Reduced-order modelling of non-linear, transient aerodynamics of the HIRENASD wing

Lindhorst, K.; Haupt, Matthias; Horst, Peter

doi:10.1017/aer.2016.12

Cited by 6 publications

(4 citation statements)

References 29 publications

(56 reference statements)

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“…This study employs the coupling environment ifls, which has already been used to model various multi-physics problems (see e.g., [25][26][27]). Ifls follows a modular approach that allows to couple two or more black-box solvers in a partitioned way.…”

Section: Numerical Simulation Frameworkmentioning

confidence: 99%

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Challenges of Fully-Coupled High-Fidelity Ditching Simulations

et al. 2019

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An important element of the process of aircraft certification is the demonstration of the crashworthiness of the structure in the event of an emergency landing on water, also referred to as ditching. Novel numerical simulation methods, that incorporate the interaction between fluid and structure, open up a promising way to model ditching in full scale. This study focuses on two main issues of high-fidelity ditching simulations: the development of a suitable fluid-structure coupling framework and the generation of the structural model of the aircraft. The first issue is addressed by implementing a partitioned coupling approach, which combines a finite volume hydrodynamic fluid solver as well as a finite element structural solver. The developed framework is validated by means of two ditching-like experiments, which consider the drop test of a rigid cylinder and a deformable cylindrical shell. The results of the validation studies indicate that an alternative to the standard Dirichlet-Neumann partitioning approach is needed if a strong added-mass effect is present. For the full-scale simulation of aircraft ditching, structural models become more complex and have to account for damage. Due to its high localization, the damage creates large differences in model scale and usually entails severe non-linearities in the model. To address the issue of increasing computational effort for such models, the process of developing a multi-scale model for the simulation of the failure of fuselage frames is presented.

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Section: Numerical Simulation Frameworkmentioning

confidence: 99%

“…The fluid equations are solved in the Arbitrary Lagrangian-Eulerian (ALE) form to account for mesh movement in the convective term. The communication between ifls and OpenFOAM is achieved by using a socket- [25][26][27]).…”

Section: Numerical Simulation Frameworkmentioning

confidence: 99%

Challenges of Fully-Coupled High-Fidelity Ditching Simulations

et al. 2019

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“…The MDO procedure should be as fast as possible; therefore, utilising lower fidelity and computationally cheaper models as much as possible is favoured as long as the final result is not jeopardised. Numerical solutions such as Reduced Order Models [38,39], surrogate-models [40,41] and multifidelity [42] can alleviate the computation burden. Furthermore, several methods can be used to obtain surrogate models based on samples of previously calculated results, therefore avoiding the evaluation of the constraints and objectives functions directly from expensive high-fidelity models [43].…”

Section: Introductionmentioning

confidence: 99%

On the multi-fidelity approach in surrogate-based multidisciplinary design optimisation of high-aspect-ratio wing aircraft

et al. 2022

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The reduction of computational costs in the context of the Multidisciplinary Design Optimisation of a typical medium-range aircraft was investigated through an assessment of active constraints and the use of multi-fidelity models-based estimation of drag and structural stress. The results show that for this problem, from the set of considered constraints that includes flutter boundary, the active constraint is a 2.5g pull up Maximum Take Off Weight. Results show that the multi-fidelity approach reduced the required high-fidelity aerodynamic number of evaluations, for both drag assessment and stress assessment with sufficient level of accuracy for the former and conservatively for the latter. Further computational cost reduction can be achieved using a surrogate model based Multidisciplinary Design Optimisation. The best configuration attained shows an Aspect Ratio increase of 16%, a reduction of 4.5% in fuel consumption and wing structural weight increase of 2.7% relative to a predefined baseline configuration.

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“…Furthermore, they demonstrated the application on a three-dimensional case [21], the high-Reynolds-number aerostructural dynamics (HIRENASD), and the model can capture the influences of nonlinear aerodynamic effects on the forces. Moreover, the model can be used in both static and transient aeroelastic investigations at a fixed Mach number [22]. Kou and Zhang [23] applied radial basis function neural network to model twodimensional nonlinear aerodynamics.…”

Section: Introductionmentioning

confidence: 99%

Static Aeroelastic Modeling and Rapid Analysis of Wings in Transonic Flow

Yang

Liu

Zhang

2018

International Journal of Aerospace Engineering

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A fast static aeroelastic analysis method, coupling with the modal method and Kriging surrogate model, is proposed in this paper. The deflection of the wing is described by the modal method, and the Kriging surrogate model is utilized to model the generalized forces under different deformations, angles of attack, and Mach numbers in order to replace the CFD solver. We analyzed the static aeroelasticity of HIRENASD wing in transonic flow field by coupling with the generalized force model by the static equilibrium equation. The results were compared with those of the experimental data and the references, and the comparison shows that the method is useful for the small deflections. After enough training cases are finished, the high-accuracy aerodynamic force coefficients and wing deflection will be obtained rapidly, which will only take several seconds. This method is more time saving than the CFD/CSD method, when it comes to a large quantity of the static aeroelastic analyses. Hence, it has good perspective for engineering applications during the aircraft design period.

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Reduced-order modelling of non-linear, transient aerodynamics of the HIRENASD wing

Cited by 6 publications

References 29 publications

Challenges of Fully-Coupled High-Fidelity Ditching Simulations

Challenges of Fully-Coupled High-Fidelity Ditching Simulations

On the multi-fidelity approach in surrogate-based multidisciplinary design optimisation of high-aspect-ratio wing aircraft

Static Aeroelastic Modeling and Rapid Analysis of Wings in Transonic Flow

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