NIObject = EulerIntegrator(S0)
else:
NIObject = RK4Integrator(S0)
NIObject.setStateDerivativeFunction(EOM)
# Quality check through iterations
for row in range(steps.size):
# Extracting the step size and solving using the desired integrator
step = steps[row]
qualityCheck[row,0] = step
Sol = NIObject.integrate(npMain.array([t0,te,step]))
# Extracting the final state and converting it into the equivalent cartesian coordinates
FinalS = Sol[-1,:]
FinalS_carte = convertCartesianToKepler(FinalS[1:7],mu)
# Quality-check
qualityCheck[row,2] = FinalS_carte[0]
qualityCheck[row,3] = (qualityCheck[row,2]-qualityCheck[row,1])*100/qualityCheck[row,1] # % error in semi-major axis
qualityCheck[row,5] = FinalS_carte[1]
qualityCheck[row,6] = (qualityCheck[row,5]-qualityCheck[row,4]) # absolute error in eccentricity
print('Quality-check complete at step size of ',step, ' s.')
######################################
######## Visualization ###############
######################################
if visualize == 0:
print('No visualizations are requested by the user.')
elif visualize == 1:
-4869.8462227
])
# Extracting mu from SPICE kernels
print(spice.tkvrsn('TOOLKIT'))
spice.furnsh("./External_files/Spice_kernels/kernel_load.txt")
muE = spice.bodvrd('EARTH', 'GM', 1)
#mu = 398600.441E9 # Gravitational parameter for Earth [m^3/s^2]
mu = muE[1][0] * 1e9
spice.kclear
CovertedKep = convertCartesianToKepler(
S_bar, mu, True, True) # Position arguments are passed
# Part(Problem) 2 of Basics-I assignment
a = 12158817.9615 # Semi-major axis[m]
e = 0.014074320051 # Eccentricity
i = 52.666016957 # Inclination [deg]
RAAN = 323.089150643 # Right ascention of ascending node [deg]
omega = 148.382589129 # Argument of pericenter [deg]
M = 112.192638384 # Mean anomaly[deg]
Kepler = np.array([a, e, i, RAAN, omega, M])
ConvertedCarte = convertKeplerToCartesian(Kepler,
mu,
1,
isInputInDegree=True,