Application of immersed boundary method with wall injection for solid rocket motor internal flow

Takuya Hirose; Shinichiro Ogawa; Daisuke Sasaki; Yuma Fukushima; Shigeru Obayashi

Application of immersed boundary method with wall injection for solid rocket motor internal flow

Takuya Hirose, Shinichiro Ogawa, Daisuke Sasaki, Yuma Fukushima, Shigeru Obayashi

Creative Flow Research Division

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

1 Citation (Scopus)

Abstract

The vortex shedding in combustion chamber of solid rocket motor may lead the pressure oscillations, which deteriorates the rocket motor performance and could even damage the payload. Cartesian mesh CFD solver is expected to accurately predict such vortex flows using higher-order scheme and to treat complicated configurations easily. Therefore, blockstructured Cartesian mesh solver, Building-Cube Method (BCM), is applied to Taylor flow analysis, which is the simplified combustion chamber model of solid rocket. Immersed boundary method is extended to treat the wall injection from the grain surface. The approach is also applied to real grain configuration, and the usefulness for the complicated geometry is validated.

Original language	English
Title of host publication	AIAA Modeling and Simulation Technologies Conference, 2017
Publisher	American Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)	9781624104510
Publication status	Published - 2017 Jan 1
Event	AIAA Modeling and Simulation Technologies Conference, 2017 - Grapevine, United States Duration: 2017 Jan 9 → 2017 Jan 13

Publication series

Name	AIAA Modeling and Simulation Technologies Conference, 2017

Other

Other	AIAA Modeling and Simulation Technologies Conference, 2017
Country/Territory	United States
City	Grapevine
Period	17/1/9 → 17/1/13

ASJC Scopus subject areas

Aerospace Engineering
Modelling and Simulation

Cite this

Application of immersed boundary method with wall injection for solid rocket motor internal flow. / Hirose, Takuya; Ogawa, Shinichiro; Sasaki, Daisuke; Fukushima, Yuma; Obayashi, Shigeru.

AIAA Modeling and Simulation Technologies Conference, 2017. American Institute of Aeronautics and Astronautics Inc, AIAA, 2017. (AIAA Modeling and Simulation Technologies Conference, 2017).

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

Hirose, T, Ogawa, S, Sasaki, D, Fukushima, Y & Obayashi, S 2017, Application of immersed boundary method with wall injection for solid rocket motor internal flow. in AIAA Modeling and Simulation Technologies Conference, 2017. AIAA Modeling and Simulation Technologies Conference, 2017, American Institute of Aeronautics and Astronautics Inc, AIAA, AIAA Modeling and Simulation Technologies Conference, 2017, Grapevine, United States, 17/1/9.

Hirose, Takuya ; Ogawa, Shinichiro ; Sasaki, Daisuke ; Fukushima, Yuma ; Obayashi, Shigeru. / Application of immersed boundary method with wall injection for solid rocket motor internal flow. AIAA Modeling and Simulation Technologies Conference, 2017. American Institute of Aeronautics and Astronautics Inc, AIAA, 2017. (AIAA Modeling and Simulation Technologies Conference, 2017).

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title = "Application of immersed boundary method with wall injection for solid rocket motor internal flow",

abstract = "The vortex shedding in combustion chamber of solid rocket motor may lead the pressure oscillations, which deteriorates the rocket motor performance and could even damage the payload. Cartesian mesh CFD solver is expected to accurately predict such vortex flows using higher-order scheme and to treat complicated configurations easily. Therefore, blockstructured Cartesian mesh solver, Building-Cube Method (BCM), is applied to Taylor flow analysis, which is the simplified combustion chamber model of solid rocket. Immersed boundary method is extended to treat the wall injection from the grain surface. The approach is also applied to real grain configuration, and the usefulness for the complicated geometry is validated.",

author = "Takuya Hirose and Shinichiro Ogawa and Daisuke Sasaki and Yuma Fukushima and Shigeru Obayashi",

year = "2017",

month = jan,

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language = "English",

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series = "AIAA Modeling and Simulation Technologies Conference, 2017",

publisher = "American Institute of Aeronautics and Astronautics Inc, AIAA",

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note = "AIAA Modeling and Simulation Technologies Conference, 2017 ; Conference date: 09-01-2017 Through 13-01-2017",

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AU - Hirose, Takuya

AU - Ogawa, Shinichiro

AU - Sasaki, Daisuke

AU - Fukushima, Yuma

AU - Obayashi, Shigeru

PY - 2017/1/1

Y1 - 2017/1/1

N2 - The vortex shedding in combustion chamber of solid rocket motor may lead the pressure oscillations, which deteriorates the rocket motor performance and could even damage the payload. Cartesian mesh CFD solver is expected to accurately predict such vortex flows using higher-order scheme and to treat complicated configurations easily. Therefore, blockstructured Cartesian mesh solver, Building-Cube Method (BCM), is applied to Taylor flow analysis, which is the simplified combustion chamber model of solid rocket. Immersed boundary method is extended to treat the wall injection from the grain surface. The approach is also applied to real grain configuration, and the usefulness for the complicated geometry is validated.

AB - The vortex shedding in combustion chamber of solid rocket motor may lead the pressure oscillations, which deteriorates the rocket motor performance and could even damage the payload. Cartesian mesh CFD solver is expected to accurately predict such vortex flows using higher-order scheme and to treat complicated configurations easily. Therefore, blockstructured Cartesian mesh solver, Building-Cube Method (BCM), is applied to Taylor flow analysis, which is the simplified combustion chamber model of solid rocket. Immersed boundary method is extended to treat the wall injection from the grain surface. The approach is also applied to real grain configuration, and the usefulness for the complicated geometry is validated.

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M3 - Conference contribution

SN - 9781624104510

T3 - AIAA Modeling and Simulation Technologies Conference, 2017

BT - AIAA Modeling and Simulation Technologies Conference, 2017

PB - American Institute of Aeronautics and Astronautics Inc, AIAA

T2 - AIAA Modeling and Simulation Technologies Conference, 2017

Y2 - 9 January 2017 through 13 January 2017

ER -

Application of immersed boundary method with wall injection for solid rocket motor internal flow

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