Consider an inertial reference frame with the center of the earth as its origin and with the x-y (i-j) plane in the euqatorial plane. Directly above the equator, a satellite is at position r = 6807j km, and has an instataneous v = 5.4i + 0.5j - 5.4k km/s.
a) What is the orbit looks like?
b) Calculate POSITION of apaopsis and periapsis and draw them.
c) Calculate the eccentricity vector and draw it.
d) Calculate and draw the specific angular momentum vector.
e) Calculate the angle between periapsis and the equatorial plane.
f) Calculate the angle between i and the point where the satellite intersects the orbital plane with negative velocity in the k-direction.