guidance, flight mechanics and trajectory optimization

of the control vector u. Also, the final time, tf, is explicitly specified.
Note that the simple attitude controller which was considered in Section (2.4.8)
is a special case of the above problem.
Substituting the state expressions of (2.4.121B) into (2.4.120) provides
MIA/ @ I
atj =o (214.124)
uct)o u
Since the admissible setu is the entire control space, the minimization
operation in (2.4.124) is accomplished simply by differentiating with respect
to u . Thus (2.4.124) is equivalent to the two equations
Using Eq. (2.4.l22B), the boundary condition on R as given in Eq. (2.4.117)
reduces to
where/ is the m-dimensional constant vector
Try as a solution, the function
IQ= Y T S(r) p!trcdr
93
ON b-d =o
t = f/.
(2.4.125)
(2.4.126)
(2.4.127)
(2.4.128)
(2.4.129)