Reliability-based design optimization of composite and steel aerospace structures

d’Ippolito, Roberto; Donders, Stijn; Hack, Michael; Tzannetakis, Nick; Linden, Geert Van Der; Vandepitte, Dirk

doi:10.2514/6.2006-2153

Cited by 5 publications

(1 citation statement)

References 6 publications

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“…However, it is well known that there are inherent uncertainties that might cause real aircraft performance to deviate and lead to the impracticality of a design based on conventional approaches [4,25]. To alleviate the effect of uncertainty in the process of aircraft design, reliability-based design optimization (RBDO) has been proposed [26]. The uncertainty quantification is integrated into the optimization process to analyze the reliability or failure probability of the design structure.…”

Section: Introductionmentioning

confidence: 99%

Multi-Objective Reliability-Based Partial Topology Optimization of a Composite Aircraft Wing

2023

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Reliability-based partial topology optimization (RBPTO) is a new approach for aircraft structural design; however, it brings computational complexity and makes aeroelasticity analysis quite challenging. Therefore, the present study proposed the multi-objective reliability-based partial topology optimization of a composite aircraft wing using a fuzzy-based metaheuristic (MRBPTOFBMH) approach. The objective is to obtain an optimal layout including partial topology and sizing of the aircraft wing structure. Here, an optimal aeroelastic structure is designed by taking into account the uncertain nature of material properties and the permitted transverse displacement. To increase computational efficiency in the design process, a non-probabilistic approach called a possibilistic safety index-based design optimization (PSIBDO) with fuzzy uncertainties is proposed to quantify the uncertainties due to aeroelastic and structural constraints. Various optimum partial topological shapes and sizing of aircraft wing structures with various PSI values in the range of [0.001, 1.0] have been obtained in a single optimization run. These outcomes, including deterministic and reliable optimal aircraft wing structures, demonstrate the high effectiveness of the proposed MRBPTOFBMH technique to alleviate the complexity of unconventional aircraft wing structure design. The findings also reveal the ease in cooperation of the suggested technique with a high-performance multi-objective evolutionary algorithm (MOEA) and its application in real-world multi-objective design optimization (MODO) problems with the least computational requirements against the traditional method’s multiple runs. Furthermore, the proposed methodology can generate potential aircraft wing structures in a range of m = [89.38–127.84] kg, and flutter speed = [285.61–632.78] m/s, that adhere to all the constraints requirements.

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Section: Introductionmentioning

confidence: 99%