The adaptive structures’ concept is of great interest for researchers involved in the aeronautical field because of the several benefits which can be accomplished and are compulsory in the design of future aircrafts, such as noise reduction, load alleviation, weight reduction. Improvements in terms of aerodynamic efficiency, aeroelastic behaviour, stability and manoeuvrability performance were proved by many international studies, based on the Smart Structure concept. Among the family of Smart Materials, Shape Memory Alloys (SMAs) seems to be the most suitable solution for many static applications in the aerospace field. Their high structural integration and thermo-mechanical properties, in conjunction with actuation capability and a favourable performance per weight ratio, allows for the development of an original and architecture. In this work, an application for a morphing wing trailing edge is presented; morphing capability was introduced in order to replace a conventional flap device. A compliant rib structure has been designed, based on SMA actuators able to sustain the external aerodynamic loads and simultaneously allow controlled wing shape modification. The numerical results, achieved through a FE approach, have been presented in terms of trailing edge induced displacement and morphed shape.

A Novel SMA implementation oriented to Airfoil Morphing

PECORA, ROSARIO;LECCE, LEONARDO;
2009

Abstract

The adaptive structures’ concept is of great interest for researchers involved in the aeronautical field because of the several benefits which can be accomplished and are compulsory in the design of future aircrafts, such as noise reduction, load alleviation, weight reduction. Improvements in terms of aerodynamic efficiency, aeroelastic behaviour, stability and manoeuvrability performance were proved by many international studies, based on the Smart Structure concept. Among the family of Smart Materials, Shape Memory Alloys (SMAs) seems to be the most suitable solution for many static applications in the aerospace field. Their high structural integration and thermo-mechanical properties, in conjunction with actuation capability and a favourable performance per weight ratio, allows for the development of an original and architecture. In this work, an application for a morphing wing trailing edge is presented; morphing capability was introduced in order to replace a conventional flap device. A compliant rib structure has been designed, based on SMA actuators able to sustain the external aerodynamic loads and simultaneously allow controlled wing shape modification. The numerical results, achieved through a FE approach, have been presented in terms of trailing edge induced displacement and morphed shape.
9781441908452
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11588/425820
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