- Dec 2, 2009
- Reaction score
In the pic above we have two spacecrafts in orbits A and B. The orbits are circular and coplanar.
We are given the radii of orbits A and B and the TOF=t1-t0 that it takes to get from A to B via a hyperbolic transfer trajectory.
Are these enough to calculate the semi major axis or the eccentricity of the transfer hyperbola? If yes, how?
I have been reading the equations for hyperbolic orbits but I seem to be going in circles, ending up with equations with two unknowns and not being able to "isolate" one of them. Once I have either of these two unknowns, I can calculate the other one very easily.