Title Page
Abstract
Contents
Chapter 1. Introduction 10
1.1. Study Background 10
1.2. Cases of Fuel Cell Aircraft Development 13
1.3. Purpose of Research 16
Chapter 2. Method 17
2.1. Aircraft Modeling 17
2.2. Aerodynamic Analyses 19
2.3. Performance Analyses 22
2.4. Weight Estimation 28
Chapter 3. Results and Discussion 33
3.1. Panel Sensitivity Test 33
3.2. Aerodynamic Database Development 38
3.3. Propulsion Database Development 42
3.4. Weight Estimation 48
3.5. Performance Analyses 51
Chapter 4. Concluding Remarks 54
Bibliography 56
국문초록 60
Table 1.1. Specifications of Previously Developed Fuel Cell Aircrafts 16
Table 2.1. Specification of KC-100 Aircraft 18
Table 2.2. Coefficients and Parameters for Weight Estimation Model 31
Table 3.1. Solver Validation Analysis Condition of Cessna 172 Case 38
Table 3.2. Experiment Setup of KC-100 Wind Tunnel Test 42
Table 3.3. VSPAERO Input Parameters for Propeller Model Validation 42
Table 3.4. Flow Condition and Propeller Configuration for Propeller Performance Map Development 46
Table 3.4. Parameters of Mission Segment for the Weight Estimation 49
Table 3.5. Weight Estimation Result 50
Table 3.6. Cruise Speed Calculation Result 51
Table 3.7. Results of the Mission Performance Analysis 53
Figure 1.1. Annual Increase of CO2 Emission from the Aviation Transport 11
Figure 1.2. Energy Density of Variable Energy Sources 11
Figure 1.3. Photo of the Boeing Fuel Cell Demonstrator 13
Figure 1.4. Photo of the ENFICA-FC 14
Figure 1.5. Photo of the Antares DLR-H2 14
Figure 1.6. Photo of the DLR HY4 15
Figure 2.1. Graphics of the KC-100 "Naraon" 17
Figure 2.2. KC-100 and Propeller Models on OpenVSP 19
Figure 2.3. The Amesim Simulation Model for the Mission Simulation 24
Figure 2.4. The Tafel Plots 26
Figure 2.5. Typical Polarization Curve Modeled in Simcenter Amesim 28
Figure 2.6. Schematic Diagram of Weight Estimation Approach 29
Figure 2.7. Flow Chart of Weight Estimation Model 32
Figure 3.1. Lifting Body Panel Distribution for Aspect Ratio 1:1 Model 33
Figure 3.2. Lifting Body Panel Distribution for Aspect Ratio 2:1 Model 33
Figure 3.3. Propeller Panel Distribution for Aspect Ratio 1:1 Model 34
Figure 3.4. Propeller Panel Distribution for Aspect Ratio 2:1 Model 34
Figure 3.5. Lift Coefficient Variance of Lifting Surfaces along the Number of Panels 35
Figure 3.6. Induced Drag Coefficient Variance of Lifting Surfaces along the Number of Panels 35
Figure 3.7. Elapsed Time versus Number of Panels for Lifting Surfaces 36
Figure 3.8. Thrust Coefficient Variance of Propeller along the Number of Panels 36
Figure 3.9. Power Coefficient Variance of Propeller along the Number of Panels 37
Figure 3.10. Elapsed Time versus Number of Panels for Propeller 37
Figure 3.11. Cessna 172 Model on OpenVSP 38
Figure 3.12. Lift Coefficient of Cessna 172 Calculated from VSPAERO and DATCOM 39
Figure 3.13. Drag Coefficient of Cessna 172 Calculated from VSPAERO and DATCOM 39
Figure 3.14. Pressure Coefficient Distribution along the Lifting Surface of KC-100 Model 40
Figure 3.15. Lift Coefficients of KC-100 Model 41
Figure 3.16. Drag Coefficients of KC-100 Model 41
Figure 3.17. Lift Coefficient Result of Unsteady Analysis 44
Figure 3.18. Drag Coefficient Result of Unsteady Analysis 44
Figure 3.19. VSPAERO Thrust Estimation Result 44
Figure 3.20. Lift Coefficient Result of Unsteady Analysis After Thrust Correction 45
Figure 3.21. Drag Coefficient Result of Unsteady Analysis After Thrust Correction 45
Figure 3.22. Propeller Performance Map with the Power Coefficient 47
Figure 3.23. Propeller Performance Map with the Thrust Coefficient 47
Figure 3.24. Mission Plot for the Weight Estimation 49
Figure 3.25. Fuel Consumption Rate and Mass Variance over Time 50
Figure 3.26. Flowchart of Performance Analysis 51
Figure 3.27. Performance Analysis Results of (a) Thrust, (b) Power, and (c) Rate of Climb 52