29 research outputs found
Fluid-Structure-Combustion Interaction Simulation for Solid Propellant Rocket Interior Phenomena
๊ณ ์ฒด ๋ก์ผ ๋ด๋ถ ํ์ ์ ์ฐ ํด์์ ์ํด ๊ธฐ์กด ์ด๋ ๊ธฐ์ ๋ฐฉ๋ฒ๋ค์ ์ฅ์ ์ ๊ฒฐํฉํ ALE ๊ธฐ๋ฒ์ ๋์
ํ์ฌ ์ ์ฒด ๊ตฌ์กฐ ์ฐ๋ ํด์์ ์ํํ์๋ค. ์ด๋ฅผ ์ํด ๊ฐ๋ณ ํด์ ์์(์ ๋, ๊ตฌ์กฐ, ์ฐ์)์ธ์ ํตํฉ ๊ธฐ๋ฒ๋ค๊ณผ ๋ณํํ๋ ํด์ ์์ญ์ ๋ํ ์๋ ๊ฒฉ์ ์์ฑ ๊ธฐ๋ฒ์ด ์ฐ๊ตฌ๋์๋ค. ๊ฐ๋ฐ๋ ํด์ ํ๋ก๊ทธ๋จ์ ์ด์ฉํ์ฌ ๊ณ ์ฒด ์ถ์ง ๋ก์ผ์ ์ ํ๊ณผ์ ๋ถํฐ ๋๋ถ๋ถ์ ์ฐ๋ฃ๊ฐ ์์ง๋๋ ์์ ๊น์ง์ ์ ์ฐ ํด์์ด ์ํ๋์์ผ๋ฉฐ ์ด๋ฅผ ํตํ์ฌ ์ฐ์์ค ๋ด๋ถ์ ์ ๋ ๋ฌผ๋ฆฌ ํ์๊ณผ ์ถ์ง์ ๊ทธ๋ ์ธ์ ๋ณํ ํน์ฑ์ ๊ด์ฐฐํ์๋ค.A fluid-structure interaction simulation of solid propellant rocket interior is carried out by employing the ALE (Arbitrary Lagrangian Eulerian) description, a hybrid model of continuum motion description combining the advantages of classical Lagrangian and Eulerian description. The integration process for fluid-structure interaction and an automatic re-meshing algorithm are included to analyze an unsteady fluid-structure interaction phenomenon with the deformation of solid grain during the simulation. The developed solver is applied for the full burning simulation of a solid propellant grain, which is a highly-coupled unsteady phenomenon between gas flow and propellant structure. Based on the integrated computed results, flow physics in the combustion chamber and the behavior of a solid propellant deformation are examined.๋ณธ ์ฐ๊ตฌ๋ ๊ต์ก๊ณผํ๊ธฐ์ ๋ถ์ ์ฐ์ฃผ๊ธฐ์ด์์ฒ๊ธฐ์
๊ฐ๋ฐ ์ฌ์
(NSL, National Space Lab, No. 2011-
0029871)๊ณผ ๊ตญํ ํด์๋ถ ๊ฑด์ค๊ธฐ์ ํ์ ์ฌ์
์ด์ฅ๋
๊ต๋์ฌ์
๋จ(08 ๊ธฐ์ ํ์ E01)์ ์ง์์ ๋ฐ์ ์ด๋ฃจ์ด์ก์.OAIID:oai:osos.snu.ac.kr:snu2012-01/104/0000004648/14SEQ:14PERF_CD:SNU2012-01EVAL_ITEM_CD:104USER_ID:0000004648ADJUST_YN:NEMP_ID:A001138DEPT_CD:446CITE_RATE:0FILENAME:๊ณ ์ฒด_๋ก์ผ_์ฐ์์ค_๋ด๋ถ์_๋ํ_FScI_ํด์.pdfDEPT_NM:๊ธฐ๊ณํญ๊ณต๊ณตํ๋ถEMAIL:[email protected]:
The study of data transfer method between non-matching meshes interface using common-refinement method for fluid-structure interaction
๋ณธ ์ฐ๊ตฌ๋ ์ ์ฒด-๊ณ ์ฒด ์ฐ์ฑ ํด์์ด ํ๋ฐํ ์งํ๋๊ณ ์๋ ๊ณ ์ฒด๋ก์ผ์ 3์ฐจ์ ์ฐ์์ค ์๊ฒฝ๊ณ๋ฉด ํ์์ ๋ํด ์ ๋ณด ์ ๋ฌ ๊ธฐ๋ฒ ์ค ํ๋์ธ common-refinement ๊ธฐ๋ฒ์ ์ ์ฉ์ ๋ชฉ์ ์ผ๋ก ์ํ๋์๋ค. ๊ธฐ๋ฒ ๊ตฌํ์ ์๊ฒฝ๊ณ๋ฉด์ common surface๋ฅผ ๊ตฌ์ฑํ๊ณ ํน์ error norm์ ์ต์ํ ์ํค๋ minimization ๋ด์ฝ๋ฒ์ ์ ์ฉํ๋ ๊ณผ์ ์ผ๋ก ์ํ๋์๋ค. ์ด๋ฅผ ๋ฐํ์ผ๋ก ๋ค์ํ ๋ค์ฐจ์ ์๊ฒฝ๊ณ๋ฉด ํ์์์ ์ฐ์ ๋ฐ ๋ถ์ฐ์ ํจ์๋ฅผ ์ด์ฉํ ์ ๋ณด ์ ๋ฌ ์คํ์ ์ํํ์๊ณ , ๋ค๋ฅธ ๊ธฐ๋ฒ๋ค๊ณผ ํด์ ๊ฒฐ๊ณผ๋ฅผ ๋น๊ตํ์๋ค.During multi-physics or multi-phase simulations accompanying fluid-structure thermal interaction, data transfer problems always arise along non-matching interfaces caused by different computational meshes for each physical domain. Common-refinement scheme, among many available methods, is attractive since it is known to yield conservative and accurate data transfer for non-matching interface cases. This is particularly important in simulating compressible unsteady fluid-structure thermal interaction inside solid propellant rockets, where grid size along solid-fluid interfaces is substantially different. From this perspective, we examine performances of common-refinement-based data transfer scheme between structured quadrilateral (structure part) and unstructured triangular (fluid part) meshes by comparing computed results with other data transfer methods.๋ณธ ์ฐ๊ตฌ๋ ๊ต์ก๊ณผํ๊ธฐ์ ๋ถ์ ์ฐ์ฃผ๊ธฐ์ด์์ฒ๊ธฐ์
๊ฐ๋ฐ ์ฌ์
(NSL, National Space Lab, No.
2011-0029871) ๋ฐ 2012๋
๋ ์ ๋ถ(๊ต์ก๊ณผํ๊ธฐ์ ๋ถ)
์ ์ฌ์์ผ๋ก ๊ตญ๊ฐ์๋ฆฌ๊ณผํ์ฐ๊ตฌ์์ ์ฃผ์์ฌ์
(No. A21001)์ผ๋ก๋ถํฐ ์ง์์ ๋ฐ์ ์ด๋ฃจ์ด์ก์OAIID:oai:osos.snu.ac.kr:snu2012-01/104/0000004648/35SEQ:35PERF_CD:SNU2012-01EVAL_ITEM_CD:104USER_ID:0000004648ADJUST_YN:NEMP_ID:A001138DEPT_CD:446CITE_RATE:0FILENAME:์ ์ฒด-๊ตฌ์กฐ_์ฐ์ฑ_ํด์์_์ํ_common-refinement_๊ธฐ๋ฐ_๋ถ์ผ์น_๊ฒฉ์_๊ฒฝ๊ณ๋ฉด์์์_์ ๋ณด_์ ๋ฌ_๊ธฐ๋ฒ_์ฐ๊ตฌ.pdfDEPT_NM:๊ธฐ๊ณํญ๊ณต๊ณตํ๋ถEMAIL:[email protected]:
Full burning ALE based Fluid-Structure-combustion Interaction simulation for solid propellant rocket interior
A fluid-structure interaction simulation of solid propellant rocket interior is carried out by employing the ALE (Arbitrary Lagrangian Eulerian) description, a hybrid model of continuum motion description combining the advantages of classical Lagrangian and Eulerian description. The integration process for fluid-structure interaction and an automatic re-meshing algorithm are included to analyze an unsteady fluid-structure interaction phenomenon with the deformation of solid grain during the simulation. The developed solver is applied for the full burning simulation of a solid propellant grain, which is a highly-coupled unsteady phenomenon between gas flow and propellant structure. Based on the integrated computed results, flow physics in the combustion chamber and the behavior of a solid propellant deformation are examined.OAIID:oai:osos.snu.ac.kr:snu2013-01/104/0000004648/3SEQ:3PERF_CD:SNU2013-01EVAL_ITEM_CD:104USER_ID:0000004648ADJUST_YN:NEMP_ID:A001138DEPT_CD:446CITE_RATE:0FILENAME:2013์ฐ์ฃผ๋ฐ์ฌ์ฒด๊ธฐ์ ์ฌํฌ์ง์_ํ์ํธ.pdfDEPT_NM:๊ธฐ๊ณํญ๊ณต๊ณตํ๋ถEMAIL:[email protected]:
The study of data transfer method non-matching meshes interface using common-refinement method for fluid-structure interface
๋ณธ ์ฐ๊ตฌ๋ ์ ์ฒด-๊ณ ์ฒด ์ฐ์ฑ ํด์์ด ํ๋ฐํ ์งํ๋๊ณ ์๋ ๊ณ ์ฒด๋ก์ผ์ 3์ฐจ์ ์ฐ์์ค ์๊ฒฝ๊ณ๋ฉด ํ์์ ๋ํด ์ ๋ณด ์ ๋ฌ ๊ธฐ๋ฒ ์ค ํ๋์ธ ๊ณตํต์ธ๋ถ ๊ธฐ๋ฒ์ ์ ์ฉ์ ๋ชฉ์ ์ผ๋ก ์ํ๋์๋ค. ๋ณธ ๊ธฐ๋ฒ์ ๋ถ์ผ์นํ๋ ๊ฒฝ๊ณ๋ฉด๊ฐ ์ ๋ณด ์ ๋ฌ์๋ ๋ณด์กด์ฑ๊ณผ ์ ํ๋๋ฅผ ๋์์ ๋ง์กฑ์ํฌ ์ ์๋ค๋ ์ฅ์ ์ ๊ฐ๋๋ค. ๊ธฐ๋ฒ ๊ตฌํ์ ์๊ฒฝ๊ณ๋ฉด์ ๊ณตํตํ๋ฉด์ ๊ตฌ์ฑํ๊ณ ํน์ ์ค์ฐจ๋ฅผ ์ต์ํ ์ํค๋ ์ต์ํ ๋ด์ฝ๋ฒ์ ์ ์ฉํ๋ ๊ณผ์ ์ผ๋ก ์ํ๋์๋ค. ์ด๋ฅผ ๋ฐํ์ผ๋ก ๋ค์ํ ๋ค์ฐจ์ ์๊ฒฝ๊ณ๋ฉด ํ์์์ ์ฐ์ ๋ฐ ๋ถ์ฐ์ ํจ์๋ฅผ ์ด์ฉํ ์ ๋ณด ์ ๋ฌ ์คํ์ ์ํํ์๊ณ , ๋ค๋ฅธ ๊ธฐ๋ฒ๋ค๊ณผ ํด์ ๊ฒฐ๊ณผ๋ฅผ ๋น๊ตํ์๋ค.During multi-physics or multi-phase simulations accompanying fluid- structure- thermal interaction, data transfer problems always arise along non- matching interfaces caused by different computational meshes for each physical domain. Common- refinement scheme, among many available methods, is attractive since it is known to yield conservative and accurate data transfer for non- matching interface cases. This is particularly important in simulating compressible unsteady fluid- structure- thermal interaction inside solid propellant rockets, where grid size along solid- fluid interfaces is substantially different. From this perspective, we examine performances of common- refinement- based data transfer scheme between structured quadrilateral (structure part) and unstructured triangular (fluid part) meshes by comparing computed results with other data transfer methodsOAIID:oai:osos.snu.ac.kr:snu2014-01/102/0000004648/1SEQ:1PERF_CD:SNU2014-01EVAL_ITEM_CD:102USER_ID:0000004648ADJUST_YN:YEMP_ID:A001138DEPT_CD:446CITE_RATE:0FILENAME:์ ์ฒด-๊ตฌ์กฐ_์ฐ์ฑ_ํด์์_์ํ_common-refinement_๊ธฐ๋ฐ_๋ถ์ผ์น_๊ฒฉ์_๊ฒฝ๊ณ๋ฉด์์์_์ ๋ณด_์ ๋ฌ_๊ธฐ๋ฒ_์ฐ๊ตฌ.pdfDEPT_NM:๊ธฐ๊ณํญ๊ณต๊ณตํ๋ถSCOPUS_YN:NCONFIRM:
ALE based Fluid-Structure-Interaction Simulation of Solid Propellant Rocket
The Arbitrary Lagrangian-Eulerian(ALE, in short) method is the new description of continum motion ,which combines the advantages of the classical kinematical descriptions, i.e. Lagrangian and Eulerian description, while minimizing their respective drawbacks. In this paper, the ALE description is adapted to simulate fluid-structure interaction problems. An automatic re-mesh algorithm and a fluid-structure coupling process are included to analyze the interaction and moving motion during the 2-D axisymmetric solid rocket interior FSI phenomena simulation.๋ณธ ๋
ผ๋ฌธ์ ์ ๋๊ณผ ๊ตฌ์กฐ๋ฌผ๊ฐ์ ์ํธ์์ฉ์ผ๋ก ์ธํด ์ ์ฒด๋ ๊ตฌ์กฐ, ํ ์ชฝ ๋ถ์ผ์์์ ์ ๊ทผ์ผ๋ก๋ ํ๊ณ๊ฐ ์๋ ๊ณ ์ฒด ๋ก์ผ ๋ด๋ถ ์ ๋-๊ตฌ์กฐ-์ฐ์ ๊ฒฐํฉ ๋ฌธ์ ๋ฅผ ํด๊ฒฐํ๊ธฐ ์ํด FSI๋ฅผ ์ด์ฉํ ์ ์ฐํด์์ ๋ชฉ์ ์ผ๋ก ํ๋ค. ALE(Arbitrary Lagrangian Eulerian) ๊ธฐ์ ๋ฐฉ์์ ๋์
ํ์ฌ ๊ณ์ฐ ๊ฒฉ์์ ์์ง์์ ํ์ฉํ๋ฉด์๋ ๊ฒฉ์์ ๋ํ ์ฐ์์ฒด ์
์์ ์๋์ด๋์ด ๊ฐ๋ฅํ๋๋ก ํ์๋ค. ์ ์ฒด ์์ญ์ ํด์ ํ๋ก๊ทธ๋จ์ 2์ฐจ์ ์์ถ์ฑ ๋น์ ์ ์ ๋ ํด์์ ์ํ ์ค์ผ๋ฌ ๋ฐฉ์ ์์ ALE ํํ๋ฅผ ๋ณํ์์ผ ์ ์ฉ ํ์๊ณ , ๊ณ ์ฒด ์์ญ์ ํด์ ํ๋ก๊ทธ๋จ์ ALE๋ฅผ ๊ณ ๋ คํ 2์ฐจ์ ๋์ ์ ํ ์์ ๋ฐฉ๋ฒ์ ์ฌ์ฉํ์๋ค.OAIID:oai:osos.snu.ac.kr:snu2009-01/104/0000004648/20SEQ:20PERF_CD:SNU2009-01EVAL_ITEM_CD:104USER_ID:0000004648ADJUST_YN:NEMP_ID:A001138DEPT_CD:446CITE_RATE:0FILENAME:๊ณ ์ฒด_๋ก์ผ_๋ด๋ถ_๊ทธ๋ ์ธ_์ ์ฒด-๊ตฌ์กฐ-์ฐ์_ํตํฉ_ํด์.pdfDEPT_NM:๊ธฐ๊ณํญ๊ณต๊ณตํ๋ถEMAIL:[email protected]:
๊ณ ์ฒด ๋ก์ผ ์ฐ์์ค ๋ด๋ถ ๋ณตํฉ ํ์์ ๋ํ ์ ์ฒด-๊ตฌ์กฐ ์ฐ์ฑ ํด์
ํ์๋
ผ๋ฌธ (๋ฐ์ฌ)-- ์์ธ๋ํ๊ต ๋ํ์ : ๊ธฐ๊ณํญ๊ณต๊ณตํ๋ถ, 2014. 2. ๊น์ข
์.The interior phenomena in solid rocket exhibit highly unsteady, multi-scale, and multi-physics features because fluid, structure, and combustion generates a non-linear feedback cycle by influencing one another inside the combustion chamber. In order to integrated fluid-structure-combustion simulation to understand the highly unsteady, multi-physics phenomena inside of solid rocket motor interior, fully integrated computational simulations inside solid propellant rocket are carried out to examine the nonlinear feedback interaction between fluid, structure and combustion module. The Arbitrary Lagrangian Eulerian (ALE) description is employed to efficiently tracking the burning process along grain surface. An automatic re-meshing algorithm is added to the FSbI process to accurately analyze unsteady fluid-structure coupling phenomena with deforming solid grain during simulation. The developed solver is then applied to the full-burning simulation of a solid propellant grain, which is a highly-coupled unsteady phenomenon between gas flow and propellant structure. Based on the integrated computed results, detailed ignition mechanism and flame propagation process along propellant grain surface are investigated. In particular, flame propagation delay and secondary burning phenomena are explained from the physical and numerical perspectives. Furthermore, virtual contact line method is introduced to overcome the boots contact problem occurring in the gas flow-propellant interaction, and the deforming behavior of full-burning solid propellant is examined.๊ณตํ๋ฐ์ฌ ํ์๋
ผ๋ฌธ
ABSTRACT
NOMENCLATURE
LIST OF TABLES
LIST OF FIGURES
CHAPTER I
INTRODUCTION 1
1.1 Fluid-structure simulation for solid rocket interior
1.2 Dissertation Objectives: A Summary
1.3 Outline of Dissertation
CHAPTER II
NUMERICAL METHOD I
2.1 The arbitrary Lagrangian-Eulerian method
2.2 Descriptions of motion
2.3 The fundamental ALE equation
2.4 The ALE forms of governing equations
CHAPTER III
NUMERICAL METHODS II
3.1 Fluid solver
3.2 Structural solver
3.3 Combustion solver
3.4 Spatial and temporal data transfer scheme
3.5 Dynamic mesh treatment
3.6 Surface regression model
3.7 Virtual contact line method
CHAPTER IV
SIMULATION RESULTS
4.1 Validation problem
4.2 Validation problem
4.3 Rocket modeling and thermal analysis
4.4 Rocket simulation results
CHAPTER V
CONCLUDING REMARKS & FUTURE WORKS
5.1 Concluding Remarks
5.2 Future work
APPENDIX
A1. Common refinement data transfer scheme for 3-D rocket
REFERENCES
๊ตญ๋ฌธ ์ด๋กDocto
flow analysis for interior part of solid propellant rocket using fluid-structure interaction
ํ์๋
ผ๋ฌธ(์์ฌ) --์์ธ๋ํ๊ต ๋ํ์ :๊ธฐ๊ณํญ๊ณต๊ณตํ๋ถ,2007.Maste
์ฌ๋ฒ๊ฐํ๊ณผ ๋ฒ์กฐ์์ฑ : ์ 2์ฃผ์ ๋ฐํ๋ ผ๋ฌธ ; ๋ฒ์กฐ์ง๋ฌด์ ๋ฒ์กฐ์ธ๊ตฌ / ์ 2์ฃผ์ ์ง์ ํ ๋ก -๋ฒ์กฐ์ธ์ ํ๋์์ญ๊ณผ ์ ์ ํ ๋ฒ์กฐ์ธ๊ตฌ
๋ฒํ๊ต์ก์ ๋ํ ์ธ๋ฏธ๋์ ์ฐธ์ํ๊ฒ ๋จ์ ๊ธฐ์๊ฒ ์๊ฐํฉ๋๋ค. ์ ๋ฐ์ ์ธ ํ ๋ก ์ ์ฐธ์ฌํ๋ ๊ณผ์ ์ค์์ ๋ณธ์ธ์๊ฒ๋ ๋ฒ์กฐ์ธ๊ตฌ์ ๊ดํ ์์ ๋ชฉ์ด ๋ถ์ฌ์ก์ต๋๋ค. ๊ทธ์ ๋ํ ์๊ธฐ๋ฅผ ํ๊ธฐ ์ํ์ฌ ๋ฒํ๊ต์ก ์ ๋ฐ์ ๊ฑธ์น ์๊ฐ, ์ฌ๋ฒ์ํ์ ๋, ๊ทธ๋ฆฌ๊ณ ๋ฒ์กฐ์ธ๊ตฌ๋ฅผ ์ฐจ๋ก๋ก ์ธ๊ธํ๊ณ ์ ํฉ๋๋ค.
๋ฒ์ ๋ํ ๊ตญ๋ฏผ์ ๊ฐ๋
์ ์์ง๋ ๋ฒ์ด๋ ๋ฐ๋์งํ ๋ชจ๋ธ ์ ๋์ผ ๊ฒ์
๋๋ค. ์งํค๊ธฐ๋ฅผ ํฌ๋งํ๋ ์ ๋์
๋๋ค. ๋ฐ๋ผ์ ๋ฒ์ ์๋ฐํ๋ค๋ ๊ฒ์ ์ด๋ ํฌ๋ง์ ์ธ ์ด์์ ํฌ๊ธฐํ๋ค๋ ๊ฒ ์ฏค์
๋๋ค. ๋ฐ๋ผ์ ๋ฒ์ ์๋ฐํ ๊ฒ์ด ์ฒ๋ฒ๋๋ ๊ฒ์ ๋ณด๋ ๊ฒ์ ๊ตญ๋ฏผ์ ๋์๋ ์์ง๋ ์ด์ํ ๊ฒ์
๋๋ค. ๊ฑด์ถ๋ฒ์ ์๋ฐํ๋ ํ์, ์ ๊ฑฐ๋ฒ์ ์๋ฐํ๋ ํ์, ๊ณต๋ฌด์์ด ๋๋ฌผ์ ์์ํ๋ ํ์ - ์ด ๋ชจ๋ ๊ฒ์ด ์ฒ๋ฒ๋๋ ๊ฒ์ด ์ด์ํ ๊ฒ์ผ๋ก ๋๊ปด์ง๋ ๋ฒ๋ฅ ๋ค์
๋๋ค. ๊ทธ๋ฌ๋ ์ธ์์ด ๋ณํ๊ณ ์์ต๋๋ค. ๋๋ก๊ตํต๋ฒ์ ์๋ฐํ๋ฉด ์ฒ๋ฒ๋๊ธฐ ์ ์ ์ฌ๋์ด ๋จผ์ ์ฃฝ์ด ๋ฒ๋ฆฝ๋๋ค. ๋นจ๊ฐ ์ ํธ๋ฅผ ๋ณด๊ณ ๋ ๋์ฌ์ง์์ ์ฐจ๊ฐ ์ง๋๊ฐ๋ฉด ๋ค๋ฅธ ์ฐจ๊ฐ ์์ ์ถฉ๋ํ์ฌ ์ฌ๋์ด ๋ค์น๋ ์ฌ๊ณ ๊ฐ ๋ฐ์ํฉ๋๋ค. ๋ฒ์ ๋ ์ด์ ๋ชจ๋ธ์ด ์๋์ ๋ณด์ฌ ์ค ๊ฒ์
๋๋ค. ๊ตญ๋ฏผ ๋ชจ๋์๊ฒ ๋ฒ์ ์ง์ผ์ผ ํ๋ค๋ผ๋ ๊ธฐ์ด ์ฌ์ค์ด ๋ฟ๋ฆฌ๊ฐ ๊น์ง ๋ชปํ ๊ฒ์ด ํ์ค์
๋๋ค. ๋ฒํ๊ต์ก์ ๊ตญ๊ฐ์ ์ฐจ์์์ ๊ตญ๋ฏผ ๋ชจ๋์ ๊ต์ก์ด ๋์ด์ผ ํ๋ ์ด๋ ค์ด ์ฌ๋ช
์ ๊ฐ์ง๊ณ ์๋ค๊ณ ๋ณด์์ผ ํฉ๋๋ค. ์ ์ง์ผ๋ด์ผ ๋ณธ์ ์
๋๋ค. ์์ ๊ฒ์ ์๊ฒ ํ๋ ๊ฒ์ด ๋๋ถ๋ถ์ผ ๊ฒ์
๋๋ค. ์ด๊ฒ์ ๋ชปํด๋ด๊ณ ์์ต๋๋ค
FScI simulation for solid propellant rocket interior with ignition delay and secondary ignition
๊ณ ์ฒด ๋ก์ผ ๋ด๋ถ ํ์ ํด์์ ์ํด ๊ธฐ์กด ์ด๋ ๊ธฐ์ ๋ฐฉ๋ฒ๋ค์ ์ฅ์ ์ ๊ฒฐํฉํ ALE ๊ธฐ๋ฒ์ ๋์
ํ์ฌ ์ ์ฒด-๊ตฌ์กฐ-์ฐ์ ์ฐ๋ ํด์์ ์ํํ์๋ค. ์ด๋ฅผ ์ํด ๊ฐ๋ณ ํด์ ๊ธฐ๋ฒ(์ ๋, ๊ตฌ์กฐ, ์ฐ์)์ธ์ ํตํฉ ๊ธฐ๋ฒ๋ค๊ณผ ๋ณํํ๋ ํด์ ์์ญ์ ๋ํ ์๋ ๊ฒฉ์ ์์ฑ ๊ธฐ๋ฒ์ด ์ฐ๊ตฌ๋์๋ค. ๊ฐ๋ฐ๋ ํด์ ํ๋ก๊ทธ๋จ์ ์ด์ฉํ์ฌ ๊ณ ์ฒด ๋ก์ผ์ ๋ํด ๋น์ ์ฑ/์ ์ฑ ํด์์ ์ํํ์์ผ๋ฉฐ ์ ์ฑ ํด์ ์ ์ ํ๊ณผ์ ์์ ๋ฐ์ํ๋ ์ ํ ์ง์ฐ ํ์๊ณผ ์ด์ฐจ ์ ํ ํ์์ ๋ํด ๋ถ์ํ์๋ค.A fluid-structure interaction simulation of solid propellant rocket interior is carried out by employing the ALE (Arbitrary Lagrangian Eulerian) description, a hybrid model of continuum motion description combining the advantages of classical Lagrangian and Eulerian description. The integration process for fluid-structure interaction and an automatic re-meshing algorithm are included to analyze an unsteady fluid-structure interaction phenomenon with the deformation of solid grain during the simulation. The developed solver is applied for the simulation of a solid propellant grain with inviscid/viscous fluid model. Based on the integrated computed results, ignition delay and secondary ignition phenomena are examined from the physical and numerical perspectives.๋ณธ ๋
ผ๋ฌธ์ ๊ต์ก๊ณผํ๊ธฐ์ ๋ถ์ ์ฌ์์ผ๋ก ํ๊ตญ์ฐ๊ตฌ
์ฌ๋จ ์ฒจ๋จ์ฌ์ด์ธ์ค ๊ต์กํ๋ธ๊ฐ๋ฐ์ฌ์
(EDISON)์
์ง์(2011-0020559)์ ๋ฐ์ ์ํ๋์์.OAIID:oai:osos.snu.ac.kr:snu2013-01/104/0000004648/17SEQ:17PERF_CD:SNU2013-01EVAL_ITEM_CD:104USER_ID:0000004648ADJUST_YN:NEMP_ID:A001138DEPT_CD:446CITE_RATE:0FILENAME:2013์ถ๊ณํญ๊ณต์ฐ์ฃผํํ_์ด์ฐฝ์.pdfDEPT_NM:๊ธฐ๊ณํญ๊ณต๊ณตํ๋ถEMAIL:[email protected]:
The study on data transfer between non-matching meshes using common-refinement method for fluid-structure interaction simulations
During multi-physics or multi-phase simulations accompanying fluid-structure thermal interaction, data transfer problems always arise along non-matching interfaces caused by different computational meshes for each physical domain. Common-refinement scheme, among several available methods, is attractive since it is known to yield-conservative and accurate data transfer along non-matching interface boundary. This is particularly important in simulating compressible unsteady fluid-structure thermal interaction inside solid propellant rockets, where grid size along solid-fluid interfaces is substantially different. From this perspective, we examine performances of a common-refinement-based data transfer scheme between structured quadrilateral (structure part) and unstructured triangular (fluid part) meshes by comparing the computed results with other data transfer methods.๋ณธ ์ฐ๊ตฌ๋ ํ๊ตญํญ๊ณต์ฐ์ฃผ์ฐ๊ตฌ์์ ํ์ฐํ๋ ฅ๊ฐํ์ฌ์
๊ณผ ๊ต์ก๊ณผํ๊ธฐ์ ๋ถ์ ์ฐ์ฃผ๊ธฐ์ด์์ฒ๊ธฐ์ ๊ฐ๋ฐ ์ฌ์
(No.2011-0029871), ๊ต์ก๊ณผํ๊ธฐ์ ๋ถ์ ์ฌ์์ผ๋ก ํ๊ตญ๊ณผํ์ฌ๋จ(No.2011-0027486)์ ์ง์์ ๋ฐ์ ์ด๋ฃจ์ด์ก์.OAIID:oai:osos.snu.ac.kr:snu2012-01/104/0000004648/19SEQ:19PERF_CD:SNU2012-01EVAL_ITEM_CD:104USER_ID:0000004648ADJUST_YN:NEMP_ID:A001138DEPT_CD:446CITE_RATE:0FILENAME:์ ์ฒด-๊ตฌ์กฐ_์ฐ์ฑ_ํด์์_์ํ_common-refinement_๊ธฐ๋ฐ์_๋ถ์ผ์น_๊ฒฉ์_๊ฐ_์ ๋ณด_์ ๋ฌ_๊ธฐ๋ฒ_์ฐ๊ตฌ.pdfDEPT_NM:๊ธฐ๊ณํญ๊ณต๊ณตํ๋ถEMAIL:[email protected]: