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Consider a satellite in an elliptical orbit (with eccentricity e, =0.6). At the perigee of this orbit, it increases its speed in the tangential direction by an amount a=1.6, so
its new speed is now v2=1.6v1.
What is the new orbit's eccentricity? x
If the satellite wishes by this "tangential thrust" to enter a circular orbit, what must a be? x

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