Paul Hewitt's "Figuring Physics" in the Feb. 2016 issue asked whether it would take a larger velocity change to stop a satellite in a circular orbit or to cause it to escape. An extension of this problem asks: What "minimum" velocity change is required to crash a satellite into the planet, and how does that compare with the velocity change required for escape? The solution presented here, using conservation principles taught in a mechanics course, serves as an introduction to orbital maneuvers, and can be applied to questions regarding the removal of objects orbiting Earth, other planets, and the Sun. In this article I examine the possible effects of a single coplanar impulse on a satellite in a circular orbit around an isolated spherical planet of mass M. I treat these impulses as "instantaneous" (of duration much less than the orbital period), which is a good approximation for most spacecraft.