integrating orbital trajectories 2 - python-2.7

Question

The original second order ODEs are
x'' - 2 * omega * y' - omega ** 2 * x = - mue * (x + pi2 * r12) / np.sqrt((x + pi2 * r12) ** 2 + y ** 2) ** 3 - mum * (x - pi1 * r12) / np.sqrt((x - pi1 * r12) ** 2 + y ** 2)
y'' + 2 * omega * x' - omega **2 * y = - mue * y / np.sqrt((x + pi2 * r12) ** 2 + y ** 2) ** 3 - mum * y / np.sqrt((x - pi1 * r12) ** 2 + y ** 2)
z'' = 0
So here is the code I used to solve the ODE but first I broke it up into 2 first orders.
I am receiving the error that the module on line 61 is not callable.
Line 61 is u = odeint(deriv, u0, dt)
#!/usr/bin/env python
import numpy as np
import scipy.integrate as odeint
import matplotlib.pyplot as plt
from mpl_toolkits.mplot3d import Axes3D
me = 5.974 * 10 ** (24) # mass of the earth
mm = 7.348 * 10 ** (22) # mass of the moon
G = 6.67259 * 10 ** (-20) # gravitational parameter
re = 6378.0 # radius of the earth in km
rm = 1737.0 # radius of the moon in km
r12 = 384400.0 # distance between the CoM of the earth and moon
M = me + mm
pi1 = me / M
pi2 = mm / M
mue = 398600.0 # gravitational parameter of earth km^3/sec^2
mum = G * mm # grav param of the moon
mu = mue + mum
omega = np.sqrt(mu / r12 ** 3)
nu = 0.0 # flight path angle
x = 327156.0 # x location where the moon's SOI effects the spacecraft
y = 33050.0 # y location
vbo = 10.85 # velocity at burnout
gamma = -141.868 * np.pi / 180 # angle in radians of true anomaly
vx = vbo * (np.sin(gamma) * np.cos(nu) - np.cos(gamma) * np.sin(nu))
# velocity of the bo in the x direction
vy = vbo * (np.sin(gamma) * np.sin(nu) + np.cos(gamma) * np.cos(nu))
# velocity of the bo in the y direction
xrel = (re + 300.0) * np.cos(gamma)
# spacecraft x location relative to the earth
yrel = (re + 300.0) * np.sin(gamma)
# r0 = [xrel, yrel, 0]
# v0 = [vx, vy, 0]
u0 = [xrel, yrel, 0, vx, vy, 0]
def deriv(u, dt):
n1 = -((mue * (u[0] + pi2 * r12) / np.sqrt((u[0] + pi2 * r12) ** 2
+ u[1] ** 2) ** 3)
- (mum * (u[0] - pi1 * r12) / np.sqrt((u[0] - pi1 * r12) ** 2
+ u[1] ** 2) ** 3))
n2 = -((mue * u[1] / np.sqrt((u[0] + pi2 * r12) ** 2 + u[1] ** 2) ** 3)
- (mum * u[1] / np.sqrt((u[0] - pi1 * r12) ** 2 + u[1] ** 2) ** 3))
return [u[3], # dotu[0] = u[3]
u[4], # dotu[1] = u[4]
u[5], # dotu[2] = u[5]
2 * omega * u[5] + omega ** 2 * u[0] + n1, # dotu[3] = that
omega ** 2 * u[1] - 2 * omega * u[4] + n2, # dotu[4] = that
0] # dotu[5] = 0
dt = np.arange(0.0, 250000.0, .1)
u = odeint(deriv, u0, dt)
x, y, z, x2, y2, z2 = u.T
fig = plt.figure()
ax = fig.add_subplot(111, projection='3d')
ax.plot(x, y, z)
plt.show()

Answer 1

Assuming you mean this error:
~/coding$ python orbit1.py
Traceback (most recent call last):
File "orbit1.py", line 61, in <module>
u = odeint(deriv, u0, dt)
TypeError: 'module' object is not callable
This is because you want the function named odeint in scipy.integrate. Your line
import scipy.integrate as odeint
imports the entire module and gives it the name odeint. Try
from scipy.integrate import odeint
instead, or
import scipy.integrate
[...]
u = scipy.integrate.odeint(deriv, u0, dt)
which should give you