def setup_orbit():
b = Bunch(
equatorial_radius = 6378*km,
gravitational_parameter = 398600*km**3,
)
z1 = 1545*km
θ1 = 126*deg
z2 = 852*km
θ2 = 58*deg
return Orbit.from_altitude_at_true_anomaly(z1,θ1,z2,θ2,b)
