Flutter suppression and stability analysis for a variable-span wing via morphing technology

• Published in: Journal of sound and vibration Vol. 412; pp. 410 - 423
• Main Authors: Li, Wencheng, Jin, Dongping
• Format: Journal Article
• Language: English
• Published: Amsterdam Elsevier Ltd 06.01.2018; Elsevier Science Ltd
• Subjects: Aerodynamic characteristics; Aerodynamic loads; Aerodynamic stability; Aerodynamics; Ailerons; Axially moving plate; Cantilever plates; Computer simulation; Dynamic stability; Equations of motion; Flutter analysis; Flutter suppression; Mathematical models; Morphing; Morphing wing; Motion stability; Piston theory; Simulation; Slowly varying system; Stability; Stability analysis; Supersonic aircraft; Transient stability; Upper bounds; Vibration; Axially moving plate; Stability; Morphing wing; Flutter suppression; Slowly varying system
• ISSN: 0022-460X; 1095-8568
• DOI: 10.1016/j.jsv.2017.10.009

A morphing wing can enhance aerodynamic characteristics and control authority as an alternative to using ailerons. To use morphing technology for flutter suppression, the dynamical behavior and stability of a variable-span wing subjected to the supersonic aerodynamic loads are investigated numerically in this paper. An axially moving cantilever plate is employed to model the variable-span wing, in which the governing equations of motion are established via the Kane method and piston theory. A morphing strategy based on axially moving rates is proposed to suppress the flutter that occurs beyond the critical span length, and the flutter stability is verified by Floquet theory. Furthermore, the transient stability during the morphing motion is analyzed and the upper bound of the morphing rate is obtained. The simulation results indicate that the proposed morphing law, which is varying periodically with a proper amplitude, could accomplish the flutter suppression. Further, the upper bound of the morphing speed decreases rapidly once the span length is close to its critical span length.