Aeroelastic and strength optimisation of a large aircraft wing with wing parameter variations

Battoo, R.

doi:10.2514/6.1998-1821

Cited by 5 publications

(3 citation statements)

References 3 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…This increases the flutter boundary for a range of freestream flight conditions giving the airfoil a more robust operational capacity. Predominantly, optimization studies in flutter have been conducted considering twoor three-dimensional wing bodies (Battoo and de Visser, 1998;Morris et al, 2008). Whilst research in airfoil shape optimization for aeroelastic performance is uncommon, two notable studies in the field have been identified.…”

Section: Introductionmentioning

confidence: 99%

Evolutionary optimization of transonic airfoils for static and dynamic trim performance

Candon

Carrese

Joseph³

et al. 2016

Journal of Intelligent Material Systems and Structures

View full text Add to dashboard Cite

The development and accelerated use of optimization frameworks in aircraft design is a testament to their ability to identify optimal and often non-intuitive shapes as a result of multi-disciplinary design objectives. Airfoil design is a continuously revised multi-disciplinary problem, and is pivotal to illustrate the performance of optimization frameworks involving numerical simulation, flexible shape parametrization, and intelligent evolutionary algorithms. An often overlooked component of this classic problem is to consider the dynamic aeroelastic behavior under trim conditions, which can generate explicit boundaries to the flight envelope. Trim introduces a significantly strong coupling with objectives governing static performance, e.g. aerodynamic and/or structural, thereby resulting in a highly nonlinear and discontinuous design space. In this paper, a multi-objective particle swarm optimization framework for multi-disciplinary performance improvement is presented, pertaining to aerodynamic, structural and aeroelastic design criteria at trim conditions. The framework is assisted by the construction of adaptive Kriging surrogates, which is cooperatively used with the numerical solver to identify optimal solutions within a computational constraint. Designer preferences are introduced to reflect the optimal compromise between the objectives. Results of the optimization process indicate a large spread in design variable influence and interaction, and a subtle yet clear distinction between all objectives is illustrated through the catalog of final airfoil candidates obtained.

show abstract

Section: Introductionmentioning

confidence: 99%

Evolutionary optimization of transonic airfoils for static and dynamic trim performance

Candon

Carrese

Joseph³

et al. 2016

Journal of Intelligent Material Systems and Structures

View full text Add to dashboard Cite

show abstract

“…The aeroelastic optimization process, in essence, is a unified, multidisciplinary design process which can overcome barriers between different discipline groups while reducing the design cycle time. Previous 2 Shock and Vibration researches have mainly optimized aircraft structures from the perspectives of both static and dynamic constraints such as stress, displacement, modal frequency, and flutter constraints; see, for example, the previous publications by Sikes et al [7], Patil [8], Battoo and de Visser [9], Maute and Allen [10], Tischler, and Venkayya [11]. However, these researches have not taken into account the geometric nonlinearity induced by large deformation.…”

Section: Introductionmentioning

confidence: 99%

“…According to (9) and the static equilibrium condition, the vibration equation of the dynamic system reduces to…”

Section: Geometrical Nonlinear Elasticitymentioning

confidence: 99%

Aeroelastic Optimization Design for High-Aspect-Ratio Wings with Large Deformation

Xie

Meng

Wang³

et al. 2017

Shock and Vibration

View full text Add to dashboard Cite

This paper presents a framework of aeroelastic optimization design for high-aspect-ratio wing with large deformation. A highly flexible wing model for wind tunnel test is optimized subjected to multiple aeroelastic constraints. Static aeroelastic analysis is carried out for the beamlike wing model, using a geometrically nonlinear beam formulation coupled with the nonplanar vortex lattice method. The flutter solutions are obtained using the -method based on the static equilibrium configuration. The corresponding unsteady aerodynamic forces are calculated by nonplanar doublet-lattice method. This paper obtains linear and nonlinear aeroelastic optimum results, respectively, by the ISIGHT optimization platform. In this optimization problem, parameters of beam cross section are chosen as the design variables to satisfy the displacement, flutter, and strength requirements, while minimizing wing weight. The results indicate that it is necessary to consider geometrical nonlinearity in aeroelastic optimization design. In addition, optimization strategies are explored to simplify the complex optimization process and reduce the computing time. Different criterion values are selected and studied for judging the effects of the simplified method on the computing time and the accuracy of results. In this way, the computing time is reduced by more than 30% on the premise of ensuring the accuracy.

show abstract

Aeroelastic two-level optimization for preliminary design of wing structures considering robust constraints

Wan

Zhang

et al. 2014

Chinese Journal of Aeronautics

View full text Add to dashboard Cite

Aeroelastic and strength optimisation of a large aircraft wing with wing parameter variations

Cited by 5 publications

References 3 publications

Evolutionary optimization of transonic airfoils for static and dynamic trim performance

Evolutionary optimization of transonic airfoils for static and dynamic trim performance

Aeroelastic Optimization Design for High-Aspect-Ratio Wings with Large Deformation

Aeroelastic two-level optimization for preliminary design of wing structures considering robust constraints

Contact Info

Product

Resources

About