Aero-servo-elastic design of a morphing wing trailing edge system for enhanced cruise performance

Arena, Maurizio; Concilio, Antonio; Pecora, Rosario

doi:10.1016/j.ast.2019.01.020

Cited by 40 publications

(22 citation statements)

References 22 publications

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“…Winglet movables were also modelled through equivalent beams, and the rotation around their longitudinal axis was constrained by means of grounded springs reproducing the stiffness of the actuators in power-on mode. The aircraft aeroelastic stability equation was solved in the space of modal coordinates and in the frequency domain; the critical speeds were evaluated by means of PK-method [50] under the following assumptions: All flutter calculations and the elaboration of Vg plots were made in SANDY software environment [51].…”

Section: Aeroelastic Trade-offmentioning

confidence: 99%

Integrated Design of a Morphing Winglet for Active Load Control and Alleviation of Turboprop Regional Aircraft

et al. 2021

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Aircraft winglets are well-established devices that improve aircraft fuel efficiency by enabling a higher lift over drag ratios and lower induced drag. Retrofitting winglets to existing aircraft also increases aircraft payload/range by the same order of the fuel burn savings, although the additional loads and moments imparted to the wing may impact structural interfaces, adding more weight to the wing. Winglet installation on aircraft wing influences numerous design parameters and requires a proper balance between aerodynamics and weight efficiency. Advanced dynamic aeroelastic analyses of the wing/winglet structure are also crucial for this assessment. Within the scope of the Clean Sky 2 REG IADP Airgreen 2 project, targeting novel technologies for next-generation regional aircraft, this paper deals with the integrated design of a full-scale morphing winglet for the purpose of improving aircraft aerodynamic efficiency in off-design flight conditions, lowering wing-bending moments due to maneuvers and increasing aircraft flight stability through morphing technology. A fault-tolerant morphing winglet architecture, based on two independent and asynchronous control surfaces with variable camber and differential settings, is presented. The system is designed to face different flight situations by a proper action on the movable control tabs. The potential for reducing wing and winglet loads by means of the winglet control surfaces is numerically assessed, along with the expected aerodynamic performance and the actuation systems’ integration in the winglet surface geometry. Such a device was designed by CIRA for regional aircraft installation, whereas the aerodynamic benefits and performance were estimated by ONERA on the natural laminar flow wing. An active load controller was developed by PoliMI and UniNA performed aeroelastic trade-offs and flutter calculations due to the coupling of winglet movable harmonics and aircraft wing bending and torsion.

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Section: Aeroelastic Trade-offmentioning

confidence: 99%

Integrated Design of a Morphing Winglet for Active Load Control and Alleviation of Turboprop Regional Aircraft

et al. 2021

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“…The SARISTU included a series of research collaborations to addresses aircraft weight and operational cost reductions as well as an improvement in the flight profile specific aerodynamic performance [39]. Other projects by the European Union were the "Novel Air Vehicle Configurations" (NOVEMOR) project, in which morphing wing solutions (span and camber strategies and wing-tip devices) were proposed to enhance lift capabilities and maneuvering [40]; the "Clean-Sky 1 and 2" projects [41,42]; the "Combined Morphing Assessment Software Using Flight Envelope Data" (CHANGE) project, which developed a modular software architecture capable of determining and achieving optimum wing shape [43]; and the "Sustainable and Energy Efficient Aviation" (SE2A) project aimed to investigate the Morphing structures for the 1g-wing to exploit the nonlinear structural behavior of wing design components to achieve passive load alleviation [44].…”

Section: Literature Surveymentioning

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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“…In modern aircraft, active gust load alleviation has become an integral part that has allowed for cost savings in terms of fuel and maintenance [18]. Moreover, the development of new technologies such as morphing wings has increased gust load alleviation performance as studied, for example, in [20][21][22][23][24][25]. However, to achieve a maximum overall aircraft performance, the gust load alleviation function needs to be already considered needs to be considered in early aircraft design phases [26].…”

Section: Previous Campaigns: Lessons Learnedmentioning

confidence: 99%

Design and Optimization of an Aeroservoelastic Wind Tunnel Model

Dillinger

Meddaikar

Lübker

et al. 2020

Fluids

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Through the combination of passive and active load alleviation techniques, this paper presents the design, optimization, manufacturing, and update of a flexible composite wind tunnel model. In a first step, starting from the specification of an adequate wing and trailing edge flap geometry, passive, static aeroelastic stiffness optimizations for various objective functions have been performed. The second optimization step comprised a discretization of the continuous stiffness distributions, resulting in manufacturable stacking sequences. In order to determine which of the objective functions investigated in the passive structural optimization most efficiently complemented the projected active control schemes, the condensed modal finite element models were integrated in an aeroelastic model, involving a dedicated gust load alleviation controller. The most promising design was selected for manufacturing. The finite element representation could be updated to conform to the measured eigenfrequencies, based on the dynamic identification of the model. Eventually, a wind tunnel test campaign was conducted in November 2018 and results have been examined in separate reports.

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Aero-servo-elastic design of a morphing wing trailing edge system for enhanced cruise performance

Cited by 40 publications

References 22 publications

Integrated Design of a Morphing Winglet for Active Load Control and Alleviation of Turboprop Regional Aircraft

Integrated Design of a Morphing Winglet for Active Load Control and Alleviation of Turboprop Regional Aircraft

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

Design and Optimization of an Aeroservoelastic Wind Tunnel Model

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