Abstract
A study was conducted to demonstrate aeroelastic wing section control via relaxed tensor product model transformation framework. The investigations focused on the three-degree-of-freedom (3-DOF) nonlinear aeroelastic test apparatus (NATA) model. The study also revisited the parallel distributed compensation (PDC) framework-based control solution of the 3-DOF NATA model in the case where the model was extended to incorporate friction. It presented a new general theoretical control design framework based on tensor product (TP) model transformation. The proposed framework was capable of a significant complexity reduction of quasi-linear parameter-varying (QLPV) models, including numerical and theoretical for linear matrix inequality (LMI)-based control design. The proposed control design framework was applied for active stabilization of the 3-DOF aeroelastic wing section as an extension of the design method.
| Original language | English (US) |
|---|---|
| Pages (from-to) | 1671-1677 |
| Number of pages | 7 |
| Journal | Journal of Guidance, Control, and Dynamics |
| Volume | 37 |
| Issue number | 5 |
| DOIs | |
| State | Published - Sep 1 2014 |
| Externally published | Yes |
Bibliographical note
Funding Information:The research was supported by the Hungarian National Development Agency (ERC-HU-09-1-2009-0004, MTASZTAK; OMFB-01677/2009). The research was part of the Zoltán Magyary Postdoctoral Scholarship. Béla Takarics’s research was supported by the European Union and the State of Hungary, and it was cofinanced by the European Social Fund in the framework of the Társadalmi Megújulás Operatív Program (TÁMOP) 4.2.4. A/1-11-1-2012-0001 National Excellence Program.