Hohmann transfer orbit
A space vehicle is in circular orbit about the Earth. The mass of the vehicle is 3000 kg and the radius of the orbit is 2Re = 12 800 km. It is desired to transfer the vehicle to a circular orbit of radius 4Re. 4Re 2Re A B
(a) What is the minimum energy expenditure required for the transfer?
(b) An efficient way to accomplish the transfer is to use a semi-elliptical orbit (known as a Hoh mann transfer orbit), as shown. What velocity changes are required at the points of intersection, A and B?
