1. The problem statement, all variables and given/known data INTRO TO THE PROBLEM :For a circular orbit around a massive gravitating body, the speed depends on the radius according to the equation V = sqrt (GM/r) ; for elliptical orbits, the speed varies according to the equation v^2 = 2GM([ 1/r - 1/(2a), where r is the distance from the massive body and a is the semimajor axis of the ellipse (i.e., half the sum of the closest and farthest distances). A satellite can be transferred from one circular orbit (at radius r1) to a higher orbit (at radius r1) by boosting the circular speed v1 at v2 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. THE PROBLEM STATEMENT : How much energy is required for the first boost in such a transfer to take a 280kg satellite from a circular orbit at a 400 km altitude to the altitude of a geosynchronous orbit? change in K_1 = _________J 2. Relevant equations stated above in the intro 3. The attempt at a solution clueless?