The testing equipment for fuselage panels of aircrafts at the IMA GmbH Dresden is designed for fatigue tests as a preliminary stage to the full aircraft fatigue test. The natural disturbance at the boundaries of these panels is going to be minimized due to a well-adapted test rig design. The main advantage of this testing scenario lies in the lower testing effort and is therefore used to assess new design or material concepts. A numerical simulation of this process by means of a finite element (FE) analysis is the most important tool to model the actual setup and to adjust the loads in terms of a varying panel configuration.
The objective in this project is to extend the current testing strategy to panel configurations with an open set of geometrical parameters. The consideration of cut-outs or new materials as well as a new variety of fuselage diameters and non-circular cross-sections gets into focus. The results coming from these analyses can be used to draw conclusions for the loading situation of future detailed structure tests having refinement and sub-modelling strategies of an FE model in mind.
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References
L. le Tellier, F. Repiton (2007) In: Full-scale testing and analysis of Falcon 7X curved fuselage panels with Butt-joints, Proceedings of the 24th ICAF Symposium, vol. I, p. 340, L. Lazzeri and A. Salvetti (Ed.), Publ. Pacini, Naples
D. R. Ambur, J. A. Cerrof, J. Dickson (1995) In: D-Box Fixture for Testing Stiffened Panels in Compression and Pressure, AIAA Journal of Aircraft, vol. 32–6, p. 1382
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Ziegenhorn, M., Schulze, F., Sparr, H., Wenke, K., Fleischer, T. (2009). Simulation of the Stress Distribution on Fuselage Structures for the Pre- and Post Analyses of Curved Panel Tests. In: Bos, M.J. (eds) ICAF 2009, Bridging the Gap between Theory and Operational Practice. Springer, Dordrecht. https://doi.org/10.1007/978-90-481-2746-7_32
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