Six sigma robust design optimization for thermal protection system of hypersonic vehicles based on successive response surface method

Zhu, Jingjing; Wang, Xiaojun; Zhang, Haiguo; Li, Yuwen; Wang, Ruixing; Qiu, Zhiping

doi:10.1016/j.cja.2019.04.009

Cited by 28 publications

(6 citation statements)

References 43 publications

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“…The SSP is deemed the best integration step for reliability to boost the optimal level of the SPO technique by improving the ribs' size for the triangular duct. So, this step includes finding the total chances of the ribs getting taller, reducing these chances using Central Composite Design (CCD), analyzing the results using Response Surface Methodology (RSM), and finally making the design better [89][90][91]. As depicted in Figure 11, the steps of the SSP path were followed depending on the proposed heights over 30 mm to enhance the vortices at the test section [92][93][94].…”

Section: Outcomes Of Investigation Stagementioning

confidence: 99%

Optimization of Laminar Flow in Non-Circular Ducts: A Comprehensive CFD Analysis

Hameed,

Mohammed,

Abbas

2023

JSE

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This study presents a detailed Computational fluid dynamics (CFD) analysis, focusing on optimizing laminar flow within non-circular ducts, specifically those with square, rectangular, and triangular configurations. The study centers on the effective use of mesh quality and size in these ducts, a factor which is previously underrepresented in those CFD studies that predominantly emphasized turbulent rather than laminar flows. With the help of finite element approach, this study compares the performance of these non-circular ducts, employing Reynolds numbers ranging from 1600 to 2000 and mesh sizes of 6, 12, and 18 mm. A ribbed duct style, arranged in a hybrid manner, is adopted to further this study. Analysis in this paper applied the Single predictive optimization (SPO) technique to the identification of the K-ε-Standard as the preferred viscosity model and a hybrid rib distribution as optimal within the triangular duct configuration. Parameters of a Reynolds number of 1600 and a mesh size of 18 mm emerged as the most effective values for this duct style. Then, the attained results of the Analysis of variance (ANOVA) indicated the F-Criterion's insignificance for Reynolds laminar levels, rendering the laminar viscosity model less relevant within the test section. Additionally, the implementation of the Six sigma procedure (SSP) markedly enhanced both the performance factor (PF) and turbulence intensity, which were observed at 4.90% and 146.77%, respectively. This improvement was most notable in the triangular duct, characterized by rib heights of 66 mm (semi-circle), 66 mm (rectangular), and 38.126 mm (triangular).

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Section: Outcomes Of Investigation Stagementioning

confidence: 99%

Optimization of Laminar Flow in Non-Circular Ducts: A Comprehensive CFD Analysis

Hameed,

Mohammed,

Abbas

2023

JSE

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“…Therefore, the convex model, based on interval mathematics, can serve as a powerful supplement to this part [29]. In order to predict the bounds of the response, some methods have been developed, such as the perturbation method [30], Taylor expansion method and gradient method [31], and response surface method [32]. Using the vertex method (VM), the exact solution will be obtained if the monotonicity of the function is guaranteed [33].…”

Section: Introductionmentioning

confidence: 99%

Size-Dependent Mechanical Behaviors of Defective FGM Nanobeam Subjected to Random Loading

2022

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Considering the uncertainties of the materials and loads, the nanobeam made of functionally graded materials were investigated based on the non-local elastic theory. The spline finite point method (SFPM) was established to analyze the bending behavior of the nanobeam-based Timoshenko theory. In comparison with finite element method (FEM), SFPM has higher accuracy. Further, the multi-source uncertainties are considered, material properties are quantified as interval parameters, and loads are taken as random parameters. To deal with the problems with two types of uncertainties coexisting, a hybrid uncertain analysis model was established, and the method of polynomial chaos expansion and dimensional wise (PCE–DW) analysis was proposed to predict the response of nanobeam in the hybrid uncertain system. Numerical examples ultimately illustrate the effectiveness of the model and solution techniques, compared with MCS. The results furtherly verify the efficiency and accuracy.

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“…Procedures for robust design have been investigated in the literature. For example, Response Surface Methodology was incorporated with the compromise Decision Support Problem 2 . Robust design methods such as the Taguchi design method are widely used and involve evaluating the parameters to be designed, designing the parameters using an orthogonal array, and performing analysis of variance using ANOVA and signal to noise ratios 3 .…”

Section: Introductionmentioning

confidence: 99%

Robust design of a multirotor aerial vehicle

Dutta

2021

Sci Rep

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This paper introduces the methodology of systematic robust design of a multirotor vehicle as an example of how to carry out the robust design of a physical system. Robustness in aerial vehicles is highly desirable as it guarantees a desired level of performance even under environmental uncertainties. Thus far, robustness has been considered in terms of active control in the space of multirotor vehicles, but exploration of the design space itself is lacking. In this work, a conceptual design followed by a robust design is performed to come up with the specifications that lead to least uncertain performance of the multirotor vehicle with respect to stochastic wind disturbances.

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Six sigma robust design optimization for thermal protection system of hypersonic vehicles based on successive response surface method

Cited by 28 publications

References 43 publications

Optimization of Laminar Flow in Non-Circular Ducts: A Comprehensive CFD Analysis

Optimization of Laminar Flow in Non-Circular Ducts: A Comprehensive CFD Analysis

Size-Dependent Mechanical Behaviors of Defective FGM Nanobeam Subjected to Random Loading

Robust design of a multirotor aerial vehicle

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