**Hi everyone,**

**I was propagating with the following code:**

orbit = KeplerianOrbit(

altitude,

ecc,

inc,

float(np.radians(180)),

float(np.radians(261)),

float(np.radians(0)),

PositionAngle.MEAN,

frame,

initial_date,

Constants.EIGEN5C_EARTH_MU,

)

initialState = SpacecraftState(orbit, float(sat_mass))

orbitType = OrbitType.EQUINOCTIAL

tol = NumericalPropagator.tolerances(1.0, orbit, orbitType)

integrator = DormandPrince853Integrator(

float(0.0000000000001),

float(1000),

orekit.JArray(“double”).cast_(tol[0]),

orekit.JArray(“double”).cast_(tol[1]),

)

integrator.setInitialStepSize(float(60))

propagator = NumericalPropagator(integrator)

propagator.setOrbitType(orbitType)

propagator.setInitialState(initialState)

propagator.setAttitudeProvider(LofOffset(frame, LOFType.VNC))

**I was then trying to retrieve the keplerian parameters using:**

```
currentState = propagator.propagate(time)
orbit = OrbitType.KEPLERIAN.convertType(currentState.getOrbit())
print(orbit.getA())
print(orbit.getPerigeeArgument())
```

**Now getA() is working but getPerigeeArgument() is not. The error is**

```
AttributeError: 'Orbit' object has no attribute 'getPerigeeArgument'
```

**Any thoughts on this would be greatly appreciated!**