1. The problem statement, all variables and given/known data A satellite is in elliptical orbit with a period of 8.00 x 10^4 s about a planet of mass 7.00 x 10^24 kg. At aphelion, at radius 4.5 x 10^7 m, the satellite's angular speed is 7.158 x 10^-5 rad/s. What is its angular speed at perihelion? 2. Relevant equations V(orbital) = sqrt(GM/R) T=2∏sqrt(R^3/GM) V=ωr 3. The attempt at a solution I used Kepler's 3rd law to find the semimajor axis of the satellite: T=2∏sqrt(R^3/GM) 8.00 x 10^4 s = 2∏sqrt(R^3/(6.67 x 10^.11)(7 x 10^24 kg)) and found that the semimajor axis (R) is 4.23 x 10^7 m I then reasoned that twice the semimajor axis minus the aphelion distance = the perihelion distance, so 2(4.23 x 10^7 m) - 4.5 x 10^7 m = perihelion distance Perihelion distance (r) = 3.96 x 10^7 m I then used the value of the radius at perihelion (r) in the V(orbital) = sqrt(GM/r) expression and found: V(orbital) = sqrt[((6.67 x 10^-11)(7 x 10^24 kg))/(3.96 x 10^7 m)] V(orbital) = 3433.65 m/s I then plugged this into V=ωr: 3433.65 m/s = ω x 3.96 x 10^7 m ω = 8.67 x 10^-5 rad/s However, the answer should be 9.29 x 10^-5 rad/s. My answer key shows that the conservation of angular momentum was used to find the answer. However, I don't see why my approach doesn't also work. It seems to yield a similar answer, but just far off enough to make me think that the approach is flawed. Any help would be greatly appreciated!