By Gilles Ferreres
1. MOTIVATION in lots of actual occasions, a plant version is usually supplied with a qualitative or quantitative degree of linked version uncertainties. at the one hand, the validity of the version is assured purely inside of a frequency band, in order that approximately not anything might be stated concerning the habit of the genuine plant at excessive frequencies. nonetheless, if the version is derived at the foundation of actual equations, it may be parameterized as a functionality of some actual parameters, that are often now not completely recognized in perform. this is often e.g. the case in aeronautical platforms: for example, the ae- dynamic version of an aircraft is derived from the flight mechanics eq- tions. whilst synthesizing the plane keep watch over legislation, it really is then essential to bear in mind uncertainties within the values of the steadiness derivatives, which correspond to the actual coefficients of the aerodynamic version. additionally, this aircraft version doesn't completely characterize the be- vior of the true plane. As an easy instance, the flight regulate method or the autopilot are typically synthesized simply utilizing the aerodynamic version, therefore with no accounting for the versatile mechanicalstructure: the c- responding dynamics are certainly regarded as excessive frequency ignored 1 dynamics, with appreciate to the dynamics of the inflexible version .
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Extra resources for A Practical Approach to Robustness Analysis with Aeronautical Applications
A simple static control law is synthesized for this rigid model in the second subsection. The third subsection presents the flexible model, which is to be added to the aerodynamic model in order to obtain a complete aircraft model. The fourth subsection presents the design of the new flight control system. Glossary sideslip angle. roll angle. yaw rotational rate. roll rotational rate. acceleration output. aileron deflection. 29 A PRACTICAL APPROACH TO ROBUSTNESS ANALYSIS 30 rudder deflection. angle of attack.
2. e. 12), one obtains by identifying each term: The issue is finally to come back to an input/output framework. 6) corresponds to the augmented transfer matrix: As expected, when using the feedback one obtains: Realization of uncertain systems under an LFT form 3. 1 47 THE GENERAL CASE INTERCONNECTION OF LFTS • It is first illustrated that the interconnection of various elementary LFTs is also an LFT. 2, which represents the way a complete LFT model of the transport aircraft will be obtained in the next chapter.
1 % for the damping ratio of the bending modes for the telescope, about 1 % for the aircraft). 1. A TRANSPORT AIRCRAFT Two different control problems are considered. The first classical one consists in designing a flight control system for a rigid airplane. In the second one, which is far less standard, a flexible airplane is considered. The aerodynamic model is presented in the first subsection. A simple static control law is synthesized for this rigid model in the second subsection. The third subsection presents the flexible model, which is to be added to the aerodynamic model in order to obtain a complete aircraft model.