A new synthetic metamodel methodology for liquid‐propellant engine's cooling system optimization

Alimohammadi, H R; Naseh, Hassan; Ommi, Fathollah

doi:10.1002/htj.21911

Cited by 4 publications

(2 citation statements)

References 30 publications

(29 reference statements)

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“…For example, Way and Olds 1 have proposed a web-based code to enhance the simulation of the propulsion systems. Alimohammadi et al 2 used synthetic meta-model methodology utilizing the design of experiment (DOE) method for the optimization of the cooling system. Lee et al 3 considered specific impulse and thrust-to-weight ratio as target functions and tried to improve the engine performance.…”

Section: Introductionmentioning

confidence: 99%

“…Yaqun et al 14 proposed a method for evaluating the reliability of thrust chambers and quantifying the geometric dimensions and properties of materials for chamber reliability. Mohammad Zadeh et al 15 introduced a mass-based hybrid GA and SQP 2 optimization model to enhance the performance parameters of the space propulsion systems. Actually, in this hybrid optimization model, a global optimization algorithm (GA) together with a local algorithm (SQL) starts to solve the problem from the data obtained by the GA. Wanying et al 16 employed parameter global reliability sensitivity analysis with meta-models: A probability estimation-driven approach.…”

Section: Introductionmentioning

confidence: 99%

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Multi-objective multidisciplinary design optimization of liquid-propellant engines thrust chamber based on a surrogate model

Alimohammadi,

Aghaei-Togh

2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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The design of liquid-propellant engines (LPEs) has several challenges in setting the performance parameters. Accordingly, optimizing the design of a thrust chamber is of considerable importance that has been considered in several research projects. Previous research has focused on multidisciplinary design optimization (MDO). However, despite these efforts, the main issues remain. The present paper proposes a multi-objective multidisciplinary design optimization based on an efficient adaptive surrogate model of the thrust chamber to address these issues. The proposed method introduces a practical multidisciplinary optimization method based on an adaptive surrogate model that uses the moving least squares methodology, CCM, sensitivity analysis, and the elite multi-objective genetic algorithm (NSGAII). Due to the high importance of specific impulse and thrust-to-weight ratio, these two functions were used as target functions and in the NSGAII framework, the Pareto frontier was drawn for them. The proposed method is applied to a thrust-chamber engine test case. The results show that the target performance of the engine is improved, the specific impulse value is increased by 3.4 s, and the thrust-to-weight ratio is increased by 4%. These values represent significant advances in LPE engine design. The results obtained in this study indicate the potential of the proposed method in solving large-scale thrust-chamber design optimization problems.

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Section: Introductionmentioning

confidence: 99%