1.Consider a satellite of the earth in a circular orbit ofradius R. Let M and m be the mass of the earth and that of thesatellite, respectively. Show that the centripetal acceleration ofthe satellite is aR =-(v^2/R)*(r/r) where v = |v| isthe magnitude of the velocity V andr/r is a unit vector in the radial direction.
2.Using Newton's second low of motion and the law of universalgravitation, determine the speed v=|V| and theangular speed w for the circular orbit.
3.For two satellites in two different circular orbits with radiiR1 and R2, respectively, prove kepler's second and third laws forthis special case.
