Abstract:

The linear models of an aero engine at different equilibrium points were uniformly transferred into a linear model with norm bounded structured parameter uncertainty with singular value decomposition techniques, then a PI type robust H ∞ series controller was designed by applying robust H ∞ control theory and using PI type H ∞ controller design method, and the two variable regulating scheme was realized in which both the lower pressure compressor speed and the after turbine temperature were kept constant. Simulations on nonlinear aero thermodynamic simulator were also implemented and the results showed that both the robust stability and the robust performance were achieved.

Key words: aero engine control, robustness, H &infin, control, proportional and integral controller