Design and Performance Analysis of a multi-requirement output feedback Control Strategy through the Tensor Product model transformation based Framework on a 3DoF Aerospace Wing Model

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Supervisor:
Dr. Baranyi Péter Zoltán
Department of Telecommunications and Media Informatics

One of the main challenging areas of modern control theory in various engineering fields is the optimized design based on multiple requirements of highly complex, nonlinear systems with possible parametric attributes and in some cases various types of delays. These various engineering disciplines include information technology, electrical, mechanical, chemical, biological, etc. fields, spanning across different industries like automotive, aerospace, military, etc.

A new and efficient approach in the field of control theory is represented by the Tensor Product (TP) model transformation. A wide range of different models, which can be identified and modeled through various identification and modeling techniques based on different representations, e.g. quasi-Linear Parameter Varying (qLPV) models, can be rendered through the TP model transformation into TP model type polytopic models, upon which highly efficient modern Linear Matrix Inequality (LMI) based design and optimization techniques well-known to control theory can be easily applied.

In addition the issue of active control of aeroelasticity has been in the focus of aerospace and control engineering for several decades. The aeroelastic aerospace wing section model and its aspects have traditionally been used for theoretical as well as experimental analysis of aeroelastic behavior. The challenges in the control design of the aerospace wing section model is the strong nonlinearity and various parametric attributes, which without control effort can lead to limit cycle oscillation and chaotic behavior of the model.

The goal of the Master of Science Thesis is to examine the usefulness of the TP model transformation by applying it to this complex, highly non-linear control theory case of a three degrees-of-freedom (3DoF) Nonlinear Aeroelastic Test Apparatus (NATA) model. Further details can be found in the task announcement.

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