I'm making a spacecraft maneuver from one orbit to another. Firstly, I'm going to change the inclination, therefore, moving to a coplanar orbit.
- Where is it better to change the inclination, in terms of less Delta-V?
- If I know the current keplerian elements for my spacecraft, how to calculate the time, when the spacecraft will be on the above point, to make an optimal maneuver?
Found, that the optimal points are the orbital nodes. Are the orbital nodes at 90 and 270 degrees of true anomaly?