Develpoment of advanced structural multifield models for the study of smart wing
type: CreativeWork
description: In the field of aeronautics, shape morphing has been used to identify those aircraft that undergo certain geometrical changes to enhance or adapt to their mission profile. In spite of there is not a clear definition of shape morphing, it is a general agreement that the conventional hinged control surfaces or high lift device, such as flap or slat that provide discrete geometry changes cannot be considered as morphing. Otherwise from the conventional solution the shape morphing required: distributed high-power density actuation, structural mechanization, flexible skins, and control law development. In these scenario, models able to capture the insertion of new generation sensor and actuator, and able to minimize the computational cost become very interesting. Refined plate theories offer significant advantages in terms of accuracy of the solution and detection of non-classical effects. The drawback of these theories is that a higher computational cost is incurred because of the presence of a large number of variables. Such an increase could become prohibitive in the case of the application of computational methods such as the Finite Element Method. Moreover to control the behaviour of an distributed actuated wing are necessary model with low computational times. In fact the computational time must be lower than the characteristic time of the controlled phenomenon. In this contest it is very interesting try to identify a method able to build reduced model which didn't penalize the results fidelity. The question which require an answer to identify the reduced model is: for a given problem (geometry, loading, boundary conditions, lamination lay-out) what is the most accurate theory in terms of a fixed accuracy with the lowest computational time? A method able to find an answer has been developed in the first part of this work. The Carrera Unified Formulations (CUF) give the possibility to run various theories for an assigned problem (materials, geometry, lamination lay-…
abstract: In the field of aeronautics, shape morphing has been used to identify those aircraft that undergo certain geometrical changes to enhance or adapt to their mission profile. In spite of there is not a clear definition of shape morphing, it is a general agreement that the conventional hinged control surfaces or high lift device, such as flap or slat that provide discrete geometry changes cannot be considered as morphing. Otherwise from the conventional solution the shape morphing required: distributed high-power density actuation, structural mechanization, flexible skins, and control law development. In these scenario, models able to capture the insertion of new generation sensor and actuator, and able to minimize the computational cost become very interesting. Refined plate theories offer significant advantages in terms of accuracy of the solution and detection of non-classical effects. The drawback of these theories is that a higher computational cost is incurred because of the presence of a large number of variables. Such an increase could become prohibitive in the case of the application of computational methods such as the Finite Element Method. Moreover to control the behaviour of an distributed actuated wing are necessary model with low computational times. In fact the computational time must be lower than the characteristic time of the controlled phenomenon. In this contest it is very interesting try to identify a method able to build reduced model which didn't penalize the results fidelity. The question which require an answer to identify the reduced model is: for a given problem (geometry, loading, boundary conditions, lamination lay-out) what is the most accurate theory in terms of a fixed accuracy with the lowest computational time? A method able to find an answer has been developed in the first part of this work. The Carrera Unified Formulations (CUF) give the possibility to run various theories for an assigned problem (materials, geometry, lamination lay-…
author: MIGLIORETTI, FEDERICO
language: eng
keywords: Settore ING-IND/04 - Costruzioni e Strutture Aerospaziali
date published: 2013
date modified: 2026-07-24T03:51:05Z
provider: Politecnico di Torino
publisher: Networked Digital Library of Theses and Dissertations
type: WebPage
source organization: Politecnico di Torino

PropertyValue
property ID: Handle
value: http://hdl.handle.net/11583/2509280