1. The problem statement, all variables and given/known data Two satellites are launched at a distance R from a planet of negligible radius. Both satellites are launched in the tangential direction. The first satellite launches correctly at a speed v0 and enters a circular orbit. The second satellite, however, is launched at a speed .5v0. what is the minimum distance between the second satellite and the planet over the course of its orbit? R=launch radius, r=minimum radius, v=velocity at minimum radius 2. Relevant equations F=GMm/R^2 U= -GMm/R K=.5mv^2 mvr= const. (conservation of angular momentum) K+U=const. (conservation of energy) 3. The attempt at a solution GM= R(v0)^2 v0R/2 = vr, v = (v0R)/(2r) .5m(.5v0)^2 - GM (m/R) = .5m(v^2) - GM (m/r) Substituting in values and solving for r doesn't lead me to the answer. Any help?