where Ct is a constant. Substituting Eq. 23 into the limiting form of Eq. 17 yields the relation A formula for attitude pointing error 0U in terms of 6 as t—Can thus be established as follows, Note that both stable and unstable equilibria are solutions to these equations with 0 = 0, ±77 as stable states and 0 = ±tt/2 as unstable. Theorem 1 states that as the satellite will have once-per-orbit revolutions and will always be along the local vertical corresponding to 0 = 0, ±tt, since, in reality, unstable states 0 = ±tt/2 can never be reached in such an environment. PARAMETRIC ANALYSIS A parametric analysis is performed to determine the relationship between the inertia ratio / = (4 - Ix)/ly and the attitude pointing error 0y. By recalling the definitions of the moment of inertia, it can be shown that
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