1. The problem statement, all variables and given/known data a satellite is set to orbit a planet of mass 4X 10^20 kg . It is placed at a distance of seperation of 10^7m with a velocity of 30 degrees to the line connecting the center of the planet and the satellite. What will be its eccentrity fo orbit? (Answer is .89) 2. Relevant equations ME = KE + PE KE = 1/2 mv^2 PE = -GMm/r 3. The attempt at a solution I did 40m/s *sin (30) = vertical velocity. Then, I plugged it into the equation -GMm/r = .5m(40m/s *sin (30))^2 + -GMm/r I didn't get the answer though... please help!