guidance, flight mechanics and trajectory optimization

For this case (t - to = T)
This solution, valid for circular reference orbits, is also applicable to
elliptic reference orbits by changing nt to 8 which is then true anomaly.
The solution to the out-of-plane problem for the case of elliptical target
orbits and eccentric anomaly is given by Tschauner (Reference 1.5). Let
Thus, the set becomes
where
The fundamental matrix is now
and
In this case, the substitution
and
z =F-'La&
gives the equation (q = r/a = 1 -e Cos E)
15
1.39
1.40
1.41
1.42
1.43