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

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