Flutter Analysis of a Morphing Wing Technology Demonstrator: Numerical Simulation and Wind Tunnel Testing

INCAS Bulletin

Andreea KOREANSCHI¹  Ruxandra Mihaela BOTEZ²  Mehdi ben HENIA³  Francois MICHAUD⁴  Manuel FLORES SALINAS⁵  Olivier GUILLEMETTE⁶  Oliviu SUGAR GABOR⁷  Yvan TONDJI⁸ 

[1] LARCASE Laboratory of Applied Research in Active Control, Avionics and Aeroservoelasticity, École de Technologie Supérieure Montreal, H3C1K3, Quebec, Canada [e-mail];LARCASE Laboratory of Applied Research in Active Control, Avionics and Aeroservoelasticity, École de Technologie Supérieure Montreal, H3C1K3, Quebec, Canada, [e-mail]*;LARCASE Laboratory of Applied Research in Active Control, Avionics and Aeroservoelasticity, École de Technologie Supérieure Montreal, H3C1K3, Quebec, Canada, [e-mail];LARCASE Laboratory of Applied Research in Active Control, Avionics and Aeroservoelasticity, École de Technologie Supérieure Montreal, H3C1K3, Quebec, Canada, [e-mail];LARCASE Laboratory of Applied Research in Active Control, Avionics and Aeroservoelasticity, École de Technologie Supérieure Montreal, H3C1K3, Quebec, Canada, [e-mail];LARCASE Laboratory of Applied Research in Active Control, Avionics and Aeroservoelasticity, École de Technologie Supérieure Montreal, H3C1K3, Quebec, Canada, [e-mail];LARCASE Laboratory of Applied Research in Active Control, Avionics and Aeroservoelasticity, École de Technologie Supérieure Montreal, H3C1K3, Quebec, Canada, [e-mail];LARCASE Laboratory of Applied Research in Active Control, Avionics and Aeroservoelasticity, École de Technologie Supérieure Montreal, H3C1K3, Quebec, Canada, [e-mail];

关键词: morphing wing;    aeroelasticity;    flutter analysis;    control;    wind tunnel experiment;   

DOI  :  10.13111/2066-8201.2016.8.1.10

来源: DOAJ

【 摘 要 】

As part of a morphing wing technology project, the flutter analysis of two finite element models and the experimental results of a morphing wing demonstrator equipped with aileron are presented. The finite element models are representing a wing section situated at the tip of the wing; the first model corresponds to a traditional aluminium upper surface skin of constant thickness and the second model corresponds to a composite optimized upper surface skin for morphing capabilities. The two models were analyzed for flutter occurrence and effects on the aeroelastic behaviour of the wing were studied by replacing the aluminium upper surface skin of the wing with a specially developed composite version. The morphing wing model with composite upper surface was manufactured and fitted with three accelerometers to record the amplitudes and frequencies during tests at the subsonic wind tunnel facility at the National Research Council. The results presented showed that no aeroelastic phenomenon occurred at the speeds, angles of attack and aileron deflections studied in the wind tunnel and confirmed the prediction of the flutter analysis on the frequencies and modal displacements.

【 授权许可】

Unknown