tag:blogger.com,1999:blog-8134468339313902988.post5534323745143007227..comments2023-10-29T08:48:05.831-04:00Comments on Bulldogs Blog: For those who are wondering ...Seth Emersonhttp://www.blogger.com/profile/06528604970395659237noreply@blogger.comBlogger2125tag:blogger.com,1999:blog-8134468339313902988.post-14070168959289595942011-04-06T11:55:19.125-04:002011-04-06T11:55:19.125-04:00This comment has been removed by the author.Anonymousnoreply@blogger.comtag:blogger.com,1999:blog-8134468339313902988.post-59776471737557221442011-04-06T11:53:56.749-04:002011-04-06T11:53:56.749-04:00Let m be the mass of the satellite, even though we...Let m be the mass of the satellite, even though we don't need it. Let a be the semi-major axis. Let e be the eccentricity.<br /><br />For a circular orbit: v_0^2 = GM/r_0 (*1)<br /><br />For our setup: v_0^2 = (v_0 sin γ)^2 + (v_0 cos γ)^2<br /><br />For the extreme points in the orbit, there is no inward or outward motion.<br />So by the conservation of angular momentum, we must have<br /><Anonymousnoreply@blogger.com