Geometrically nonlinear electro-aeroelastic framework for morphing wing with piezoelectric actuators

Abstract

In this paper, a flexible morphing wing with piezoelectric materials for morphing actuation is studied. The objectives of this paper are 1) to develop an integrated geometrically nonlinear electro-aeroelastic framework, which allows evaluating performances of flexible morphing wings with piezoelectric actuators, 2) to validate the developed analysis framework, and 3) to demonstrate the capability of the framework and explore the performance. This paper provides a description of the electro-aeroelastic equations of morphing wings taking into account piezoelectric effects, which can be used to actuate morphing wings. The electro-mechanical model is validated by comparing with experimental results. The validation with a single macro fiber composite showed a very good agreement between the experimental result and the simulation. The result of an actuation test with an integrated corrugated structure and macro fiber composite also reasonably agreed with the solution from the present code. Aeroelastic behaviors of a corrugated wing with the piezoelectric actuator are then explored. The camber morphing wing with the corrugated structure actuated by the piezoelectric actuator could provide a larger lift in the vicinity of the trailing edge. Such a camber morphing has a good potential to control aeroelastic response by wing morphing with piezoelectric actuation.

Keywords

• aeroelasticity
• structural analysis
• morphing wings
• piezoelectric materials
• smart structures
• aircraft