Active control design for an unmanned air vehicle with a morphing wing

Abstract

Purpose

The purpose of this study is to develop an active controller of both leading-edge (LE) and trailing-edge (TE) control surfaces for an unmanned air vehicle (UAV) with a composite morphing wing.

Design/methodology/approach

Instead of conventional hinged control surfaces, both LE and TE seamless control surfaces were integrated with the wing. Based on the longitudinal state space equation, the root locus plot of the morphing wing aircraft, with a stability augmented system, was constructed. Using the pole placement, the feedback gain matrix for an active control was obtained.

Findings

The aerodynamic benefits of a morphing wing section are compared with a wing of a rigid control surface. However, the 3D morphing wing with a large sweptback angle produces a washout negative aeroelastic effect, which causes a significant reduction of the control effectiveness. The results show that the stability augmentation system can significantly improve the longitudinal controllability of an aircraft with a morphing wing.

Practical implications

This study is necessary to analyse the effect of a morphing wing on an UAV and perform a comparison with the rigid model.

Originality/value

The control surfaces assignment plan for trim, pitch and roll control was obtained. An active control algorism for the morphing wing was created to satisfy the required stability and control effectiveness by operating the LE and TE control surfaces according to flight conditions. The aeroelastic effect of control derivatives on the morphing aircraft was considered.

Citation

Li, D., Guo, S., Aburass, T.O., Yang, D. and Xiang, J. (2016), "Active control design for an unmanned air vehicle with a morphing wing", Aircraft Engineering and Aerospace Technology, Vol. 88 No. 1, pp. 168-177. https://doi.org/10.1108/AEAT-12-2013-0234