Ensemble of four metaheuristic using a weighted sum technique for aircraft wing design

Recently, metaheuristics (MHs) have become increasingly popular in real-world engineering applications such as in the design of airframes structures and aeroelastic designs owing to its simple, flexible, and efficient nature. In this study, a novel hybrid algorithm is termed as Ensemble of Genetic algorithm, Grey wolf optimizer, Water cycle algorithm and Population base increment learningusing Weighted sum (E-GGWP-W), based on the successive archive methodology of the weighted population has been proposed to solve the aircraft composite wing design problem. Four distinguished algorithms viz. a Genetic algorithm (GA), a Grey wolf optimizer (GWO), a Water cycle algorithm (WCA), and Population base increment learning (PBIL) were used as ingredients of the proposed algorithm. The considered wing design problem is posed for overall weight minimization subject to several aeroelastic and structural constraints along with multiple discrete design variables to ascertain its viability for real-world applications. The algorithms are validated through the standard test functions of the CEC-RW-2020 test suite and composite Goland wing aeroelastic optimization. To check the performance, the proposed algorithm is contrasted with eight well established and newly developed MHs. Finally, a statistical analysis is done by performing Friedman’s rank test and allocating respective ranks to the algorithms. Based on the outcome, ithas been observed that the suggested algorithm outperforms the others

Study of Brake Pad Shim Modification to Improve Stability Against High Frequency Squeal Noise by Finite Element Analysis

This research studying on brake pad shim design with 4 configurations to improve the brake squeal noise phenomenon for high frequency noise in the range of 4-16 kHz. Various shims were designed with different configurations to increase structural damping and avoid instabilities in a brake system, which arise from friction drawing the vibration modes to coalesce between brake disc and brake pads. Then, the suspect brake module was tested in the laboratory using a dynamometer machine to confirm brake frequency noise parameters and conditions. The numerical models including brake disc, brake pad and brake pad shim were created using finite elements software and the unstable modes analysed for negative damping and positive real part values with the Complex Eigenvalue Analysis (CEA) technique. The simulation result showed that the instability of the brake system comes from mode coupling of the brake disc and brake pads in the out-of-plane modes (11ND) and (2 ND), respectively. The brake pads shim design1, design2 and design3 are component which goes in between the calipers and brake pads, were able to avoid high frequency brake squeal but make the noise move toward the direction of the lower frequency. The brake pad shim design4 is the good structure modification to avoid high frequency brake squeal and low frequency

Automated design of aircraft fuselage stiffeners using multiobjective evolutionary optimisation

This paper proposes an optimisation process for the design of aircraft fuselage stiffeners using evolutionary optimisation. A new design problem is developed to find a layout for fuselage stiffeners (rings and stringers) such that the structural mass, compliance, and the first-mode natural frequency can be optimised, subject to structural constraints. The stiffeners are modelled as beam elements. Three multiobjective meta-heuristics are employed to solve the problem, and a comparative study of the results of these optimisers is carried out. It is found that the proposed layout synthesis problem for aircraft fuselage stiffeners leads to a set of efficient structural solutions, which can be used at the decision-making stage. It is an automated design strategy with high potential for further investigation.Thailand Research Fund (RTA6180010