def setup_orbit():
b = CelestialBody(
equatorial_radius = 6378*km,
gravitational_parameter = 398600*km**3)
o = Orbit(body=b)
o.epoch = 0
o.radius_at_epoch = 7200*km
o.radial_speed_at_epoch = 1*km
o.semi_major_axis = 10000*km
o.i = 0
o.Ω = 0
o.ω = 0
return o
