Hi all,

I am using a DSST propagator where I set the max step to every few orbits, which results in sparse orbital data outputs. Unfortunately, only having satellite positional data once every few orbits leads to some interesting orbits in Cesium. In order to visualize this orbit in Cesium accurately so that the Cesium interpolation doesn’t lead to unusual visuals, I decided to try to implement the spacecraft state interpolator to generate more points in between the data from propagation. However, I am having trouble implementing the class. I get the following error,

state_interpolated = state_interpolator.interpolate(new_dates[idx], state_pairs)

^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^

orekit.InvalidArgsError: (<class ‘org.orekit.propagation.SpacecraftStateInterpolator’>, ‘interpolate’, (<AbsoluteDate: 2031-01-01T00:00:00.000002Z>, [<SpacecraftState: SpacecraftState{orbit=Keplerian parameters: {a: 7083137.0; e: 0.0; i: 98.19999999999999; pa: 0.0; raan: 0.0; v: 0.0;}, attitude=org.orekit.attitudes.Attitude@30c0d731, mass=6.0, additional={}, additionalDot={}}>, <SpacecraftState: SpacecraftState{orbit=equinoctial parameters: {a: 7073969.732352099; ex: -4.662468848297403E-4; ey: -3.0329160680545307E-7; hx: 1.1545078325623306; hy: -1.3486024884883569E-6; lv: 0.0026791290180058413;}, attitude=org.orekit.attitudes.Attitude@61c7222b, mass=6.0, additional={}, additionalDot={}}>])).

Any help or alternative suggestions for obtaining smooth orbital visualizations would be greatly appreciated.