guidance, flight mechanics and trajectory optimization

while the active (or chasing) satellite is taken to be at
r = rl(l + el) g + r1 5, x 1.3
where U lies in the orbit plane at the angle e2 ahead of U1, and where
!z r
51 9 53 are small angles while 52 is unlimited (Figure l.lT. Thus for
circular target orbits, the chase vehicle is allowed to be anywhere inside a
torus of small lateral dimensions centered on the orbit of the target. For
elliptical
so different
target
for
orbits
large
of high eccentricity, the values
t2 that tl could become large.
rl and r
Or to put it?EobtEer
way, if a torus of reasonably small cross section centered at the radius of
the semi-major axis of the target orbit does not include the whole elliptical
orbit in its interior, then 62 will have to be limited to moderately small
angles in order to keep [I small.
Figure 1.1 The Target Orbit Plane Vectors and Angles
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