Spacecraft a is in an elliptical earth orbit having the following orbital elements: e = 0.1, ω = 40°, i = 60°, ω = 30° and θ = 50° , h = 65,000 km2 /s and spacecraft b is in a nearly circular earth orbit with the following orbital elements: e = 0.02, ω = 20°, i = 20°, ω = 110° and θ = 40° , h = 61,000 km2 /s a) determine the relative position, velocity and acceleration of spacecraft b relative to a, measured in local vertical/local horizontal commoving coordinate system of spacecraft a. b) plot the two orbits and show the location of each satellite in the geocentric equatorial frame