1. The problem statement, all variables and given/known data Show that a satellite in low-Earth orbit is approximately P = C(1 + 3h/2R_E) where h is the height of the satellite, C is a constant, and R_E is the radius of the earth) 2. Relevant equations p=C(1+3H/2R_E) p2 = (4∏2)/(GM) * a3. (G - gravitational constant, M - mass of the earth (in this case) and a = semi-major axis) 3. The attempt at a solution I've been googling this and I seen one person say use Taylor series. We have not touched that so Im pretty sure it isnt how I should be finding this so the a is equal to the radui of earth, and its high a=h+R_E and i can write that as a=R_E(1+h/R_E) SO p2 = (4∏2)/(GM) * R_E(1+h/R_E)3. I just saw in my noes thats if (4∏2)/(GM) can be cancled out if all meaurments are in Au's, years and solars mass. Then Id get p2 = R_E(1+h/R_E)3 and p= R_E(1+h/R_E)3/2 Now what?