def test_DeltaOmega(t_max=160): time, r0, v0 = integrate_orbits(t_max=t_max, coupled=False) time, r, v = integrate_orbits(t_max=160, coupled=True) DeltaOmegaU = omega(v0[:, 0], r0[:, 0]) - omega(v[:, 0], r[:, 0]) result = [DeltaOmegaU.min(), DeltaOmegaU.max()] assert_array_almost_equal(result, [-1.0492366485e-05, 7.84639028908e-05], err_msg="DeltaOmega incorrect")
def test_uranus_initial_conditions(t_max=10, dt=0.01): time, r, v = integrate_orbits(t_max=t_max, dt=dt) assert_equal(len(r), int(t_max/dt)) assert_array_almost_equal(r[0, 0], np.array([-17.30163539, -8.30441128]), err_msg="Uranus initial position wrong") assert_array_almost_equal(v[0, 0], np.array([-0.62108718, 1.29398985]), err_msg="Uranus initinal velocity wrong")
def test_neptune_initial_conditions(t_max=10, dt=0.01): time, r, v = integrate_orbits(t_max=t_max, dt=dt) assert_equal(len(r), int(t_max/dt)) assert_array_almost_equal(r[0, 1], np.array([ 9.47879984, -28.52756714]), err_msg="Neptune initial position wrong") assert_array_almost_equal(v[0, 1], np.array([-1.08771092, -0.36141161]), err_msg="Neptune initinal velocity wrong")