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jcook735
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Homework Statement
For a circular orbit around a massive gravitating body, the speed depends on the radius according to Equation 8.3; for elliptical orbits, the speed varies according to the equation v2= 2GM[(1/r)-(1/2a)], where r is the distance from the massive body and a is the semimajor axis of the ellipse. A satellite can be transferred from one circular orbit at radius r1 to a higher orbit at radius r2 by boosting the circular speed v1 at r1 to the appropriate speed for an elliptical orbit whose distance varies between r1 and r2, and then boosting the speed in the elliptical orbit at r2 to the circular speed v2. this is called a Hohmann transfer. (a) How much energy is required for the first boost in such a transfer to take a 250-kg satellite from a circular orbit at a 400-km altitude to the altitude of a geosynchronous orbit? (b) how much energy is required for the second boost?
Homework Equations
Conservation of energy and the v2 equation given in the problem
The Attempt at a Solution
Well, I used conservation of energy E1 + E = E2 and found the E required to move the satellite between the two orbits. However, this question is asking for the energy required for each boost, and I have no idea how to separate these. Any help would be greatly appreciated!