DGLR-Publikationsdatenbank - Detailansicht
Autor(en):
K. Bramsiepe, M. Herberhold, A. Voß
Zusammenfassung:
Background: For the preliminary aircraft design, the loads of a configuration have to be analyzed for several load cases and the structure is optimized for minimum weight. The load selection between the load analysis and the structural optimization determines the calculation time. The less critical load cases are identified, the faster is the optimization. Objective: Thus, a new method is tested at a conventional tail-aft configuration in order to investigate the reduction of critical load cases towards the final result and the computational effort. Method: The new method based on finite elements calculates the failure indices for each element for each load case. The highest failure index of an element identifies the critical load case. Simulation Model: To analyze the new method on a conventional tail-aft aircraft, the XRF1-DLR-C is utilized. It is a full composite FE-model which was developed from the data set of the XRF1 of Airbus. Results: The identified load cases and the calculation time are reduced while the results change only marginally.
Veranstaltung:
Deutscher Luft- und Raumfahrtkongress 2021
Verlag, Ort:
Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn, 2021
Medientyp:
Conference Paper
Sprache:
englisch
Format:
21,0 x 29,7 cm, 7 Seiten
URN:
urn:nbn:de:101:1-2021111211313780686136
DOI:
10.25967/550237
Stichworte zum Inhalt:
Lastauswahl, Strukturoptimierung
Verfügbarkeit:
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Kommentar:
Zitierform:
Bramsiepe, K.; Herberhold, M.; Voß, A. (2021): Aeroelastic Load Selection based on Elements Indices. Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V.. (Text). https://doi.org/10.25967/550237. urn:nbn:de:101:1-2021111211313780686136.
Veröffentlicht am:
12.11.2021