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Es wurde eine multidisziplinäre Toolkette für die Flügelmassenabschätzung in frühen Entwurfsphasen entwickelt. Neben der Flügelprimärstruktur enthält das FE Model die Klappen inklusive Klappenführungsmechanismen, die Querruder, das Fahrwerk und den Triebwerkspylon. The Toolkette enthält Module für die Strukturanalyse und -dimensionierung, sowie die Abschätzung der Aerodynamik-, Treibstoff-, Fahrwerks- und Triebwerkslasten. Die Toolkette wurde anhand zweier Referenzflugzeuge kalibriert. Die Kalibrierung zeigt die hohe Genauigkeit des gewählten Ansatzes., A multidisciplinary tool chain for wing mass estimation for early design stages is presented. Beside the wing primary structure, the structural FE model includes flaps and tracks, ailerons, landing gears and engine pylons. The chain includes the structural analysis and sizing capability and models for aerodynamic, fuel, landing gear and engine loads. The chain is calibrated against two reference aircraft. The calibration shows the high accuracy of the extended physical modeling.

This paper introduces a fully parameterized finite element based tool chain for the structural sizing of transport aircraft. The chain consists of two model generators, a coupling module, a loads module for the computation of aerodynamic, fuel, landing gear and engine loads as well as a structural analysis and sizing algorithm. The finite element models of the wing and the empennage are created by the ELWIS multi-model generator, while the corresponding fuselage model is created using the TRAFUMO model generator. The structural coupling comprises the detailed modeling of all key structural elements of the center fuselage area including a keelbeam, bulkheads, sideboxes and lateral panels. The empennage coupling structure includes a reinforcement framework, reinforced frames and a mounting structure for the horizontal tail plane trim device. To establish suitability in preliminary aircraft design, a knowledge-based approach is chosen that enables a fully automatic model generation and coupling on a minimum set of required input parameters. As a central data format for input and output the DLR aircraft parameterization format CPACS is used. Therefore, the chain can be easily embedded in a wider MDA/MDO approach for overall preliminary aircraft design. Finally, first static sizing results are discussed and different validation methods for the static sizing algorithm are presented, including a comparison with a validated analytical method.

This paper presents a comparison between the beam and shell theory for the application on wing box mass estimation in preliminary aircraft wing design. At first, the difference between the two theories in bending, in twist around the beam axis and in twist in flight direction is analyzed for a range of different wing geometries and load cases. In addition the differences in local and integral values of the x-normal, y-normal, xy-shear and von Mises stress are analyzed. Afterwards, certain geometries are selected and a realistic aerodynamic load is applied. For those wings a sizing of the skin and spar thickness is performed using both, the beam and shell theory. The sizing is performed with constant aerodynamic loads as well as with aeroelastic loads. Finally, explanatory statements for the differences in mass estimation and for different aeroelastic behaviour between both theories are discussed.