표제지
국문요약
목차
제1장 서론 14
제1절 연구배경 및 목적 14
제2절 연구동향 18
제3절 연구범위 및 내용 22
제2장 이론적 고찰 25
제1절 지배방정식 25
제2절 난류 모델 27
1. Standard k-ε Model 30
2. Standard k-ω Model 32
3. SST k-ω Model 36
제3장 유동해석 및 공압실험 방법 40
제1절 유동해석 접근방법 40
1. 격자구성 좌표계 40
2. 단일화학종 비반응 모델 41
3. 유입 압력 및 작동유체 42
제2절 유동해석 방법 45
1. 해석 방법 45
2. 해석 모델 45
3. 격자 생성 51
4. 경계조건 및 초기조건 60
제3절 공압실험 방법 64
1. 실험장치 64
2. 실험조건 70
제4장 유동해석 및 공압실험 결과 고찰 73
제1절 유동해석 결과 73
1. 펄스분리장치 홀 면적대 노즐 목 면적비의 영향 73
2. 펄스분리장치 설치위치의 영향 93
3. 펄스분리장치 홀 배치 형상의 영향 107
4. 작동 유체의 영향 122
5. 유동해석 결과 종합 132
제2절 공압실험 결과 135
1. 펄스분리장치 홀 면적 및 설치위치에 따른 영향 135
2. 펄스분리장치 홀 배치 형상에 따른 영향 140
3. 공압실험 결과 종합 143
제5장 유동해석 결과 검증 145
제1절 펄스분리장치 홀 면적 및 설치위치 145
제2절 펄스분리장치 홀 배치 형상 149
제3절 2D 및 3D 해석 결과 152
제6장 결론 154
참고문헌 161
Abstract 173
Table 3.1. Specification of CFD models 47
Table 3.2. Design parameters with PSD configuration 50
Table 3.3. Mesh information of 2D analysis models 54
Table 3.4. Mesh information of 3D analysis models 59
Table 3.5. Boundary conditions of analysis model 61
Table 3.6. Value of input variables for CFD analysis 63
Table 3.7. Specification of pneumatic test sample according to hole area and installation location of PSD 68
Table 3.8. Specification of pneumatic test sample according to hole arrangement configuration of PSD 69
Table 4.1. Composition of propellant 123
Table 4.2. Value of input variables for CFD analysis of combustion gas 124
Table 4.3. Pneumatic test result for 1st chamber pressure according to hole area and installation location of PSD 139
Table 4.4. Result of pneumatic test for 1st chamber pressure according to hole arrangement configuration of PSD 142
Table 5.1. Comparison of CFD and pneumatic test result for 1st chamber pressure 148
Table 5.2. Comparison of CFD and pneumatic test result 151
Fig. 1.1. Simplified diagram of a dual pulse rocket motor with two grains separated by a pulse separation device 14
Fig. 1.2. Comparison of the velocity over distance of two hypervelocity missiles with boost-sustain motor and double pulse motor 15
Fig. 1.3. Flow characteristics when combustion gases exit 2nd chamber through the pulse separation device hole in a dual pulse rocket motor(이미지참조) 16
Fig. 1.4. Typical thrust-time history of a dual pulse rocket motor 17
Fig. 3.1. 3D configuration of PSD, PSD dimension of B type and C type 49
Fig. 3.2. Computational domain, detailed configuration of PSD and nozzle mesh for 2D analysis model 52
Fig. 3.3. Independence of CFD result with cell number of 2D model 53
Fig. 3.4. Computational domain and detailed PSD mesh of 3D analysis models 57
Fig. 3.5. Independence of CFD result with cell number of 3D model 58
Fig. 3.6. Boundary condition of analysis model 62
Fig. 3.7. Schematic diagram of a pneumatic test chamber 66
Fig. 3.8. Component configurations of pneumatic experimental apparatus 67
Fig. 3.9. Schematic diagram of pneumatic experimental apparatus 71
Fig. 3.10. Schematic diagram of pneumatic chamber 72
Fig. 4.1. Results of CFD for static pressure distribution and dynamic pressure streamline 75
Fig. 4.2. Results of CFD for dynamic pressure streamline of group I 76
Fig. 4.3. Pressure distribution with axis line, 1st chamber pressure and pressure difference of group I 77
Fig. 4.4. Pressure distribution with axis line, 1st chamber pressure and pressure difference of group II 78
Fig. 4.5. Pressure distribution with axis line, 1st chamber pressure and pressure difference of group III 79
Fig. 4.6. Comparison of pressure for each group at 1st chamber 80
Fig. 4.7. Turbulent kinetic energy(k) and specific dissipation rate(ω) value of 1st chamber for group III 81
Fig. 4.8. Results of CFD for velocity distribution and velocity streamline 84
Fig. 4.9. Results of CFD for velocity streamline of group I 85
Fig. 4.10. Velocity distribution with axis line 87
Fig. 4.11. Comparison of mach number for each group at PSD hole 88
Fig. 4.12. Results of CFD for temperature streamline of group I 90
Fig. 4.13. Temperature distribution with axis line 92
Fig. 4.14. Results of CFD for pressure streamline of case 3 95
Fig. 4.15. Pressure distribution with axis line 97
Fig. 4.16. Results of CFD for velocity streamline of case 4 99
Fig. 4.17. Velocity distribution with axis line 102
Fig. 4.18. Results of CFD for temperature streamline of case 3 104
Fig. 4.19. Temperature distribution with axis line 106
Fig. 4.20. Result of CFD for pressure distribution according to PSD type with the axis line 108
Fig. 4.21. Velocity distribution with axis line and velocity streamline according to PSD hole arrangement configuration 111
Fig. 4.22. Mach number distribution with the center line and PSD hole axis 114
Fig. 4.23. Velocity distribution of radial direction 118
Fig. 4.24. Distribution of temperature with axis line 120
Fig. 4.25. Results of CFD for temperature distribution 121
Fig. 4.26. Pressure distribution of group II applied combustion gas and comparison of 1st chamber pressure... 126
Fig. 4.27. Mach number distribution of group II applied combustion gas and comparison of mach... 128
Fig. 4.28. Temperature distribution of group II applied combustion gas and comparison of temperature... 131
Fig. 4.29. Comparison of pneumatic test result for 1st chamber pressure and pressure difference 138
Fig. 5.1. Comparison of CFD and pneumatic test result for 1st chamber pressure 147
Fig. 5.2. Comparison of CFD analysis results between 2D and 3D 153