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5 An Earth-orbiting satellite is in an elliptical orbit with perigee and apogee altitudes of 300 and 800 km, respectively. Compare the v required to
5
An Earth-orbiting satellite is in an elliptical orbit with perigee and apogee altitudes of 300 and 800 km, respectively. Compare the v required to achieve an escape (i.e., parabolic) trajectory if the impulse occurs at perigee or apogee.
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