Approximate controller design for singularly perturbed aircraft systems

The purpose of this paper is to extend the Quasi-Steady State Approximation and Matrix Block Diagonalization methods utilized in the Approximate Controller Design for Singularly Perturbed Aircraft Systems [1]. In that paper, it was shown that an approximate controller solution could be developed by relocating only the slow poles for two-time scale aircraft dynamics. In addition, it showed the difference between the approximate solutions and the exact solutions were bounded within limits as O(ε) and O(ε²). This technique was successfully applied to the lateral dynamics of the DeHaviland Canada DHC-2 Beaver. In this paper, the same technique is applied to the NASA F-8 Aircraft dynamics in order to show that the method is not unique to the Beaver and can be applied to other aircraft models. It also extended the method to consider the singularly perturbed stochastic system and confirmed stability was maintained.