigee
A satellite of mass m is in a circular orbit of radius r around Earth with speed v₀. The satellite’s orbit is changed to an elliptical path that has the same total mechanical energy and an apogee of 2r. What is the speed of the satellite at perigee, expressed in terms of v₀?
A
v = \(\frac{2}{\sqrt{3}}\) v_{0}
B
C
D
v = \(\sqrt{2}\) v_{0}
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