Optimum design of nozzle used in wide Mach Number

Bing Chen; Liang Xian Gu; Chun Lin Gong

doi:10.7673/j.issn.1006-2793.2013.06.010

Optimum design of nozzle used in wide Mach Number

Bing Chen, Liang Xian Gu, Chun Lin Gong

School of Astronautics

Northwestern Polytechnical University Xian

Research output: Contribution to journal › Article › peer-review

2 Scopus citations

Abstract

The surrogate models of thrust and lift coefficients were established by CFD. Single objective optimization was done by genetic algorithms at Mach 2.5, 5.0 and 8.0. The effect of geometry parameters on the performance of nozzle was analyzed by the optimum results. The multiobjective optimization on the nozzle was performed to obtain the optimum Pareto, and establish the objective function in all fly range by the weighting coefficient. The optimization results consider the thrust and lift performance in all velocity range, and the nozzle can work normally and efficiently in all fly range.

Original language	English
Pages (from-to)	758-762
Number of pages	5
Journal	Guti Huojian Jishu/Journal of Solid Rocket Technology
Volume	36
Issue number	6
DOIs	https://doi.org/10.7673/j.issn.1006-2793.2013.06.010
State	Published - Dec 2013

Keywords

Nozzle
Optimum design
Wide mach number

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10.7673/j.issn.1006-2793.2013.06.010

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title = "Optimum design of nozzle used in wide Mach Number",

abstract = "The surrogate models of thrust and lift coefficients were established by CFD. Single objective optimization was done by genetic algorithms at Mach 2.5, 5.0 and 8.0. The effect of geometry parameters on the performance of nozzle was analyzed by the optimum results. The multiobjective optimization on the nozzle was performed to obtain the optimum Pareto, and establish the objective function in all fly range by the weighting coefficient. The optimization results consider the thrust and lift performance in all velocity range, and the nozzle can work normally and efficiently in all fly range.",

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author = "Bing Chen and Gu, {Liang Xian} and Gong, {Chun Lin}",

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T1 - Optimum design of nozzle used in wide Mach Number

AU - Chen, Bing

AU - Gu, Liang Xian

AU - Gong, Chun Lin

PY - 2013/12

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N2 - The surrogate models of thrust and lift coefficients were established by CFD. Single objective optimization was done by genetic algorithms at Mach 2.5, 5.0 and 8.0. The effect of geometry parameters on the performance of nozzle was analyzed by the optimum results. The multiobjective optimization on the nozzle was performed to obtain the optimum Pareto, and establish the objective function in all fly range by the weighting coefficient. The optimization results consider the thrust and lift performance in all velocity range, and the nozzle can work normally and efficiently in all fly range.

AB - The surrogate models of thrust and lift coefficients were established by CFD. Single objective optimization was done by genetic algorithms at Mach 2.5, 5.0 and 8.0. The effect of geometry parameters on the performance of nozzle was analyzed by the optimum results. The multiobjective optimization on the nozzle was performed to obtain the optimum Pareto, and establish the objective function in all fly range by the weighting coefficient. The optimization results consider the thrust and lift performance in all velocity range, and the nozzle can work normally and efficiently in all fly range.

KW - Nozzle

KW - Optimum design

KW - Wide mach number

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JO - Guti Huojian Jishu/Journal of Solid Rocket Technology

JF - Guti Huojian Jishu/Journal of Solid Rocket Technology

IS - 6

ER -

Optimum design of nozzle used in wide Mach Number

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Keywords

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