22nd Congress of International Council of the Aeronautical Sciences, Harrogate, UK, 28 August - 1st September, 2000
Paper ICAS 2000-1.4.1

FLEXIBLE COMPOSITE WING WITH INTERNAL ACTUATION FOR ROLL MANEUVER

N. S. Khot (1), J. V. Zweber (1), D. E. Veley (1), H. Öz (2), F. E. Eastep (3)
(1) AFRL/VASD, USA; (2) Ohio State University, USA; (3) University of Dayton, USA

Keywords: composite material, flexible wing, control design, roll maneuver, smart structures

This paper is concerned with designing an optimum composite flexible wing structure to enhance roll maneuver capability at high dynamic pressures using an embedded actuating system without external control surfaces. A minimum weight design, with constraints on strength for three different flight conditions, on the frequency distribution and lift effectiveness was used for this study. The elastic twist and camber is achieved by providing a system of actuating elements distributed within the internal substructure of the wing to provide control forces. The modal approach is used to develop the dynamic equilibrium equations which culminates in the steady roll maneuver of a wing subjected to aerodynamic loads and the actuating forces. The distribution of actuating forces to achieve the specified steady roll rate and roll angle of the flexible vehicle within a specified time was determined by using Independent Modal-Space Control (IMSC) design approach. Here, a full-scale realistic wing is considered for the assessment of the strain energy and distribution of actuator forces required to produce the antisymmetric twist and camber deformation to achieve the specified roll performance.

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