[Orekit Users] Numerical Propagator using the Python Orekit wrapper

Hi everyone,

I am trying to use the Python Orekit wrapper to numerically integrate orbits and I'm running into a few problems.

I am following the tutorial here:

https://www.orekit.org/static/tutorial/propagation.html

I've gotten the Slave mode and the Ephemeris mode part of the tutorial to work. But I get an error when I try to set up the integrator, i.e., in the following part of the tutorial:

// Adaptive step integrator
// with a minimum step of 0.001 and a maximum step of 1000
double minStep = 0.001;
double maxstep = 1000.0;
double positionTolerance = 10.0;
OrbitType propagationType = OrbitType.KEPLERIAN;
double[][] tolerances =
NumericalPropagator.tolerances(positionTolerance, initialOrbit, propagationType);
AdaptiveStepsizeIntegrator integrator =
new DormandPrince853Integrator(minStep, maxstep, tolerances[0], tolerances[1]);

The error I get is:

InvalidArgsError: (<type 'DormandPrince853Integrator'>, '__init__', (0.001, 1000.0, <Object: [D@e50a6f6>, <Object: [D@14ec4505>))

It looks like it is something to do with the handling of tolerances. I have attached my IPython notebook in case anyone can help me. The code I have for running the example is:

# Import all the required libraries
#Initialize orekit and JVM
import orekit
orekit.initVM()
from orekit.pyhelpers import setup_orekit_curdir
setup_orekit_curdir()
#Apache math
from org.orekit.bodies import CelestialBodyFactory, CelestialBody
from org.orekit.errors import OrekitException
from org.orekit.frames import LOFType, Frame, FramesFactory, Transform
from org.orekit.orbits import KeplerianOrbit, Orbit, CartesianOrbit, OrbitType, PositionAngle
from org.orekit.propagation import Propagator, SpacecraftState
from org.orekit.propagation.analytical import tle, KeplerianPropagator
from org.orekit.propagation.numerical import NumericalPropagator, Jacobianizer, TimeDerivativesEquations
from org.orekit.time import TimeScalesFactory, AbsoluteDate, DateComponents, TimeComponents
from org.orekit.utils import IERSConventions, Constants, PVCoordinates, PVCoordinatesProvider
from org.orekit.python import PythonEventHandler, PythonOrekitFixedStepHandler
from org.orekit.utils import IERSConventions
from org.hipparchus.geometry.euclidean.threed import Vector3D
from org.hipparchus.geometry.euclidean.threed import RotationOrder
from org.hipparchus.ode.nonstiff import DormandPrince853Integrator, ClassicalRungeKuttaIntegrator

# Inertial frame
inertialFrame = FramesFactory.getEME2000();
# Initial date
utc = TimeScalesFactory.getUTC();
initialDate = AbsoluteDate(2004, 01, 01, 23, 30, 00.000,utc);
# Central attraction coefficient
mu = 3.986004415e+14;
# Initial orbit
a = 24396159.0; # semi major axis in meters
e = 0.72831215; # eccentricity
i = 0.122173; # inclination
omega = 3.14159; # perigee argument
raan = 4.55531; # right ascention of ascending node
lM = 0.0; # mean anomaly
initialOrbit = KeplerianOrbit(a, e, i, omega, raan, lM, PositionAngle.MEAN, inertialFrame, initialDate, mu)
# Initial state definition
initialState = SpacecraftState(initialOrbit);
# Adaptive step integrator
# with a minimum step of 0.001 and a maximum step of 1000
minStep = 0.001;
maxstep = 1000.0;
positionTolerance = 10.0;
propagationType = OrbitType.KEPLERIAN;
tolerances = NumericalPropagator.tolerances(positionTolerance, initialOrbit, propagationType);

integrator = DormandPrince853Integrator(minStep,
maxstep,
tolerances[0],
tolerances[1]) # Error here

propagator = NumericalPropagator(integrator)
propagator.setOrbitType(propagationType)

I wonder if I am missing any imports. I would greatly appreciate any help!

Best Regards,

Vivek