Improved aircraft roll maneuver performance using smart deformable wings

Rama K. Yedavalli; Narendra S. Khot; Seung-Keon Kwak

doi:10.1117/12.316354

24 July 1998 Improved aircraft roll maneuver performance using smart deformable wings

Rama K. Yedavalli, Narendra S. Khot, Seung-Keon Kwak

Proceedings Volume 3323, Smart Structures and Materials 1998: Mathematics and Control in Smart Structures; (1998) https://doi.org/10.1117/12.316354
Event: 5th Annual International Symposium on Smart Structures and Materials, 1998, San Diego, CA, United States

Abstract

In this paper, the aspects of modeling and control design methodology for improving roll maneuver performance in aircrafts (for achieving a desired roll rate) by deforming a flexible wing with piezoelectric actuation and sensing are studied. An integrated finite element model of a laminated composite plate embedded with smart piezo actuators and sensors subject to aerodynamic loading giving rise to a steady roll rate is developed. The resulting model in the generalized coordinates which has nonsymmetric aerodynamic damping matrix and a nonsymmetric stiffness matrix (due to aerodynamic stiffness) is then transformed to real but nonorthogonal modal coordinates and a reduced order model is developed. A new control design algorithm based on `Reciprocal State Space' framework is then developed to achieve the desired roll rate and to simultaneously suppress the flexible mode vibrations. The research carried out clearly delineates the relationship and interaction between the structural, aerodynamic and piezo actuation based control subsystems and underscores the importance, potential and the vast scope of the proposed integrated approach to improve aircraft maneuver performance.

Citation Download Citation

Rama K. Yedavalli, Narendra S. Khot, and Seung-Keon Kwak "Improved aircraft roll maneuver performance using smart deformable wings", Proc. SPIE 3323, Smart Structures and Materials 1998: Mathematics and Control in Smart Structures, (24 July 1998); https://doi.org/10.1117/12.316354

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