The optimal way of transferring a space vehicle from an inner circular orbit to an outer coplanar circular orbit is to fire its engines as it passes through A to increase its speed and place it in an elliptic transfer orbit. Another increase in speed as it passes through B will place it in the desired circular orbit. For a vehicle in a circular orbit about the earth at an altitude h1 = 200mi which is to be transferred to a circular orbit at an altitude h2 = 500mi

Determine
(a) The required increases in speed at A and at B,
(b) The total energy per unit mass required to execute the transfer.

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6370 km