Crack propagation is an important concern in the design of aircraft composite fuselage and wing panels. However, numerical simulation of crack propagation is computationally expensive. This work proposes combining high-fidelity analysis model with low-fidelity model to calculate the crack propagation constraint in the design optimization process. Correction response surfaces are employed to relate the high-fidelity models to the low-fidelity models. Four different forms of correction response surface methods are explored and their prediction capabilities are compared. The multi-fidelity approach is found to be more accurate than single-fidelity response surface method at the same computational cost.
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Received February 9, 2001
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Vitali, R., Haftka, R. & Sankar, B. Multi-fidelity design of stiffened composite panel with a crack. Struct Multidisc Optim 23, 347–356 (2002). https://doi.org/10.1007/s00158-002-0195-1
- Key words: correction response surface, response surface, approximations, crack propagation