| Popis: |
In the present work, the influence of maneuver design for stability derivatives of aerodynamic forces and moments identification in the performance of closed loop control systems is evaluated, where two maneuvers largely used in aeronautical industry - doublet and 3211 - are compared to a maneuver of restricted use in aeronautical industry, but already well known in identification - the PRBS. This evaluation is divided in two steps: in the first, it is performed the identification with each of the maneuvers and then a crosschecking of the obtained models, computing the mean quadratic prediction error; in the second, the identified models are analytically linearized and use in a bank angle tracker. The calculated gains are then applied to the nonlinear model and the performance indices computed, as peak time and maximum overshoot, of step response with each gain set. The crosschecking showed the superior capacity of PRBS maneuver to capture the dynamics of the reference model, where the prediction error was relatively small for all models when compared to the response to doublet. With the 3211 data set, the error of the model identified with doublet was significantly larger than 3211 and PRBS models error, that had similar performance, however lightly better for the PRBS. With the PRBS data set, the PRBS error was relatively small, while the doublet and 3211 models error was relatively large. This result shows the direct relation of the maneuvers frequency spectra and the excitation persistence characteristic in the identified models.With an exigent performance requirement to the bank angle tracker, it was possible to expose the differences between the models and verify the influence of these differences in the closed loop response. In an equivalent form, as observed in the crosschecking analysis, the control system designed with the PRBS model showed performance indices closer to the target in comparison to the control system designed with the 3211 model, that was significatively better than the system designed with the doublet model. The closed loop amplified the difference between the models, and depending on the control system structure, these differences can be still larger. Finally, a practical application on aircraft identification and control is presented and discussed. |
