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