scholarly journals Local Structural Optimization Method Based on Orthogonal Analysis for a Resistant Muffler

IEEE Access ◽  
2021 ◽  
Vol 9 ◽  
pp. 40560-40569
Author(s):  
Rui Li ◽  
Yiqi Zhou ◽  
Yuan Xue ◽  
Su Han
2014 ◽  
Vol 496-500 ◽  
pp. 429-435
Author(s):  
Xiao Ping Zhong ◽  
Peng Jin

Firstly, a two-level optimization procedure for composite structure is investigated with lamination parameters as design variables and MSC.Nastran as analysis tool. The details using lamination parameters as MSC.Nastran input parameters are presented. Secondly, with a proper equivalent stiffness laminate built to substitute for the lamination parameters, a two-level optimization method based on the equivalent stiffness laminate is proposed. Compared with the lamination parameters-based method, the layer thicknesses of the equivalent stiffness laminate are adopted as continuous design variables at the first level. The corresponding lamination parameters are calculated from the optimal layer thicknesses. At the second level, genetic algorithm (GA) is applied to identify an optimal laminate configuration to target the lamination parameters obtained. The numerical example shows that the proposed method without considering constraints of lamination parameters can obtain better optimal results.


2010 ◽  
Vol 83 (12) ◽  
pp. 1580-1624 ◽  
Author(s):  
Shintaro Yamasaki ◽  
Shinji Nishiwaki ◽  
Takayuki Yamada ◽  
Kazuhiro Izui ◽  
Masataka Yoshimura

2013 ◽  
Vol 341-342 ◽  
pp. 519-523
Author(s):  
Ya Hui Zhang ◽  
Ji Hong Zhu ◽  
Jun Shuo Li ◽  
Wei Hong Zhang

The problem of metal-composite wing structural optimization is discussed and a strategy is presented. Topology optimization method is applied to provide load transferring path of structure for concept design. Size, shape and other optimization method are used to provide detailed design for individual components. A three-phase optimization method is discussed for fiber reinforced composite laminate skin. Optimal parameters include ply angle, percentage, thickness, layer shape and sequence. The design of laminate for ease of manufacture is based on a set of manufacturing constraints. This paper deals with a total optimal design solution for aileron structure of an aircraft. The result satisfies all the requirements of strength and stability, and has obvious effect of weight loss.


Energies ◽  
2018 ◽  
Vol 11 (11) ◽  
pp. 3230 ◽  
Author(s):  
Puyang Zhang ◽  
Yunlong Xu ◽  
Conghuan Le ◽  
Hongyan Ding ◽  
Yaohua Guo

A two-step structural optimization method was proposed to select the transition section of a composite bucket foundation (CBF). In the first step, based on the variable density method, a solid isotropic microstructures with penalization (SIMP) interpolation model was established under specific load conditions and boundary conditions. The solution of force transmission path and the topology of the transition section in six forms (e.g., linear, arc-shaped, linear thin-walled, and arc-shaped thin-walled) were optimized. Afterwards, finite element software ABAQUS was used to verify this model. Results show that the utilization rate of the arc-shaped thin-walled structure was the largest, and its basic transmission force was more straightforward together with smaller cross-section size at the same height and smaller influence on spoiler flow. In the second step, the detailed optimization of CBF was carried out using mathematical programming. Under the premise of minimum total construction cost, the body shape parameters of each part were set as design variables satisfying the corresponding strength, stiffness, and stability conditions; meanwhile, the minimum total structure weight was set as the objective function. MATLAB was used to solve the sequence quadratic programming (SQP) algorithm and hybrid genetic algorithm, and the optimal body parameters were obtained.


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