Active control design for an unmanned air vehicle with a morphing wing. Issue 1 (4th January 2016)

• Record Type: Journal Article
• Authors: Li, Daochun; Guo, Shijun; Aburass, Tariq Osman; Yang, Daqing; Xiang, Jinwu
• Is Part Of: Aircraft engineering and aerospace technology. Volume 88:Issue 1(2016)
• Page Start: 168
• Page End: 177
• Publication Date: 2016-01-04
• Subjects: Active control -- Control effectiveness -- Control reversal -- Morphing wing; Aerospace engineering -- Periodicals; Aeronautics -- Systems engineering -- Periodicals; Astronautics -- Systems engineering -- Periodicals; Airplanes -- Equipment and supplies -- Periodicals; Space vehicles -- Equipment and supplies -- Periodicals; Aerospace industries -- Periodicals; 629.1
• DOI: 10.1108/AEAT-12-2013-0234
• Languages: English
• ISSNs: 1748-8842

Abstract

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.