guidance, flight mechanics and trajectory optimization

Cd&t- d&J dt
I
where Xc9 #II 2 % 9 $i are the solutions to the homogeneous equations
which are found by applying the transition matrix for circular orbits to the
initial conditions
x (0)
p (0)
2(O)
pro,
with G(tlOJ given by Equation 1.58, When the approximation for a^
(Equation 4.41) is substituted into the previous solutions, the resulting
equations can be written in the form
where a, b, c, and tJ are constants and the R.. 1s are nonlinear functions of
% and tf. This set of equations must be so-ved v for a, b, c and tf; this
objective is accomplished by first estimating tf and 8, from the first two
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