1. The problem statement, all variables and given/known data The spacecraft P is in the elliptical orbit shown. At the instant represented, its speed is v = 13164 ft/sec. Determine the corresponding values of and . Use g = 32.23 ft/sec2 as the acceleration of gravity on the surface of the earth and R = 3959 mi as the radius of the earth. I have uploaded an image of the solution. 2. Relevant equations 3. The attempt at a solution r = 16388 miles I've found r' = 9050.85 ft/s and θ' = 0.00011047 rad/s But I cannot for the life of mt figure out why I can get θ'' or r''. For r'' ƩFr = mar = m(r'' - rθ'2) = -GmmE/r2 r'' = -GmE/r2 + rθ'2 = -3.439x10-8ft4/lbfs4+ 4.095x1023 lbf=s2/lbf)/ 16388miles*5280) + (16388miles*5280)*0.00010472 r'' = -.93236 ft/s2 It says this is wrong and I've at a loss for where my mistake is. Likewise for θ'' maθ = m(rθ''+2r'θ') = 0 Mass cannot equal zero, therefore the summation in the brackets must be equal to zero θ'' = -2r'θ/r = _2*9050ft/s*(133.63°(π/180)) θ'' = -.0004879 This is also incorrect. Any help would be appreciated. Thanks.