We have elliptical orbit and spacecraft travelling it. I need a formula to calculate a time needed for spacecraft to travel given amount of meters starting from it's current position.
Keplerian elements of orbit are known.
If I know difference between current and future true anomaly, I can use formula of orbital period to calculate that time but how to find the future anomaly by given orbital ellipse chord length (closest point) and initial true anomaly?
And also I need the same calculations for hyperbolic trajectory