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Integrated Fluid-Structure Simulation for Coupled Phenomena of a Solid Propellant Rocket Interior : 고체 로켓 연소실 내부 복합 현상에 대한 유체-구조 연성 해석
DC Field | Value | Language |
---|---|---|
dc.contributor.advisor | 김종암 | - |
dc.contributor.author | 한상호 | - |
dc.date.accessioned | 2017-07-13T06:14:33Z | - |
dc.date.available | 2017-07-13T06:14:33Z | - |
dc.date.issued | 2014-02 | - |
dc.identifier.other | 000000018534 | - |
dc.identifier.uri | https://hdl.handle.net/10371/118381 | - |
dc.description | 학위논문 (박사)-- 서울대학교 대학원 : 기계항공공학부, 2014. 2. 김종암. | - |
dc.description.abstract | 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. | - |
dc.description.tableofcontents | 공학박사 학위논문
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 국문 초록 | - |
dc.format | application/pdf | - |
dc.format.extent | 13613835 bytes | - |
dc.format.medium | application/pdf | - |
dc.language.iso | en | - |
dc.publisher | 서울대학교 대학원 | - |
dc.subject | Solid propellant rocket | - |
dc.subject | Fluid-structure interaction | - |
dc.subject | Arbitrary Lagrangian-Eulerian method | - |
dc.subject | Common-refinement data transfer | - |
dc.subject | Dynamic mesh treatment | - |
dc.subject.ddc | 621 | - |
dc.title | Integrated Fluid-Structure Simulation for Coupled Phenomena of a Solid Propellant Rocket Interior | - |
dc.title.alternative | 고체 로켓 연소실 내부 복합 현상에 대한 유체-구조 연성 해석 | - |
dc.type | Thesis | - |
dc.contributor.AlternativeAuthor | Sangho Han | - |
dc.description.degree | Doctor | - |
dc.citation.pages | xii, 133 | - |
dc.contributor.affiliation | 공과대학 기계항공공학부 | - |
dc.date.awarded | 2014-02 | - |
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