guidance, flight mechanics and trajectory optimization
guidance, flight mechanics and trajectory optimization
guidance, flight mechanics and trajectory optimization
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Thus, the solution is written<br />
The transition matrix then becomes<br />
F(,L)F-‘(El = k Lz% 3<br />
where a <strong>and</strong> b are defined by the equations below:<br />
a = wo (L -6) -e(cooE+mEo) +e2(/-dirCE&Eo)<br />
2.1.4.2 The In-Plane Motion<br />
2.1.4.2.1 In-Plane Motion for Circular Target Orbit<br />
For the case of the in-plane motion <strong>and</strong> the circular reference orbit, the<br />
first two equations of Equations 1.21 are used. To express these as a set of<br />
linear equations, let<br />
The set becomes<br />
16<br />
1.44<br />
1.45<br />
1.46<br />
1.47a<br />
1.47b<br />
1.48<br />
1.49