표제지
목차
Abstract 10
I. 서론 12
1.1. 연구 배경 12
1.2. 문헌 조사 15
1.3. 연구 목적 및 범위 17
II. 기체 구조 설계 18
2.1. 기본 개념 설계 18
2.1.1. 대공표적기의 개요 18
2.2.2. 대공표적기 운용 조건 19
2.2.3. V-n선도 21
2.3. 날개 구조 설계 23
III. 구조 해석 28
3.1. 재료 물성치 시험 28
3.1.1. 시편 제작 28
3.2. 실험 31
3.2.1. 인장실험결과 32
3.2.2. 전단실험결과 36
3.2.3. 적층 두께 39
3.2.4. 파손형상 40
3.3. 유한 요소 해석 42
3.3.1. 주익 43
3.3.2. 랜딩기어 51
3.3.3. 정적해석결과 52
3.3.4. 동적해석결과 56
3.4. 주익 정적 실험 59
IV. 제작 62
4.1. 전동 스케일기 제작 62
4.2. 시제기 제작 68
4.2.1. 주익 제작 68
4.2.2. 수직 및 수평 꼬리날개 제작 71
4.2.3. 동체 및 랜딩기어 제작 72
4.2.4. 최종시제기 제작 76
V. 연구 결과 요약 77
참고문헌 80
감사의 글 82
Table 2-1. Requirements for various weapon 19
Table 3-1. Tensile specimen specification (ASTM-D3039) 28
Table 3-2. Material mechanical properties 38
Table 3-3. H612 and WR580A Thickness 39
Table 3-4. Main wing analysis results 50
Table 3-5. Main landing gear static analysis results of 2g (981N) load condition 55
Table 3-6. Main landing gear dynamic analysis results 58
Fig. 2-1. Schematic of a target-drone 18
Fig. 2-2. Eagle tree data recorder pro 21
Fig. 2-3. V-n diagram for the target drone 22
Fig. 2-4. Schematic of wing structure 23
Fig. 2-5. Schemetic of half wing structure 27
Fig. 3-1. V-notched beam test coupon schematic (ASTM-D5379) 29
Fig. 3-2. Specimen preparation process 30
Fig. 3-3. Experimental set-up 31
Fig. 3-4. Tensile test stress-strain curve and related data for H612(1mm) 33
Fig. 3-5. Tensile test stress-strain curve and related data for H612(3mm) 34
Fig. 3-6. Tensile test stress-strain curve and related data for WR580A(1mm) 34
Fig. 3-7. Tensile test stress-strain curve and related data for WR580A(3mm) 35
Fig. 3-8. Shear test stress-strain curve and related data for H612 36
Fig. 3-9. Shear test stress-strain curve and related data for WR580A 37
Fig. 3-10. Failure of tensile specimens 40
Fig. 3-11. Failure of shear specimens 41
Fig. 3-12. Finite element model of main wing structure 44
Fig. 3-13. Finite element model of main wing skin 45
Fig. 3-14. Number of plies for main wing skin 45
Fig. 3-15. Finite element model of main wing skin 46
Fig. 3-16. Tasi-wu failure index for main wing skin 47
Fig. 3-17. Tasi-wu failure index for main wing structure 47
Fig. 3-18. Buckling mode shape of the main wing 48
Fig. 3-19. Local buckling in the ribs 49
Fig. 3-20. Finite element model for the static analysis of the main landing gear 52
Fig. 3-21. Maximum stress failure index for main landing gear 53
Fig. 3-22. Tsai-wu failure index for main landing gear 54
Fig. 3-23. Finite element model for the dynamic analysis of the main landing gear 56
Fig. 3-24. Dynamic analysis results for main landing gear 57
Fig. 3-25. Schematic of a main wing static test set-up 60
Fig. 3-26. Main wing static test result on 6g condition 61
Fig. 3-27. Deflection at wing tip 61
Fig. 4-1. Cutting by laser cutting machine 63
Fig. 4-2. Shape of 1/3 scale model wing 64
Fig. 4-3. Reinforcement of 1/3 scale model wing 64
Fig. 4-4. Servo installation in a 1/3 scale model wing 65
Fig. 4-5. Shape of 1/3 scale model vertical and horizontal trail wing 66
Fig. 4-6. shape of 1/3 scale model fuselage 66
Fig. 4-7. Specimens of 1/3 scale model aircraft 67
Fig. 4-8. Main wing structure 68
Fig. 4-9. Painting of main wing 70
Fig. 4-10. Making a tail wing 71
Fig. 4-11. Engine mount 73
Fig. 4-12. Making fuselage and landing gear 74
Fig. 4-13. 684cc Target drone 76