guidance, flight mechanics and trajectory optimization
guidance, flight mechanics and trajectory optimization
guidance, flight mechanics and trajectory optimization
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I-<br />
Collecting the results of this section, the solution to the problem of<br />
minimizing lkhe performance index<br />
i,<br />
subject to the boundary conditions<br />
<strong>and</strong> the state equations<br />
(X,LfM f 9$, $1 = mi.ni.mum<br />
x = x0 AT t=t,<br />
Y-c+, tJ=o AT t =i+.<br />
g. = I$ (22, u) C’= /, . . ..n<br />
can be generated by solving the partial differential equation<br />
for Fl(t,x(t)) subject to the boundary conditions of Eq. (2.4.116) or Eqs.<br />
(2.4.117) <strong>and</strong> (2.4.119) where Eq. (2.4.119) is to hold only if the final<br />
time tf is not explicitly specified.<br />
91<br />
(2.4.120)