Hello dear Orekit community,
While studying the effects of PV variations in the initial state-vector on long-term dynamics of HEO satellites, I have encountered an error message for one particular semi-major axis value:
My initial cartesian state vector in the GCRF frame is the following:
x=-9553881.856064696 [m]
y=-10503594.41438614 [m]
z=-8565090.084354697 [m]
vx=-1824.5510030089001 [m/s]
vy=3055.9242374579967 [m/s]
vz=5489.458401391574 [m/s]
with a satellite mass of 1186kg, an initial date datetime(2010, 1, 1, 12, 0, 0) and a propagation target date datetime(2023, 5, 3, 0, 0, 0).
I use a 50x50 Earth gravitational model and only take into account lunisolar third-body perturbations.
I also use a Dormand-Prince integration method to the fifth order, with a position tolerance of 1e-5 m, a minimum step of 0.01s and a maximum step of 172800s.
I have tried to propagate the exact same satellite using a numerical propagator and it worked just fine, so the issue seems to be with the DSST propagator only. Moreover, when adding or subtracting 100km to the semi-major axis, the orbit propagation works just fine… so this is maybe due to lunar resonant behaviour?
Anyway, I have been trying to find a similar case to this issue on the forum, and HansenObjects related errors seem to be quite tricky. Could you have an explanation for this one?
Cheers
Goulven
