Design, development and ground testing of hingeless elevons for MAV using piezoelectric composite actuators

Dwarakanathan, D; Ramkumar, R.; Raja, S.; Rao, P. Siva Subba

doi:10.12989/aas.2015.2.3.303

Cited by 5 publications

(3 citation statements)

References 19 publications

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Section: Mfcmentioning

confidence: 99%

“…Bilgen and Friswell then went on to implement optimisation techniques to control the actuation of MFC patches on a variable camber aerofoil (Bilgen and Friswell, 2012, 2013). Dwarakanathan et al (2015) modeled and collected wind tunnel data for a MFC-actuated hingeless flap on a glass fiber bimorph micro air vehicle (MAV). Gustafson (2011) designed, simulated, and verified with a wing tunnel, a morphing trailing edge of a wing in which a composite aerofoil was designed in a MFC bimorph configuration for a MAV.…”

Section: Introductionmentioning

confidence: 99%

“…The thermal analogy has been shown to be reasonably accurate in terms of static deformation but transient behavior can require unwieldy models and accurate modeling of any insulating layers is needed to accurately capture dynamic behavior (Côté et al 2004). As a result, it has been investigated further and adopted by many different researchers when modeling the piezoelectric-induced strain (Bilgen et al, 2011; Dwarakanathan et al, 2015; Gustafson, 2011; Paradies and Ciresa, 2009; Tawfik et al, 2011).…”

Section: Introductionmentioning

confidence: 99%

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Modeling of macro fiber composite actuated laminate plates and aerofoils

Thomas

Calzada

Gilmour

2019

Journal of Intelligent Material Systems and Structures

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This article investigates the modeling of macro fiber composite-actuated laminate plates with distributed actuator patches. The investigation details an analytical and finite element modeling, with experimental validation of the bending strain and deflection of an epoxy E-glass fiber composite laminate. An analytical approach is also developed to estimate the plate deflection from the experimental strain measurements. The analytical method uses direct integration of single dimensional plate bending moments obtained by strain-induced shear moments from the macro fiber composite actuators. Finite element analysis software was used with the composite laminate modeled in ANSYS ACP. The results from both analytical and numerical models show good agreement with the experimental results, with strain values agreeing within 20 ppm and the maximum difference in deflection not exceeding 0.1 mm between models. Finally, an application of the analytical model for developing morphing aerofoil designs is demonstrated.

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Section: Mfcmentioning

confidence: 99%