표제지
목차
ABSTRACT 8
I. 서론 9
1.1. 연구배경 9
1.2. 연구목적 및 방법 12
II. 이론적 배경 13
2.1. 고전 적층판이론(Classical Lamination Theory) 13
2.2. 복합재 파손이론 19
2.2.1. 최대응력 파손이론(Maximum Stress Failure Criterion) 19
2.2.2. 최대변형률 파손이론(Maximum Strain Failure Criterion) 20
2.2.3. Tsai-Wu 파손이론(Tsai-Wu Failure Criterion) 20
2.2.4. Yamada-Sun 파손이론(Yamada-Sun Failure Criterion) 21
2.3. 유한요소해석 22
2.3.1. 하중조건 및 재료 물성치 22
2 3 2. 등가 강성, 강도 및 변형률 26
2.3.3. 유한요소모델 30
III. 결과 및 검토 44
3.1. 파손지수를 이용한 복합재 강도 해석 44
3.2. 복합재 빔 구조물의 단면 해석 51
3.3. 복합재 좌굴해석 56
3.4. 복합재 베어링/바이패스 해석 60
3.5. 복합재 손상허용 해석 64
3.6. 중량 분석 66
IV. 결론 67
참고 문헌 68
감사의 글 69
Table 1. Composite application of aircrafts 11
Table 2. Graphite-epoxy material properties 25
Table 3. Carpet plot tabular data for modulus Ex allowable(이미지참조) 28
Table 4. Carpet plot tabular data for modulus Gxy allowable(이미지참조) 29
Table 5. Layer stacking sequence and ply ratio of inboard skin 37
Table 6. Layer stacking sequence and ply ratio of inboard rib 40
Table 7. Layer stacking sequence and ply ratio of outboard skin 43
Table 8. Failure index and margin of safety of inboard skin 48
Table 9. Failure index and margin of safety of inboard rib 49
Table 10. Failure index and margin of safety of outboard skin 50
Fig. 1. Geometry of deformation in the x-z plane 14
Fig. 2. Aerodynamic finite element model 22
Fig. 3. Static load flow chart 23
Fig. 4. Laminate modulus Ex carpet plot(이미지참조) 28
Fig. 5. Laminate modulus Gxy carpet plot(이미지참조) 29
Fig. 6. Full scale aircraft finite element model 30
Fig. 7. Flaperon finite element model 33
Fig. 8. Assembly of actuator and actuator horn bracket 34
Fig. 9. Flaperon root rib and actuator horn bracket model 35
Fig. 10. Upper and lower inboard skin model 36
Fig. 11. Intercostal web model 38
Fig. 12. Inboard rib model 39
Fig. 13. Flaperon spar model 41
Fig. 14. Outboard skin model 42
Fig. 15. Failure index distribution of inboard skin 45
Fig. 16. Failure index distribution of inboard rib 46
Fig. 17. Failure index distribution of outboard skin 47
Fig. 18. Cross section shape of I beam composite structure 51
Fig. 19. Minimum margin of safety bay of inboard skin 57
Fig. 20. Bearing/Bypass Interaction Diagram 60
Fig. 21. Bearing/Bypass Interaction Diagram Envelope 62