표제지
목차
ABSTRACT 8
I. 서론 9
1.1. 연구 배경 9
1.2. 연구의 범위 및 방법 10
1.2.1. 비상사출 시스템 12
1.2.1.1. 사출좌석 16
1.2.1.2. 최소 탈출고도와 속도 19
1.2.2. 캐노피 작동 시스템 20
1.2.2.1. 캐노피 및 캐노피 작동기 설계하중 23
II. 이론적 배경 28
2.1. 유동해석 지배방정식 28
2.2. 지배 방정식의 변환 29
2.3. Transient Analysis 30
2.4. Stress Concentration 32
III. 캐노피 작동장치 전산해석 모델링 36
3.1. 캐노피 공력해석 모델링 36
3.2. 다물체 동역학 모델링 39
3.2.1. 캐노피 작동 미케니즘 39
3.3. 작동기 하중 및 응력 전산해석 모델링 41
IV. 해석결과 및 검토 43
4.1. 캐노피 공력해석 43
4.2. 다물체 동역학 해석 46
4.3. 구조 응력해석 48
4.3.1. 전산 응력해석 48
4.3.2. Roark 식을 활용한 응력해석 50
4.4. 구조 파손시험 52
V. 결론 57
참고 문헌 59
감사의 글 60
Table.1.1. In-flight emergency ejection sequence and procedure 14
Table.1.2. Bird strike capability of military aircraft 15
Table.1.3. Ejection sequence timings 19
Table.1.4. Recommended minimum ejection altitude 20
Table.3.1. CFD analysis condition of canopy 38
Table.4.1. Resulted force on canopy assembly 45
Table.4.2. Resulted force on canopy actuator 46
Table.4.3. Material properties of rod end 46
Table.4.4. Safety factor of rod end 49
Table.4.5. Stress concentration factor of bearing hole 50
Table.4.6. Stress concentration factor of 0.1 0 inch depth V-notch 50
Table.4.7. Safety factor of 0.1 0 inch depth V-notched rod end 51
Table.4.8. Resulted force on canopy assembly per flight speed 51
Table.4.9. Stress concentration factor of 0.05 inch depth V-notch 55
Table.4.10. Safety factor of 0.05 inch depth V-notched rod end 56
Fig.1.1. Flow chart for aerodynamic breakaway capability study 11
Fig.1.2. Ejection seat gas flow (Block diagram) 12
Fig.1.3. Emergency ejection 13
Fig.1.4. Ejection seat 16
Fig.1.5. Ejection modes 17
Fig.1.6. Ejection sequence 18
Fig.1.7. Electrically operated canopy, rear hinged andjettisonable 21
Fig.1.8. Canopy electrical system schematic 22
Fig.1.9. Canopy latching system layout 23
Fig.1.10. Electromechanical linear actuator 24
Fig.1.11. Internal gear trains of linear actuator 25
Fig.1.12. Closed view of canopy actuator attachment vs. CARB 26
Fig.1.13. Rod end of canopy actuator 27
Fig.2.1. Computation flow chart for SAMCEF 32
Fig.3.1. The coordinate system of canopy 36
Fig.3.2. Generated grid system (Half domain) 37
Fig.3.3. Generated grid system (Half domain, iso-view) 37
Fig.3.4. Closed view of computational grid (windshield/canopy) 38
Fig.3.5. Kinematic modeling of canopy actuation system 39
Fig.3.6. Kinematic modeling of canopy latching system 40
Fig.3.7. Gear train modeling in canopy actuator 40
Fig.3.8. Multi-body dynamic model 41
Fig.3.9. Rod end modeling 42
Fig.4.1. Flow streamline around canopy 43
Fig.4.2. Flow streamline around canopy (iso-view) 43
Fig.4.3. Closed view of flow streamline around canopy 44
Fig.4.4. Resultant static pressure contour around canopy 45
Fig.4.5. Load variation for canopy opening 47
Fig.4.6. Equivalent stress for canopy opening 48
Fig.4.7. Linear static analysis (20000 ft-120 knots flight condition) 49
Fig.4.8. Setup for actuator fracture load test 53
Fig.4.9. Fractured rod end due to tension 54
Fig.4.10. In-test data sheet of fracture load test 55