Application of the active camber morphing concept based on compliant structures to a regional aircraft

Gaspari, Alessandro De; Ricci, Sergio

doi:10.1117/12.2045225

Cited by 7 publications

(8 citation statements)

References 12 publications

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“…A value equal to In order to design a compliant mechanism able to meet both kinematic (motion) and structural (loadcarrying) requirements, the design must be decomposed into several parts considering the mechanism design and the structure design, respectively, for a number of load conditions corresponding to the analyzed aerodynamic condition. This is a typical multi-objective design problem that was efficiently incorporated into the Genetic Algorithm [31]. The approach used for solving this kind of problems applied to our purposes is the so called Elitist Non-Dominated Sorting Genetic Algorithm (NSGA-II) [32].…”

Section: Design Of Morphing Compliant Devicesmentioning

confidence: 99%

Design, Manufacturing and Wind Tunnel Validation of a Morphing Compliant Wing

Gaspari

Riccobene

Ricci

2018

Journal of Aircraft

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The paper describes the activities performed at Politecnico di Milano in the framework of FP7-NOVEMOR Project aiming at the design, manufacturing and wind tunnel test of a wing model equipped with morphing leading and trailing edges based on compliant structures. Starting from the Reference Aircraft, i.e. a typical regional aircraft developed during NOVEMOR project, a small scale wind tunnel model has been derived to validate the proposed morphing concept and to correlate the numerical models in an experimental environment. A special attention has been devoted to the selection of the manufacturing technology due to the difficulty in realizing compliant structures with enough accuracy at a small scale level. After a short reminder of the tools developed for the design of variable camber morphing wings, the paper describes in details the design and manufacturing phases together with the functionality and wind tunnel tests.The results were used to validate the procedure adopted for the synthesis of the compliant structures and to evaluate the aerodynamic performances of the morphing wing. Nomenclature a = vector of CST extra-coefficients α = angle of attack [deg] α e = "effective" angle of attack [deg] c = airfoil chord [m] C d = drag coefficient for unit span C l = lift coefficient for unit span C m = pitch moment coefficient for unit span ∆κ = curvature difference function between the initial and the deformed shape [1/m] ∆L = length difference function between the initial and the deformed shape [m] δ LE = leading edge equivalent deflection [deg] δ T E = trailing edge equivalent deflection [deg] ψ = non-dimensional airfoil chordwise coordinate T p = CST-Vandermonde matrix of order p σ axial = axial stress due to the skin length variation [Pa]σ bend = bending stress due to the skin curvature variation [Pa]

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Section: Design Of Morphing Compliant Devicesmentioning

confidence: 99%

Design, Manufacturing and Wind Tunnel Validation of a Morphing Compliant Wing

Gaspari

Riccobene

Ricci

2018

Journal of Aircraft

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“…During the shape optimization described in this paper, only aerodynamic analyses have been performed in order to evaluate the performances of wings with and without morphing devices. Therefore the generation of structural models, based on the OOP-based PFEM (Parametric Finite Element Models) class, as well as the postprocessing class including Fluid-Structure Interaction (FSI) techniques, is not described [22].…”

Section: Multidisciplinary Modellingmentioning

confidence: 99%

“…Initially, the first level was implemented as a simple 2D shape optimization linked to a viscous and subsonic 2D aerodynamic solver, while the second one represented a general code for the synthesis of compliant mechanisms [15,21] and two software pieces have been developed separately. Recently, the first one has been extended in order to produce 3D wing models starting from the results which continued to be obtained by 2D shape optimization while the second one has been improved by adding multiobjective capabilities [22].…”

Section: Introductionmentioning

confidence: 99%

Knowledge-Based Shape Optimization of Morphing Wing for More Efficient Aircraft

Gaspari

Ricci

2015

International Journal of Aerospace Engineering

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An optimization procedure for the shape design of morphing aircraft is presented. The process is coupled with a knowledge-based framework combining parametric geometry representation, multidisciplinary modelling, and genetic algorithm. The parameterization method exploits the implicit properties of the Bernstein polynomial least squares fitting to allow both local and global shape control. The framework is able to introduce morphing shape changes in a feasible way, taking into account the presence of structural parts, such as the wing-box, the physical behaviour of the morphing skins, and the effects that these modifications have on the aerodynamic performances. It inherits CAD capabilities of generating 3D deformed morphing shapes and it is able to automatically produce aerodynamic and structural models linked to the same parametric geometry. Dedicated crossover and mutation strategies are used to allow the parametric framework to be efficiently incorporated into the genetic algorithm. This procedure is applied to the shape design of Reference Aircraft (RA) and to the assessment of the potential benefits that morphing devices can bring in terms of aircraft performances. It is adopted for the design of a variable camber morphing wing to investigate the effect of conformal leading and trailing edge control surfaces. Results concerning four different morphing configurations are reported.

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“…Focusing on the same reference aircraft, but on the main section of the wing, De Gaspari and colleagues. optimized compliant structures for both leading edge and trailing edge of the wing (De Gaspari and Ricci, 2011, 2014; Ricci et al, 2016). De Gaspari et al (2018) further used the same framework to develop morphing wing for a twin-prop regional aircraft (Ricci et al, 2018).…”

Section: Introductionmentioning

confidence: 99%

Development of a hybrid (rigid-flexible) morphing leading edge equipped with bending and extending capabilities

Fereidooni

Marchwica

Leung

et al. 2020

Journal of Intelligent Material Systems and Structures

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The development of the bench model of a hybrid (rigid-flexible) morphing leading edge is presented in this paper. The distinctive feature of this design centers on compounding a fully rigid nose with a flexible structure to create a seamless morphing leading edge. The rigid nose guarantees a precise shape control in the aerodynamically critical region of the wing whereas the flexible structure allows for an increase in both chord length and its camber. These improvements offer potential solutions to many of the challenges reported in the literature about the existing morphing wing designs. In order to evaluate the feasibility of the hybrid (rigid-flexible) concept and to demonstrate the aforementioned improvements, a bench model is developed and tested in-house. This paper focuses on the analysis performed to develop this model, including (1) aerodynamic shape optimization to devise the desired drooped shape; (2) geometry optimization to specify the dimensions of the rigid nose; (3) finite element analysis to characterize the skin component of the flexible structure; and (4) finite element analysis to estimate the actuation authority. Overall, the numerical and experimental results reveal the inherent advantage of the hybrid (rigid-flexible) concept from the smart structure standpoint; however, significant considerations are required to advance the technical readiness level of this design to a commercially viable solution for aircraft manufacturers.

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Application of the active camber morphing concept based on compliant structures to a regional aircraft

Cited by 7 publications

References 12 publications

Design, Manufacturing and Wind Tunnel Validation of a Morphing Compliant Wing

Design, Manufacturing and Wind Tunnel Validation of a Morphing Compliant Wing

Knowledge-Based Shape Optimization of Morphing Wing for More Efficient Aircraft

Development of a hybrid (rigid-flexible) morphing leading edge equipped with bending and extending capabilities

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