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A spacecraft departing from a 200 km LEO has a total AV of 10 km/s. Determine the
following:
a) The maximum velocity it can attain upon leaving the solar system and the ejection angle,
relative to periapsis, required to achieve this.
b) The maximum velocity it can attain using a Jupiter fly-by gravity assist. Assume Jupiter
and Earth are in co-planar, circular orbits.

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