1. The problem statement, all variables and given/known data A satellite is in circular orbit at an altitude of 1000 km above the surface of a nonrotating planet with n orbital speed of 5.3 km/s. The escape velocity for the planet is 11.3 km/s. In this situation the orbital period of the satellite, in minutes, is....? 2. Relevant equations v(orbital)=√(GM/R+r) v(escape)=√(2GM/R) T=2∏R/v 3. The attempt at a solution Of course I converted everything to SI units first. So v(orbital)=5300m/s and v(escape)=11300m/s and r=10^6m. What I did is solved the two equations for velocity for M and then plugged in what I had. I found that R is 282,028m which seems small, but then using that I find that and the second equation I find the time period in minutes to be 25. According to my answer key the answer should be 35. I don't know if I am wrong or the answer key is wrong. What I don't know how to do is allow for any effect that the fact that the planet is non-rotating may have. Help...am I making a silly mistake? It is after midnight and I have been at this a while.