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

Abstract

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.

Surrogate metamodels from digital image correlation for testing high-performance composite vessels

“…The application of numerical methods in combination with the different PDF will allow to obtain the failure probability of the system, thus achieving more reliable designs and avoiding the use of such a wide range of properties, hence the importance of a correct adjustment of the distribution. The FEM is a very useful tool that allows the integration of the probabilistic distribution of the variables of this type of material with more advanced engineering design tools such as robust engineering [ 14 , 17 , 18 ], the most suitable for design for materials being the one known as Reliability Based-Design Optimization (RBDO) [ [19] , [20] , [21] ]. This integration makes it possible to move from a deterministic FEM to stochastic FEM [ [22] , [23] , [24] ], which is a numerical model that allows the calculation of mechanical stresses and strains under real stresses, providing a complete study of results and considering the uncertainty that affects the input variables [ 25 ].…”

Flutter Optimization of Large Swept-Back Tri-Wing Flight Vehicles

“…According to the current survey, some scholars have studied multi-objective optimization methods to analyse the flutter of wing structures and composite wings. Sleesongsom et al [19,20] aimed to reduce the solution complexity in the multi-objective reliability-based design optimization (MORBDO) of an aircraft wing structure, which is a symmetrical part of the aircraft structure. They proposed the multi-objective reliability-based partial topology optimization of a composite aircraft wing using a fuzzy-based metaheuristic (MRBPTOFBMH) approach.…”