3564. Multi-Fidelity Wing Mass Estimations Based On A Central Model Approach

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Title3564. Multi-Fidelity Wing Mass Estimations Based On A Central Model Approach
Publication TypeConference Paper
Paper Number3564
Year of Publication2012
AuthorsBöhnke, Daniel, Dorbath Felix, Nagel Björn, and Gollnick Volker
Conference71st Annual Conference, Bad Gögging, Germany
Conference LocationBad Gögging, Germany
PublisherSociety of Allied Weight Engineers, Inc.
Date Published05/2012
Abstract

Although computational power is constantly increasing and Moore’s Law is still not falsified, computational cost remains an essential barrier in aircraft design especially when a high number of design evaluations is necessary. This is especially true at the conceptual design stage of aircraft. While determining the characteristics of a new configuration the number of iterations and the low level of detail in the available data limit the analyses to simple empiric methods.
Nevertheless, at a later point in the design it is necessary to determine parameters like the wing mass with higher-fidelity analysis modules. Especially when assessing configurations that lie outside of the well-known design space of conceptual design, empiric methods become unreliable. Examples to name include high aspect ratio and forward-swept wings.
In this study a combination of an empiric method, a beam model and vortex lattice model for aerodynamic loads is introduced. While multi-fidelity approaches are already well known, this study focuses on the fact that all analysis modules derive their data from the same data model. Working on a central data model decreases the number of required interfaces and guarantees that all models relate to the same input data, i.e. a compliant geometry definition.
This paper includes a design chain starting from the conceptual design tool VAMPzero as initiator for the more advanced models PESTwing and TRIMvl. Using the PESTwing tool a large design space will be explored. An equation for determination of the wing mass based on a physical model is then derived and compared to existing methods in conceptual design.

Pages18
Key Words11. Weight Engineering - Aircraft Estimation, 23. Weight Engineering - Structural Estimation
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