Numerical and experimental transition results evaluation for a morphing wing and aileron system

Botez, Ruxandra Mihaela; Koreanschi, Andreea; Gabor, Oliviu Şugar; Tondji, Yvan; Guezguez, Mohamed Sadok; Kammegne, J. T.; Grigorie, Teodor Lucian; Sandu, Dragos George; Mébarki, Youssef; Mamou, Mahmoud; Amoroso, Francesco; Pecora, Rosario; Lecce, Leonardo; Amendola, Gianluca; Dimino, Ignazio; Concilio, Antonio

doi:10.1017/aer.2018.15

Cited by 38 publications

(14 citation statements)

References 33 publications

(30 reference statements)

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“…Various solutions have been implemented by the aviation industry, including smart material technology, laminar flow technology, air traffic management technologies, advanced propulsion techniques and sustainable fuels [2][3][4]. Morphing wing technology is one of the technologies showing high potential in decreasing aircraft fuel consumption [5][6][7][8]. Even though there is no settled definition for "morphing", this term is borrowed in Aviation Technology from avian flight to describe the ability to modify maneuvers at certain flight characteristics in order to obtain the best possible performance.…”

Section: Outline Of the Researchmentioning

confidence: 99%

Aerodynamic Design Optimization of a Morphing Leading Edge and Trailing Edge Airfoil–Application on the UAS-S45

et al. 2021

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This work presents an aerodynamic optimization method for a Droop Nose Leading Edge (DNLE) and Morphing Trailing Edge (MTE) of a UAS-S45 root airfoil by using Bezier-PARSEC parameterization. The method is performed using a hybrid optimization technique based on a Particle Swarm Optimization (PSO) algorithm combined with a Pattern Search algorithm. This is needed to provide an efficient exploitation of the potential configurations obtained by the PSO algorithm. The drag minimization and the endurance maximization were investigated for these configurations individually as two single-objective optimization functions. The aerodynamic calculations in the optimization framework were performed using the XFOIL solver with flow transition estimation criteria, and these results were next validated with a Computational Fluid Dynamics solver using the Transition Shear Stress Transport (SST) turbulence model. The optimization was conducted at different flight conditions. Both the DNLE and MTE optimized airfoils showed a significant improvement in the overall aerodynamic performance, and MTE airfoils increased the efficiency of CL3/2/CD by 10.25%, indicating better endurance performance. Therefore, both DNLE and MTE configurations show promising results in enhancing the aerodynamic efficiency of the UAS-S45 airfoil.

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Section: Outline Of the Researchmentioning

confidence: 99%

Aerodynamic Design Optimization of a Morphing Leading Edge and Trailing Edge Airfoil–Application on the UAS-S45

et al. 2021

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“…Contributing to the work on global warming, recent studies performed by the Laboratory of Applied Research in Active Controls, Avionics, and AeroServoElasticity (LARCASE) were targeted to improve aircraft aerodynamics characteristics using adaptive structures (i.e., "morphing wings" or "adaptive wings") [38]. The knowledge and skills of LARCASE in this discipline were notably highlighted in 2014 by winning the Consortium for Research and Innovation in Aerospace in Québec (CRIAQ) runner-up award for the CRIAQ MDO505 project, entitled "Morphing Architectures and related Technologies to improve the Wings Efficiency" [39][40][41][42][43][44][45][46][47].…”

Section: Literature Review: Aircraft Geometry Improvementmentioning

confidence: 99%

New Aerodynamic Studies of an Adaptive Winglet Application on the Regional Jet CRJ700

et al. 2021

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This study aims to evaluates how an adaptive winglet during flight can improve aircraft aerodynamic characteristics of the CRJ700. The aircraft geometry was slightly modified to integrate a one-rotation axis adaptive winglet. Aerodynamic characteristics of the new adaptive design were computed using a validated high-fidelity aerodynamic model developed with the open-source code OpenFoam. The aerodynamic model successively uses the two solvers simpleFoam and rhoSimpleFoam based on Reynold Averaged Navier Stokes equations. Characteristics of the adaptive winglet design were studied for 16 flight conditions, representative of climb and cruise usually considered by the CRJ700. The adaptive winglet can increase the lift-to-drag ratio by up to 6.10% and reduce the drag coefficient by up to 2.65%. This study also compared the aerodynamic polar and pitching moment coefficients variations of the Bombardier CRJ700 equipped with an adaptive versus a fixed winglet.

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“…A three-blocks segmentation was considered sufficient in order to meet the desired target shapes. The morphed target shapes have been estimated by means of a 2D aerodynamic optimisation (21) with the objective to increase Lift-Drag ratio. Block B1 is rigidly connected to the rest of the wing structure through a torsion tube enabling aileron rotation for roll control.…”

Section: The Aileron Structurementioning

confidence: 99%

A linear guide-based actuation concept for a novel morphing aileron

Amendola¹,

Dimino²,

Concilio³

et al. 2019

Aeronaut. j.

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This paper deals with the actuation system design of a full-scale morphing aileron for regional aircraft. The aileron is allowed to smoothly change its geometrical configuration and perform the in-flight transition from a baseline shape to a set of optimal morphed ones pre-defined on the basis of aerodynamic requirements. The design of such innovative aileron is aimed not only at substituting the conventional aileron installed on a real aircraft but also to provide additional functionality. The aileron is free to rotate around its main hinge axis and it is also allowed to smoothly modify camber with two independent actuation systems. In such manner it can be used also during cruise with a symmetric deflection between the two half wings in order to reduce drag in off design condition. To accomplish variable aileron shape, a rigid-body mechanism was designed. The proposed aileron architecture is characterised by segmented adaptive ribs rigidly linked each other with spanwise reinforcements such as spars and stringers in a multi-box arrangement. Each rib is split into two movable plates connected by means of rotational hinges in a finger-like mechanism. The mechanism is driven by a load-bearing actuator by means of a kinematic chain opportunely tied based on the structural requirements in terms of shape to be matched and load to be withstood. The proposed device is an innovative arrangement of the quick-return mechanism composed of a beam leverage, commercial linear guides and a crank. The actuator shaft is directly inserted in the crank, which transmits the rotation to the linear guide that slide along a rail moving upward or downward the beam thus resulting in a camber variation. The entire aileron is moved by three leverages internally contained and distributed along the first two bays while the most external ribs are considered passive and their movement slaved. Two actuation layouts are analytically and numerically studied, the analytical theory is presented and validated by means of a multi-body simulation. Moreover, a linear static analysis was carried out under the hypothesis of glued contact between linear guides components simulating a jamming condition. This assumption has been formulated because it represents the most severe condition that envelop all the operative loads to which the actuation system is subjected. The analyses conducted are preliminarily aimed to verify that no failure occur under the imposed loads. In this first design loop, the vertical static force acting on the linear carriage exceeded allowable value and then a new configuration with double-sided linear guides was then investigated.

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Numerical and experimental transition results evaluation for a morphing wing and aileron system

Cited by 38 publications

References 33 publications

Aerodynamic Design Optimization of a Morphing Leading Edge and Trailing Edge Airfoil–Application on the UAS-S45

Aerodynamic Design Optimization of a Morphing Leading Edge and Trailing Edge Airfoil–Application on the UAS-S45

New Aerodynamic Studies of an Adaptive Winglet Application on the Regional Jet CRJ700

A linear guide-based actuation concept for a novel morphing aileron

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