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Structural sizing in the preliminary design



 

 Sizing load cases on the underside of the wing in the iGREEN configuration
zum Bild Sizing load cases on the underside of the wing in the iGREEN configuration

                    
.
 FEM of the iGREEN configuration
zum Bild FEM of the iGREEN configuration

Structural sizing is a further step in the aeroelastic design process. The objective is to dimension the structure with realistic component thicknesses on the basis of the loads that are determined for selected load conditions. This results in a stiffness distribution that is as realistic as possible and which takes other non-structural masses and mass distributions into account. Coupling of these factors results in a dynamic structural model for the aeroelastic analysis, or load analysis.

Sizing is usually carried out in MSC.NASTRAN. The modelling stage provides a finite element model without specified component wall thicknesses. On the basis of the loads catalogue, a small number of load conditions are selected, which are most relevant for structural sizing. These loads in particular, these include manoeuvring loads, can be calculated in MSC.NASTRAN., or they can be obtained from external analyses; for example, landing loads can be generated in the multi-body simulation.

A complete aircraft structure is sized from a large number of different load cases. This is illustrated with the example of the main areas on the underside of the wing of the iGREEN configuration in the image on the right. For this reason, careful selection of the load conditions that are used for sizing dimensioning is necessary.

After structural sizing of the components, a model of the entire aircraft is created. These models are provided to partners for static and dynamic investigations as ‘GFEM’ (Global FEM) models in the context of internal DLR projects, as well as for national and international projects.
 

Literature:

  • Klimmek, Thomas (2009)Parameterization of topology and geometry for the multidisciplinary optimization of wing structures. In: Proceedings "CEAS 2009". CEAS 2009 - European Air and Space Conference, 26-29 October 2009, Manchester, United Kingdom.
  • Krüger, Wolf R. and Klimmek, Thomas and Liepelt, René and Schmidt, Hauke and Waitz, Stefan and Cumnuantip, Sunpeth (2014)Design and aeroelastic assessment of a forward-swept wing aircraft. CEAS Aeronautical Journal. Springer Vienna. DOI: 10.1007/s13272-014-0117-0. ISSN 1869-5582.

 


Contact
Prof. Dr.-Ing. Wolf-Reiner Krüger
Head of Loads Analysis and Design

German Aerospace Center

Institute of Aeroelasticity

Göttingen

Tel.: +49 551 709-2808

Fax: +49 551 709-2862

Projekt iGREEN
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