Investigation of local load introduction methods in aircraft pre-design

Hürlimann, Florian; Kelm, Roland; Dugas, Michael; Kress, Gerald

doi:10.1016/j.ast.2011.04.008

Cited by 20 publications

(13 citation statements)

References 3 publications

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“…9(a), the wing root has been fixed as the applied BCs. 1g equivalent aerodynamic loads have also been defined using the SMT (shear, moment, torsion) method [37]. Table 6.…”

Section: Prototype Wing Box Modelmentioning

confidence: 99%

Structural similitude design for a scaled composite wing box based on optimised stacking sequence

You

Yasaee

Dayyani

2019

Composite Structures

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Testing appropriately-designed scaled-down structures instead of the full-size prototype structure is beneficial for quickly understanding the prototype structural behaviour in a cost-effective way. In this study, a novel approach is proposed to design scaled composite structures that can be used to predict the structural responses (e.g. static bending, modal behaviour, and compressive buckling) of the prototype. The objective is to overcome the main drawback of the conventional design method, which tends to result in low accuracy of the prototype prediction when certain variables cannot be appropriately scaled due to manufacturing constraints (e.g. ply thickness). In the present work, a set of scaling laws being independent of boundary conditions were firstly derived for plates and beams respectively based on their governing equations. The genetic algorithm (GA) was then applied to help design the stacking sequence of the scaled models, accommodating the mismatch in similarity conditions resulting from the manufacturing constraint in ply thickness. This GA-based design method was demonstrated to be effective in designing scaled plate, I-beam, and stiffened plate models, with improved accuracy in predicting the prototype structural behaviour compared with the conventional method. The application of this new design method was also extended to an A320 size wing box structure, validating its robustness for complex structures.

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“…9(a), the wing root has been fixed as the applied BCs. 1g equivalent aerodynamic loads have also been defined using the SMT (shear, moment, torsion) method [37]. Table 6.…”

Section: Prototype Wing Box Modelmentioning

confidence: 99%

Structural similitude design for a scaled composite wing box based on optimised stacking sequence

You

Yasaee

Dayyani

2019

Composite Structures

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“…In the high-fidelity part of the MDO process, a more detailed structural sizing of the aircraft wing is performed, and the selected load cases are recalculated with CFD analyses to obtain more accurate loads. Instead of SMT loads (“Shear, Moment, Torsion”, that is, described in Hürlimann et al . (2012)), pressure distributions can be used to have a more realistic load distribution on the wing’s outer surfaces.…”

Section: Structural Sizing and Optimization Modulesmentioning

confidence: 99%

Automated sizing of a composite wing for the usage within a multidisciplinary design process

Bach

Führer

Willberg

et al. 2016

Aircraft Eng & Aerospace Tech

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In times of reducing product development cycles and greater economical, safety and ecological requirements on aircraft structures innovative aircraft configurations with new materials and new structural design concepts become more and more important. Although their positive impact on the conventional pre-design methods come to their limits and to an appropriate tools for design and evaluation the need for Multidisciplinary Design Optimization increases.. In this paper a structural design and optimization module developed for the application in such an optimization process is presented. The module is coupled to the software environment DELiS where structural models mathematically described by finite elements can be automatically created, based on a parametric description. The outer loads, coming from CFD or aeroelastic calculations, are applied to the model and inner loads are calculated utilizing a linear static finite element analysis. To evaluate the results information about inner loads, displacements, properties and geometry are passed to the commercial software tool HyperSizer. Material parameters like thickness and stacking sequence and also cross sectional stringer parameters are optimized for the given loads on panel level. For sizing and optimization a set of failure criteria is used; analytical equations are available for a reduced calculation time. The capabilities of the module and the sizing approach are demonstrated on a composite wing of a long range transport aircraft.

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“…The structural layout, which is provided by the geometry module is afterwards meshed and analysed using the commercial software Nastran. Furthermore, Hürlimann et al (2011Hürlimann et al ( , 2012 developed a physics based multi-disciplinary process to compute the mass of a wing box. The included structural sizing algorithm is based on the finite element method.…”

Section: Introductionmentioning

confidence: 99%

Automated model generation and sizing of aircraft structures

Führer

Willberg

Freund

et al. 2016

Aircraft Eng & Aerospace Tech

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Purpose -To obtain a good start configuration in the early design phase, simulation tools are used to create a large number of product designs and to evaluate their performance. To reduce the effort for the model generation, analysis and evaluation, a design environment for thin-walled lightweight structures (DELiS) with the focus on structural mechanics of aircrafts has been developed. Design/methodology/approach -The core of DELiS is a parametric model generator, which creates models of thin-walled lightweight structures for the aircraft preliminary design process. It is based on the common parametric aircraft configuration schema (CPACS), which is an abstract aircraft namespace. DELiS facilitates interfaces to several commercial and non-commercial finite element solvers and sizing tools. Findings -The key principles and the advantages of the DELiS process are illustrated. Also, a convergence study of the finite element model of the wing and the fuselage and the result on the mass after the sizing process are shown. Due to the high flexibility of model generation with different levels of detail and the interface to the exchange database CPACS, DELiS is well suited to study the structural behaviour of different aircraft configurations in a multi-disciplinary design process. Originality/value -The abstract definition of the object-oriented model allows several dimensions of variability, such as different fidelity levels, for the resulting structural model. Wings and fuselages can be interpreted as finite beam models, to calculate the global dynamic behaviour of a structure, or as finite shell models.

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Investigation of local load introduction methods in aircraft pre-design

Cited by 20 publications

References 3 publications

Structural similitude design for a scaled composite wing box based on optimised stacking sequence

Structural similitude design for a scaled composite wing box based on optimised stacking sequence

Automated sizing of a composite wing for the usage within a multidisciplinary design process

Automated model generation and sizing of aircraft structures

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