Salvatore Ameduri

A Novel SMA-based Concept for Airfoil Structural Morphing

The adaptive structures concept is of great interest in the aerospace field because of the several benefits which can be accomplished in the fields including noise reduction, load alleviation, weight reduction, etc., at a level in which they can be considered as compulsory in the design of future aircraft. Improvements in terms of the aerodynamic efficiency, aeroelastic behavior, stability, and manoeuvrability performance have already been proved through many international studies in the past. In the family of the Smart Materials, Shape Memory Alloys (SMA) seem to be a suitable solution for many static applications. Their high structural integrability in conjunction with actuation capabilities and a favorable performance per weight ratio, allows the development of original architectures. In this study, a morphing wing trailing edge concept is presented; morphing ability was introduced with the aim of replacing a conventional flap device. A compliant rib structure was designed, based on SMA actuators exhibiting structural potential (bearing external aerodynamic loads). Numerical results, achieved through a FE approach, are presented in terms of trailing edge induced displacement and morphed shape.

Airfoil Structural Morphing Based on S.M.A. Actuator Series: Numerical and Experimental Studies

Multiple flight regimes during typical aircraft missions mean that a single unique optimized configuration, that maximizes aerodynamic efficiency and maneuverability, cannot be defined. Discrete components such as ailerons and flaps provide some adaptability, although they are far from optimal. Wing morphing can significantly improve the performance of future aircraft, by adapting the wing shape to the specific flight regime requirements, but also represents a challenging problem: the structure has to be stiff to maintain its shape under loads, and yet be flexible to deform without collapse. One solution is to adopt structural elements made of smart materials; Shape Memory Alloys (SMAs) have demonstrated their suitability for many static applications due to their high structural integration potential and remarkable actuation capabilities. In this work, the airfoil camber at the wing trailing edge on a full scale wing of a civil regional transportation aircraft is controlled by substituting a traditional split flap with a hingeless, smooth morphed flap. Firstly, the development and testing of an actuator device based on a SMA ribbon, capable of a net rotation of 5 deg, is presented. Then, a flap bay is designed and experimentally tested in presence of static loads, based on a compliant rib built as a series repetition of the proposed actuator. An aero-thermo-mechanical simulation within a FE approach was adopted to estimate the behavior and performance of the compliant rib, integrating both aerodynamic loads, by means of a Vortex Lattice Method (VLM) code, and SMA phenomenology, implementing Liang and Rogers’ constitutive model. The prototype showed good actuation performance even in presence of external loads. Very good numerical-experimental correlation is found for the unloaded case, while some fatigue issues emerged in presence of static loads.

Wing Shape Control through an SMA-Based Device:

Based on numerical and experimental analyses, this article proposes an application of the smart structure concept aimed at realizing a bump on an airfoil profile, finalized to reduce transonic drag, through the use of shape memory alloys (SMAs). The ability of morphing the wing profile is functional to maximize the aerodynamic efficiency in different mission conditions. The use of the so-called smart materials allows a favorable actuation performance per weight ratio, also leading to simple and integrated devices. Currently, to model their mechanical behavior is still an open issue and this work presents some original ideas about this. Numerical results and experimental tests herein presented, demonstrate the efficacy of the developed concept device, calling for further studies on real structures; their correlation also validate the implemented simulation procedure.

Optimization and integration of shape memory alloy (SMA)-based elastic actuators within a morphing flap architecture

Aircraft morphing architectures are currently worldwide investigated to enhance performance while reducing weights, volumes and costs. A 3-flap wing, for instance, shall pay a penalty up to 100% due to the insertion of mechanical devices in its body. Moreover, the insertion of cover nacelles disturbs the wing aerodynamics itself. In addition, flapped wings are noisy: deformable, instead of slotted and flapped wings, may lead to significant enhancement also in this field. Within Joint European Initiative on Green Regional Aircraft frame, in cooperation with the University of Naples, Department of Aerospace Engineering, the authors with their colleagues came to the definition of dedicated morphing architectures. This paper focuses on the design and optimization of a morphing architecture based on Shape Memory Alloy (SMA) technology, aimed at increasing airfoil trailing edge curvature. The deformable rib system is constituted of four elastic elements. The aerodynamic loads were computed through a classical panel method for the most severe flight condition. The descriptive finite element model underwent an optimization process performed through a proprietary code, based on a genetic selection strategy. Resulting values, from the optimization study were different for the variables referring to each subsystem: plate thickness, depth and length, relative orientation, SMA ribbons thickness, depth and location. Trailing edge vertical displacement was assumed as target. The main features of the 4 elastic elements are presented in the body of the document. As expected, the more rearward is the element position, the less is the weight and size; decreasing values of the aerodynamic load led towards lighter solutions.

Airfoil Morphing Architecture Based on Shape Memory Alloys

The adaptive structures concept is of great interest in the aeronautical field because of the several benefits which can be accomplished in the design of future aircraft. Improvements in terms of aerodynamic efficiency, aero-elastic behaviour and manoeuvrability were proved by many international studies. The development of new structural architectures implementing and integrating innovative materials is mandatory for succeeding in these critical tasks. The so-called Smart Structure idea is more and more taken into account in aerospace applications Among the family of Smart Materials, Shape Memory Alloys (SMAs) certainly represents a convenient solution for many static applications. In this work, an application for a morphing wing trailing edge is presented as alternative for conventional flap devices. A compliant rib structure has been designed, based on SMA components working both as actuators, controlling wing chamber, and as structural elements, sustaining external aerodynamic loads. Achievable performance has been estimated by a FE approach; SMA behaviour has been modelled through a dedicated routine implementing the Liang & Rogers’ model for evaluating the internal stress and the minimum temperature necessary for activation. The numerical results have been presented in terms of induced displacements and morphed shape.Copyright

Wing chamber control architectures based on SMA: numerical investigations

Benefits in terms of aerodynamic efficiency, aeroelastic behaviour, stability and manoeuvrability performance coming from the adaptive variation of wing geometric (e.g. thickness and chamber) and mechanical (e.g. rigidity) parameters were widely proved. In this scenario, more and more efficient architectures based on innovative materials like shape memory alloys, piezoelectrics, magneto-rheologic fluids were ideated and related morphing ability was tested. Due to the large transmitted forces and deformations, for static applications, SMA based-on architectures were implemented. The essential idea of all these architectures is to integrate a SMA actuator, lacking of remarkable structural value, within a classical wing structure or within a suitably designed one. The main disadvantage of such architectures derives by the necessity of deforming a classical structure, not designed for reaching large displacements. In order to avoid these problems, in this work, the idea of integrating compliant structures by SMA elements, was considered. Some deformation strategies, focused on the wing aft part morphing, were ideated; related performance in terms of vertical displacement and rotation of the trailing edge was estimated by a FE approach. Each architecture is characterised by SMA rod elements able to guarantee large deformations and shape control under aerodynamic loads.

Real-time monitoring of a variable-camber aileron rib by original strain-angle transducer:

The object of this work is the conceptual design and modelling of a transducer based on fibre optic sensor and conceived to measure rotations of rigid components around a pivot. The device, namely, post-buckling-fibre Bragg grating, is constituted of a flexible metal plate hosting a fibre Bragg grating strain sensor; the edges of the plates are hinged onto the rotating rigid bodies, eccentrically with respect to the pivot. In this way, any increase in rotation produces a further bending of the plate corresponding to a fibre Bragg grating wavelength shift. Among the different applications, an aileron morphing architecture is considered. This architecture is composed of a rib made of three rigid parts, hinged each other and moved through a dedicated kinematic chain. Two post-buckling-fibre Bragg grating devices are installed between the adjacent rib blocks giving a measure of their current angular rotation. A peculiarity of the proposed device is its ability in working in post-buckling configuration, with two main advantages: (1) easy, plug-and-play, installation (the device supporting plate can be manually bent and plugged within the connection hinges) and (2) tuning of the sensitivity or range of measure, on the basis of the fibre Bragg grating location onto the plate and of the initial post-buckling level. At first, the conceptual design was dealt with a theoretical model describing the post-buckling behaviour of beams, highlighting the effect of the main design parameters; then, the plate displacement field was related to rotation angle of the rib; a dedicated numerical (finite element) model was thus realized to prove the concept feasibility and simulate in detail its functionality. Finally, experimental set-up was provided in order to validate the design.

Design of an FBG based-on sensor device for large displacement deformation

This article deals with the modeling of a strain-displacement transducer conceived for extending the FBG measurement range. The intrinsic fragility of the optical fiber limits their application to cases characterized by relatively small deformations. To extend the employ to the large displacement field (i.e. morphing applications), a dedicated device was conceived, constituted by a circular ring connected to the structure and laterally integrated with a FBG sensor. This device was mathematically modeled minimizing the potential energy this way arriving at a description of the displacement and deformation field along the curvilinear abscissa. The theoretical predictions were then validated through the FE approach, arriving to precious design and operative considerations on the use of the device itself.

Synchronized Switched Shunt Control Technique Applied on a Cantilevered Beam: Numerical and Experimental Investigations

During the last decades, some research interest in noise and vibration suppression has been focused on a specific control typology, based on semi-active architectures. Related advantages, like low or absent external power supply and intrinsic adaptive capacities, constitute an acceptable compromise between passive and active systems. Among the proposed ones, the so-called Synchronized Switched Shunt Architecture (SSSA) has shown good potential. Theoretical and numerical models able to describe simple systems (concentrated DOFs), controlled by an SSSA were already implemented. Anyway, these models are not immediately applicable to continuous structures (beams, plates, etc.). For this reason, and taking advantage of the previous works, a dedicated simulation code was ideated and implemented. In this article, the cited code was used to predict the benefits due to an SSSA device, applied on a beam element; later on, an experimental campaign was carried out on a dedicated prototype; finally, numerical and experimental results were compared in order to point out eventual discrepancies and assess the modeling capabilities. Sine signals were used to excite the beam resonance frequencies. Both numerical and experimental outcomes were expressed in time domain because of the unsteady nature (and consequent nonlinearity) of the examined semi-active control system.

Feasibility study on rotorcraft blade morphing in hovering

The study of acoustic noise generated by helicopter main rotors is the object of many theoretical and experimental investigations because of the complexity of the related physical phenomena and its strong influence on the vehicle performance. One of the main targets of the FriendCopter European Project is to define technical solutions aimed at improving the helicopter acoustic performance. In this work some related activities are described. The extremely complex operating environment of a helicopter rotor contributes to noise generation through several distinct mechanisms: among them, blade vortex interaction noise (BVI) results extremely annoying when it occurs. One method for BVI alleviation is to increase the separation of the tip vortex from the rotor plane using an adaptive blade tip (anhedral configuration) to diffuse the tip vortex or to displace it. In this work, as a first step of the investigation, a feasibility study on blade tip morphing will be addressed, neglecting any aeroacoustic estimation; a specific flight condition will be considered to evaluate the efficiency of a particular smart system based on the coupled action of shape memory alloys (SMAs) and magneto-rheological fluids (MRFs). Such a kind of actuation system has to realise an on-off mechanism through which the tip blade displacement is maximised: the properties of the MR fluid will be exploited to selectively reduce the bending stiffness spanwise so that the SMA actuation is increased. A theoretical model and numerical investigations will be shown to evaluate the reliability and the effectiveness of the integrated system.