A spacecraft has been injected into a 1 degree inclination orbit with an perigee radius of 33,300 km and a semi-major axis of 33,400. It has an eccentricity of 0.000012 and an perigee velocity of 3.4649 km/sec. What is its altitude at apogee? What is its angular momentum and specific mechanical energy? What is the orbital period in hours? Equations: a = {(ra + rp)/2} ra = a (1 + e) rp = a (1 - e) p = (b2/a) = a (1 - e2) e = v(1-[p/a]) = v(1-[2eh2/µ2] h = rpvp = rava e = - µ/(2a) P = 2pv(a3/µ) Use: Earth radius = 6378.1363 km Gravitational parameter µ = 3.986012 X 105 km2/sec2