def setup_orbit():
b = Bunch(
equatorial_radius = 6378*km,
gravitational_parameter = 398600*km**3,
)
o = Orbit(body=b)
o.radius_at_epoch = 14600*km
o.speed_at_epoch = 8.6*km
o.flight_path_angle_at_epoch = 50*deg
return o
