Introduction To Space Dynamics Solutions Updated Today

The most common numerical integration methods for space dynamics are:

def orbit_dynamics(t, y, mu, J2, R_e): r = y[0:3] v = y[3:6] a_grav = -mu * r / np.linalg.norm(r)**3 # J2 perturbation z2 = r[2]**2 r2 = np.linalg.norm(r) 2 factor = (3/2) * J2 * mu * R_e 2 / np.linalg.norm(r)**5 a_J2 = factor * np.array([r[0] (5 z2/r2 - 1), r[1] (5 z2/r2 - 1), r[2] (5 z2/r2 - 3)]) return np.concatenate([v, a_grav + a_J2]) Introduction To Space Dynamics Solutions