The aim of this chapter is to evaluate the applicability of the com­putational methods, which were presented in the previous chapter. See (Ferreres et al., 1996a) for a related work in the context of a single-axis and three-axes missile autopilot. See also chapter 5 (section 4.) for a summary of the computational methods.

The first section evaluates the robust stability and performance prop­erties of the longitudinal missile autopilot, robust performance being defined either as robust pole location inside a truncated sector, or as ro­bust shaping of the sensitivity function. The lateral flight control system is analyzed in the same way in the second section. Since this controller was synthesized with a modal approach, robust performance is defined in this context as robust pole location inside a truncated sector.


The aim of this section is to analyze the local stability and performance properties of the #oo autopilot in the presence of parametric uncertain­ties in the 4 stability derivatives Ma , Ms, Za, Z$. The high frequency bending mode is not taken into account (see chapter 9), so that the model perturbation only contains 4 non repeated real scalars. The weights in the stability derivatives are chosen as 5 %. See chapters 2 (subsection 2.2) and 4 (section 1.) for details concerning the description of the linearized missile model and the building of the interconnection structure.

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