1997 年 45 巻 525 号 p. 595-603
This paper first describes a modeling method for the uncertainty of aerodynamic coefficients in a linear state-space aircraft model. Second, a design method of robust flight control systems based on the model is also presented. The proposed method is applied to the structure of the uncertainty for the μ-analysis and has the following characteristics: 1) the variations of the altitude and the velocity are explicitly treated as real repeated scalar perturbations since all dimensional derivatives are the function of the altitude and the velocity, and as a result 2) a gain-scheduled controller using the dynamic pressure compensation which satisfies the robust performance for a comparatively wider flight envelope can be designed. Simulation study is carried out to indicate that the proposed method is less conservative and satisfies the robust performance for a wider flight envelope than those of the H∞ design and the μ-synthesis where all aerodynamic coefficients are assumed to be individually perturbed.