What is the minimum energy expenditure required for the


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?

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Mechanical Engineering: What is the minimum energy expenditure required for the
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