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 `h_(1) = 320 km`, which is to be transferred to a circular orbit at an altitude `h_(2) = 800 km`, determine :
(a) The required increases in speed at A and B.
(b) The total energy per unit mass required to execute the

Answer

(a) `Deltav_(A) = 147 m//s; Deltav_(B) = 117 m//s` (b) `201 MJ//kg`