Optimal Gas Generator Design for the Liquid Rocket Engine

Jeon, Kwon-Su; Lee, Jae Woo; Lee, Changjin; Chang, Jo Won

doi:10.2514/6.2004-32

Cited by 4 publications

(2 citation statements)

References 2 publications

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“…In aeronautical systems, propulsion has attracted much attention, and practical applications in optimizing the design of space systems, including its propulsion subsystems are emerging. 1,[5][6][7][8][9][10][11] In the last decade, several research works addressed multidisciplinary design optimization (MDO) of propulsion systems. For example, Son et al 12 used a genetic algorithm (GA) to optimize the gas generator and the combustion chamber of LPE, by considering the thermal requirements of the thrust chamber.…”

Section: Introductionmentioning

confidence: 99%

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%

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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show abstract

“…In the first approach, the design optimization is carried out through the space launch system. 3 2. In the second approach, the design optimization of the propulsion subsystem is carried out separately, considering the geometrical and operating requirements of the system.…”

Section: Introductionmentioning

confidence: 99%

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

2020

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The present paper strives for optimization of the cooling system of a liquid-propellant engine (LPE). To this end, the new synthetic metamodel methodology utilizing the design of experiment method and the response surface method was developed and im-How to cite this article: Alimohammadi HR, Naseh H, Ommi F. A new synthetic metamodel methodology for liquid-propellant engine's cooling system optimization.

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Development of Fuel Rich Gas Generator for 10 ton f Liquid Rocket Engine

Kwon

Lee

2004

40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

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Optimal Gas Generator Design for the Liquid Rocket Engine

Cited by 4 publications

References 2 publications

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

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

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

Development of Fuel Rich Gas Generator for 10 ton f Liquid Rocket Engine

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