The development of aircraft structural morphing devices involves the integration of complex and different systems, interacting and modifying their uncoupled characteristics. In detail, when adaptive skins, designed to afford the exceptional deformations needed to achieve morphing capabilities, are integrated into the actuation structural system, mass, stiffness and damping aspects are highly affected. This fact can have relevant impacts for the design process either from the static (load-bearing capabilities) and the dynamic (aeroelastic response, mainly), point of view. In order to properly characterise these important aspects, the manufacture of intermediate demonstrators was decided, not implementing all the design solutions yet but giving emphasis at certain subsystems. A mock-up was initially manufactured, whose structural properties (ability to carry out loads) were simply guaranteed by the elastic skin. The structural characteristics of the second one were insuured by the actuator system, only. The final one integrated both the concepts. The comparison of the results among the three allowed giving hints on the behaviour of the single and coupled subcomponents. In this paper, experimental modal analysis results are discussed, specifically addressed at characterising the damping coefficient, so important for aeroelasticity aspects.

Damping levels induced by morphing skin on an adaptive trailing edge device (ATED)

CONCILIO, ANTONIO;PECORA, ROSARIO;MAGNIFICO, MARCO;
2016

Abstract

The development of aircraft structural morphing devices involves the integration of complex and different systems, interacting and modifying their uncoupled characteristics. In detail, when adaptive skins, designed to afford the exceptional deformations needed to achieve morphing capabilities, are integrated into the actuation structural system, mass, stiffness and damping aspects are highly affected. This fact can have relevant impacts for the design process either from the static (load-bearing capabilities) and the dynamic (aeroelastic response, mainly), point of view. In order to properly characterise these important aspects, the manufacture of intermediate demonstrators was decided, not implementing all the design solutions yet but giving emphasis at certain subsystems. A mock-up was initially manufactured, whose structural properties (ability to carry out loads) were simply guaranteed by the elastic skin. The structural characteristics of the second one were insuured by the actuator system, only. The final one integrated both the concepts. The comparison of the results among the three allowed giving hints on the behaviour of the single and coupled subcomponents. In this paper, experimental modal analysis results are discussed, specifically addressed at characterising the damping coefficient, so important for aeroelasticity aspects.
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Utilizza questo identificativo per citare o creare un link a questo documento: http://hdl.handle.net/11588/630185
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