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At a given time, a satellite has the following position and velocity vectors: (R vector = 7016I^ + 5036J^ + 766K^ km; V vector =

At a given time, a satellite has the following position and velocity vectors: (R vector = 7016I^ + 5036J^ + 766K^ km; V vector = 0.339I^ - 0.556J^ - 7.696K^ km/s)

Based on this information, determine the size (semimajor axis) of this orbit.

Based on the position and velocity vectors given in problem 1, determine the shape (eccentricity) of this orbit.

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