The FutureWings project is aimed to the theoretical study and to the preliminary experimental validation of a wing structure having the capability of change its aerodynamic shape by the use of a novel type of hybrid materials based on the implementation of layers of piezo-electric fibres into laminates of composite materials. A wing conceived as the proposed one will deform on command, that is, it will be possible to modify the aerodynamic load on the wing eliminating the use of traditional control surfaces. In this sense the application of the control devices is not conventional, that is, the piezo-electric active layers, embedded in the composite material structure, will be used to impose a desired deformed shape of the wing and not to control, as an example, in a passive way, the dynamic behaviour of the wing structure as presently done in a certain number of groundbreaking applications. The conceived role of the active piezo-electric layers (the deformed shape will be defined adopting a quasi-static approach) give us the possibility of the use of a low level of electric power and then it is expected that very low current intensity and medium voltage level will be necessary to actuate the FutureWings structure. Within the project a small scale model of a FutureWings will be manufactured based on the technological definition of the hybrid active composite laminate. Mechanical tests on this model will be carried out to verify the technical feasibility of the FutureWings concept. A good part of the efforts will be also devoted to the preliminary theoretical study of a FutureWings concept aircraft, that is an aeroplane without high velocity control surfaces on wings (ailerons), without horizontal control surfaces (fully deformable horizontal tail) and without rudder (fully deformable vertical tail). In addition, the complexity of problems and the novelty of challenges which characterize the project, paves the way for the preliminary development of an integrated design tool which would allow a simplified and, at the same time, robust manipulation of the structural architecture of the components of an aeroplane. The entire project is divide in 10 working packages and a number of 23 detailed tasks.
FUTUREWINGS - Wings of the Future
CHIARELLI, MARIO ROSARIO
2013-01-01
Abstract
The FutureWings project is aimed to the theoretical study and to the preliminary experimental validation of a wing structure having the capability of change its aerodynamic shape by the use of a novel type of hybrid materials based on the implementation of layers of piezo-electric fibres into laminates of composite materials. A wing conceived as the proposed one will deform on command, that is, it will be possible to modify the aerodynamic load on the wing eliminating the use of traditional control surfaces. In this sense the application of the control devices is not conventional, that is, the piezo-electric active layers, embedded in the composite material structure, will be used to impose a desired deformed shape of the wing and not to control, as an example, in a passive way, the dynamic behaviour of the wing structure as presently done in a certain number of groundbreaking applications. The conceived role of the active piezo-electric layers (the deformed shape will be defined adopting a quasi-static approach) give us the possibility of the use of a low level of electric power and then it is expected that very low current intensity and medium voltage level will be necessary to actuate the FutureWings structure. Within the project a small scale model of a FutureWings will be manufactured based on the technological definition of the hybrid active composite laminate. Mechanical tests on this model will be carried out to verify the technical feasibility of the FutureWings concept. A good part of the efforts will be also devoted to the preliminary theoretical study of a FutureWings concept aircraft, that is an aeroplane without high velocity control surfaces on wings (ailerons), without horizontal control surfaces (fully deformable horizontal tail) and without rudder (fully deformable vertical tail). In addition, the complexity of problems and the novelty of challenges which characterize the project, paves the way for the preliminary development of an integrated design tool which would allow a simplified and, at the same time, robust manipulation of the structural architecture of the components of an aeroplane. The entire project is divide in 10 working packages and a number of 23 detailed tasks.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
