1. The problem statement, all variables and given/known data A spacecraft of mass 2500kg is in a circular orbit a distance 2560km above the surface of Mars. How much work must the spacecraft engines perform to move the spacecraft to a circular orbit that is 4660km above the surface? Take the gravitational constant to be = 6.67×10^?11 N*M^2/kg^2, the mass of Mars to be = 6.42×10^23 kg, and the radius of Mars to be = 3.40×10^6 m. 2. Relevant equations U=-GMm/r 3. The attempt at a solution r1 = 3.4x10^6m + 2560km = 5960000m r2 = 3.4x10^6m + 4660km = 8060000m U1=-GMm/r1=6.67x10^-11 * 6.42x10^23 * 2500 / 5960000 = -1.796x10^10 U2=-GMm/r2=6.67x10^-11 * 6.42x10^23 * 2500 / 8060000 = -1.328x10^10 U2-U1=4.68x10^9 But that isn't the right answer. Can anyone help point out what I'm doing wrong? Thank you.