표제지
목차
Nomenclatures 14
I. 서론 17
1.1. 연구배경 17
1.2. 관련연구 20
1.3. 연구목적 20
1.4. 연구방법 21
II. 비행체 요구조건 분석 23
2.1. 미션 프로파일(Mission Profile) 23
2.2. 주요 요구조건 25
2.2.1. 기체 사이즈 26
2.2.2. 최대이륙중량 및 임무장비중량 26
2.2.3. 체공시간 27
2.2.4. 최대비행속도 27
2.2.5. 운용고도 27
2.2.6. 풍속조건 28
2.3. 요구조건만족 평가방식 29
III. 비행체 설계 31
3.1. 무게 추정 31
3.1.1. 기체 무게 추정 31
3.1.2. 추진 시스템 무게 추정 32
3.2. Airfoil 선정 34
3.3. Stall 속도 계산 38
3.4. 비행체 레이아웃 및 크기 설정 38
3.4.1. 주날개와 꼬리날개 구성 38
3.4.2. 주날개와 꼬리날개 크기 40
3.4.3. Boom 크기 및 배치 46
3.4.4. Control Surface 크기 46
3.4.5. 동체 크기 47
3.5. 상세 디자인 51
3.6. 체공시간 및 임무거리 예측 54
IV. 디자인 해석 결과 58
4.1. 안정성 분석 58
4.1.1. 종방향 정적 안정성 분석 58
4.1.2. 중립점 및 정적마진 62
4.2. 트림각 및 엘리베이터 각도 분석 63
4.3. 엘리베이터 및 에일러론 컨트롤 파워 분석 85
4.4. 횡방향 안정성 분석 86
4.5. 무게 중심 추정 87
V. 시제품 제작 89
5.1. 목업 기체 설계 및 제작 89
5.1.1. 추진 장치 및 동력원 구성 89
5.1.2. 비행체 모듈 구성 90
5.1.3. 목업 기체 제작 91
5.2. FRP 시제품 기체 제작 92
5.2.1. 틸팅 모듈 제작 92
5.2.2. 몰드 제작 93
5.2.3. FRP 스킨 제작 100
5.2.4. 내부 구조물 제작 101
5.2.5. 시제품 비행체 조립 103
VI. 비행시험 결과 105
VII. 결론 118
참고문헌 119
국문초록 120
ABSTRACT 122
Table 1-1. Status of Development about International Flying Car 19
Table 2-1. List of Requirement about VTOL UAV 28
Table 2-2. System & Sub-System Requirements 29
Table 3-1. Weight Chart of Four Prototypes of 2.2m Wingspan Hybrid VTOL UAV 31
Table 3-2. Target Weight Chart of 2.6m Wingspan Hybrid VTOL UAV 32
Table 3-3. Weight Chart to Design MTOW between 8㎏ to 9㎏ 33
Table 3-4. Weight Chart to Design MTOW between 9㎏ to 11㎏ 33
Table 3-5. Specifications of 2.2m Hybrid VTOL UAV 44
Table 3-6. Specifications of 2.6m Hybrid VTOL UAV 45
Table 3-7. Material Properties of the Fiber and Balsa 52
Table 3-8. The Result of Motor Power and Amp. Measuring Test 57
Table 4-1. MAC and Static Margin 63
Table 4-2. Trim Angle and Angle Deflection Results (using DATCOM Data) 85
Table 4-3. Actual Flight Data 85
Table 4-4. Control Surface Angle Deflection Results (using DATCOM Data) 86
Table 4-5. Clp and Cnβ Coefficients Results (using DATCOM Data) 86
Table 4-6. Center of Gravity Estimation 88
Table 5-1. List of Manufacturing Mould about VTOL UAV 93
Table 6-1. Flight Data at CG=9.0㎝ 106
Table 6-2. Flight Data at CG=8.5㎝ 107
Table 6-3. Flight Data at CG=8.0㎝ 107
Fig. 1-1. Type of VTOL UAV 18
Fig. 1-2. Type of Latest Flying Car 18
Fig. 2-1. Mission Profile 23
Fig. 2-2. Various Mode in Mission Profile 25
Fig. 3-1. NACA 8512 Airfoil Properties 34
Fig. 3-2. NACA 9412 Airfoil Properties 34
Fig. 3-3. NACA 9618 Airfoil Properties 35
Fig. 3-4. NACA 4415 Airfoil Properties 35
Fig. 3-5. NACA 8412 Airfoil Properties 35
Fig. 3-6. SG 6043 Airfoil Properties 35
Fig. 3-7. NACA 0011 Airfoil Properties 35
Fig. 3-8. SG 6043 Cl, Cd, Cm vs. Angle of Attack 36
Fig. 3-9. NACA 0011 Cl, Cd, Cm vs. Angle of Attack 37
Fig. 3-10. SG 6043 Cl vs. Angle of attack at Re=310,000 38
Fig. 3-11. Configuration of Aircraft 39
Fig. 3-12. Configuration of Wing 42
Fig. 3-13. Mean Aerodynamic Chord (MAC) 42
Fig. 3-14. XFLR Model of 2.2m Hybrid VTOL UAV 44
Fig. 3-15. XFLR Model of 2.6m Hybrid VTOL UAV 45
Fig. 3-16. Size and Layout of Boom Structure 46
Fig. 3-17. Initial Layout of the Aircraft 47
Fig. 3-18. Initial Layout (#1) of 2.6m Wingspan Aircraft 48
Fig. 3-19. Second Layout (#2) of 2.6m Wingspan Aircraft 49
Fig. 3-20. CATIA 3D Model of the Second Layout (#2) of 2.6m Wingspan Aircraft 50
Fig. 3-21. Third Layout (#3) of the 2.6m Wingspan Aircraft 51
Fig. 3-22. 2.6m Hybrid VTOL UAV CATIA Initial 3D Modelling 51
Fig. 3-23. Aircraft Skin Composition 52
Fig. 3-24. 2.6m Hybrid VTOL UAV CATIA Final 3D modelling 53
Fig. 3-25. Motor Test Equipment 57
Fig. 4-1. 2.2m Hybrid VTOL UAV XFLR5 Model 58
Fig. 4-2. XFLR5 Model of 2.6m Aircraft Layout (#1) 59
Fig. 4-3. 2.6m Hybrid VTOL UAV XFLR5 Model Layout (#2) 59
Fig. 4-4. 2.6m Hybrid VTOL UAV XFLR5 Model Layout (#3) 59
Fig. 4-5. 2.2m Hybrid VTOL UAV Lift Coefficient vs. Angle of Attack 60
Fig. 4-6. 2.2m Hybrid VTOL UAV Moment Coefficient vs. Angle of Attack 60
Fig. 4-7. 2.6m Hybrid VTOL UAV Layout (#3) Lift Coefficient Vs Angle of Attack 61
Fig. 4-8. 2.2m Hybrid VTOL UAV Moment Coefficient Vs Angle of Attack 61
Fig. 4-9. 2.2m Hybrid VTOL UAV DATCOM Model 64
Fig. 4-10. 2.6m Hybrid VTOL UAV DATCOM Model Layout (#1) 64
Fig. 4-11. 2.6m Hybrid VTOL UAV DATCOM Model Layout (#2) 65
Fig. 4-12. 2.6m Hybrid VTOL UAV DATCOM Model Layout (#3) 65
Fig. 4-13. 2.6m Hybrid VTOL UAV CATIA 3D Model Layout (#3) 66
Fig. 4-14. 2.2m Hybrid VTOL UAV Cm vs. Alpha at Various Elevator Deflection at V=12㎧ 67
Fig. 4-15. 2.2m Hybrid VTOL UAV CL vs. Alpha at Various Elevator Deflection at V=12㎧ 68
Fig. 4-16. 2.2m Hybrid VTOL UAV Cm vs. Alpha at Various Elevator Deflection at V=16㎧ 69
Fig. 4-17. 2.2m Hybrid VTOL UAV CL vs. Alpha at Various Elevator Deflection at V=16㎧ 69
Fig. 4-18. 2.6m Wingspan Aircraft Layout (#1) Cm vs. Alpha at Various Elevator Deflection at... 70
Fig. 4-19. 2.6m Wingspan Aircraft Layout (#1) CL vs. Alpha at Various Elevator Deflection at... 70
Fig. 4-20. 2.6m Wingspan Aircraft Layout (#2) Cm vs. Alpha at Various Elevator Deflection at... 71
Fig. 4-21. 2.6m Wingspan Aircraft Layout (#2) CL vs. Alpha at Various Elevator Deflection at... 71
Fig. 4-22. 2.6m Wingspan Aircraft Layout (#3) Cm vs. Alpha at Various Elevator Deflection at... 72
Fig. 4-23. 2.6m Wingspan Aircraft Layout (#3) CL vs. Alpha at Various Elevator Deflection at... 72
Fig. 4-24. 2.2m Hybrid VTOL UAV Cm vs. Alpha at Various Elevator Deflection at V = 17㎧ 73
Fig. 4-25. 2.2m Hybrid VTOL UAV CL vs. Alpha at Various Elevator Deflection at V = 17㎧ 73
Fig. 4-26. 2.6m Wingspan Aircraft Layout (#1) Cm vs. Alpha at Various Elevator Deflection at 74
Fig. 4-27. 2.6m Wingspan Aircraft Layout (#1) CL vs. Alpha at Various Elevator Deflection at... 74
Fig. 4-28. 2.6m Wingspan Aircraft Layout (#2) Cm vs. Alpha at Various Elevator Deflection at... 75
Fig. 4-29. 2.6m Wingspan Aircraft Layout (#2) CL vs. Alpha at Various Elevator Deflection at... 75
Fig. 4-30. 2.6m Wingspan Aircraft Layout (#3) Cm vs. Alpha at Various Elevator Deflection at... 76
Fig. 4-31. 2.6m Wingspan Aircraft Layout (#3) CL vs. Alpha at Various Elevator Deflection at... 76
Fig. 4-32. 2.2m Hybrid VTOL UAV Cm vs. Alpha at Various Elevator Deflection at V=18㎧ 77
Fig. 4-33. 2.2m Hybrid VTOL UAV CL vs. Alpha at Various Elevator Deflection at V=18㎧ 77
Fig. 4-34. 2.6m Wingspan Aircraft Layout (#1) Cm vs. Alpha at Various Elevator Deflection at... 78
Fig. 4-35. 2.6m Wingspan Aircraft Layout (#1) CL vs. Alpha at Various Elevator Deflection at... 78
Fig. 4-36. 2.6m Wingspan Aircraft Layout (#2) Cm vs. Alpha at Various Elevator Deflection at... 79
Fig. 4-37. 2.6m Wingspan Aircraft Layout (#2) CL vs. Alpha at Various Elevator Deflection at... 79
Fig. 4-38. 2.6m Wingspan Aircraft Layout (#3) Cm vs. Alpha at Various Elevator Deflection at... 80
Fig. 4-39. 2.6m Wingspan Aircraft Layout (#3) CL vs. Alpha at Various Elevator Deflection at... 80
Fig. 4-40. 2.2m Hybrid VTOL UAV Cm vs. Alpha at Various Elevator Deflection at V=19㎧ 81
Fig. 4-41. 2.2m Hybrid VTOL UAV CL vs. Alpha at Various Elevator Deflection at V=19㎧ 81
Fig. 4-42. 2.6m Wingspan Aircraft Layout (#1) Cm vs. Alpha at Various Elevator Deflection at 82
Fig. 4-43. 2.6m Wingspan Aircraft Layout (#1) CL vs. Alpha at Various Elevator Deflection at 82
Fig. 4-44. 2.6m Wingspan Aircraft Layout (#2) Cm vs. Alpha at Various Elevator Deflection at 83
Fig. 4-45. 2.6m Wingspan Aircraft Layout (#2) CL vs. Alpha at Various Elevator Deflection at 83
Fig. 4-46. 2.6m Wingspan Aircraft Layout (#3) Cm vs. Alpha at Various Elevator Deflection at... 84
Fig. 4-47. 2.6m Wingspan Aircraft Layout (#3) CL vs. Alpha at Various Elevator Deflection at... 84
Fig. 5-1. Motor & ESC Device 89
Fig. 5-2. Aircraft Parts Configuration 90
Fig. 5-3. Manufacturing of Mid-Wing using Balsa Material 91
Fig. 5-4. Manufacturing of Nose Part using 3D Printing 91
Fig. 5-5. Images of Mock-up Test UAV 92
Fig. 5-6. Tilting Module 92
Fig. 5-7. Images of Aluminium Front and Back Fuselage Moulds and Front Canopy Mould 95
Fig. 5-8. Images of Aluminium Main Wing and Tail Wing Moulds 95
Fig. 5-9. Material Layup for Vacuum Bagging Process 96
Fig. 5-10. Fuselage Mould in the Autoclave 96
Fig. 5-11. Fuselage Mould during Vacuum Bagging 96
Fig. 5-12. Cracked Region of the Carbon Fiber Mould 97
Fig. 5-13. Complex Region of the Mould where the Carbon Fiber Could Not Removed 97
Fig. 5-14. Fuselage Master Mould Modeling before Design Change 98
Fig. 5-15. Fuselage Master Mould Modeling after Design Change 98
Fig. 5-16. Carbon Back Fuselage Mould (Left and Right Side) 99
Fig. 5-17. Carbon Front Fuselage Mould (Left and Right Side) 99
Fig. 5-18. Image of Wing Skin Manufacturing 100
Fig. 5-19. Inner Structures of the Mid-Wing 101
Fig. 5-20. Inner Structures of the Outer Wing 101
Fig. 5-21. Inner Structures of Horizontal and Vertical Tail Wing 102
Fig. 5-22. Images of FRP First Proto-type 103
Fig. 5-23. Total Weight of FRP First Proto-type 104
Fig. 6-1. Angle of Attack at Trim 108
Fig. 6-2. Elevator Deflection Angle at Trim 108
Fig. 6-3. Flight Trajectory 109
Fig. 6-4. Pitch Rate(q), Pitch Angle, Flight Speed, Altitude at 21㎧ Flight Test 110
Fig. 6-5. Roll Rate(p), Roll Angle, Yaw Rate(r), Yaw Angle at 21㎧ Flight Test 111
Fig. 6-6. Pitch Rate(q), Pitch Angle, Flight Speed, Altitude at 24㎧ Flight Test 112
Fig. 6-7. Roll Rate(p), Roll Angle, Yaw Rate(r), Yaw Angle at 24㎧ Flight Test 113
Fig. 6-8. Pitch Rate(q), Pitch Angle, Flight Speed, Altitude at 27㎧ Flight Test 114
Fig. 6-9. Roll Rate(p), Roll Angle, Yaw Rate(r), Yaw Angle at 27㎧ Flight Test 115
Fig. 6-10. Pitch Rate(q), Pitch Angle, Flight Speed, Altitude at 30㎧ Flight Test 116
Fig. 6-11. Roll Rate(p), Roll Angle, Yaw Rate(r), Yaw Angle at 30㎧ Flight Test 117