Hi everyone,

During orbit restitution, I estimate several drag coefficicients (using TimeSpanDragForce).

When I finally perform an orbit extrapolation, the last estimated drag coefficient will be considered (If I’m rigth, as I use the method addDragSensitiveValidAfter(), the last estimated Cd is valid for the extrapolation part)

My question is what is the best method to use a different drag coefficient for extrapolation, for example, the mean of all estimated drag coefficients.

To perform the final extrapolation, I use this piece of code:

Propagator[] od_propagators = estimator.estimate();

Propagator propagator = od_propagators[0];

…

propagator.propagate(ephem_start_date, ephem_stop_date);

I thought about updating the variable “propagator” by updating a Cd valid for extrapolation part, but I don’t think this is possible.

Another method would be to construct a whole new propagator using NumericalPropagatorBuilder, but this seems kind of tedious.

What would be the best approach ?

Many thanks,

Anthony