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제출문
보고서 요약서
국문 요약문
SUMMARY
목차
제1장 연구개발 과제의 개요 14
1. 연구개발 목적 14
2. 연구개발의 필요성 14
3. 연구개발 범위 17
제2장 국내외 기술개발현황 19
1. 국내 기술 개발 현황 19
2. 국외 기술 개발 현황 21
3. 기술개발기관 현황 24
제3장 연구수행내용 및 성과 26
1. Structure of the Flight Simulation Program 26
2. UAV standards and configuration DB 27
3. CS-VLA regulations 30
4. DB creation and development of UAV simulation 32
5. Investigation on aero db.xml file format 33
6. Simulation model tuning methodology 45
7. Flight test data processing 51
8. FDM validation and verification 56
9. Results of FDM validation 63
10. KAS-VLA certification compliance test case 67
11. Uav data verification using high-fidelity simulation software 69
12. Flight Simulation Build-up/Results Example(Cessna 172) 79
13. Aerodynamics and Dynamic Model Definition 89
14. Flight Simulation Results 93
15. Creating scenario for extreme flight situation 100
16. Conclusions 112
17. List of source code 113
제4장 목표달성도 및 관련분야 기여도 114
1. 목표 달성도 114
2. 관련 분야 기여도 114
제5장 연구개발성과의 활용계획 115
제6장 연구 과정에서 수집한 해외 과학기술 정보 116
제7장 연구개발성과의 보안등급 116
제8장 국가과학기술종합정보시스템에 등록한 연구시설·장비 현황 116
제9장 연구개발과제 수행에 따른 연구실 등의 안전 조치 이행 실적 116
제10장 연구개발과제의 대표적 연구 실적 117
제11장 기타 사항 124
제12장 참고 문헌 124
Table 1. The aircraft KLA-100 specifications 31
Table 2. Aero DB Forces Components 34
Table 3. Aero DB Moment Components 34
Table 4. Aero DB Ground Effect Components 35
Table 5. Table of available S&C derivatives from AVL 42
Table 6. Definition of variable parameter 49
Table 7. Dimensional longitudinal stability and control derivatives 50
Table 8. Coefficient value of relative derivatives 51
Table 9. List of flight test data parameters 52
Table 10. Small pitch control input test description 57
Table 11. Range of applicable damping ratio for data reduction methods 58
Table 12. Estimated parameters and current aerodynamic DB format 60
Table 13. Primary simulation result and flight test comparison 64
Table 14. Modified parameter of tuning model 65
Table 15. CS-VLA 181 Regulation - Dynamic Stability 67
Table 16. Summary of CS-VLA 181 - dynamic stability 68
Table 17. CS-VLA 181 compliance checking – short period mode 69
Table 18. Side by side comparison of KLA100 and Cessna 172 71
Table 19. Cessna 172 geometry parameters 88
Table 20. Cessna 172 mass data parameters 89
Table 21. Aerodynamic and Stability Derivatives from the current case data and Cessna 172 test case 93
Table 22. First cycle time of each result 100
Figure 1. 비행원리에 따른 무인기의 분류 14
Figure 2. 드론 사고사례 15
Figure 3. 연구 개발 개략도 18
Figure 4. The project overall process 26
Figure 5. Unpremeditated Descent Scenario(EASA E.T01001) 28
Figure 6. Loss of Control Scenario(EASA E.T01001) 29
Figure 7. RQ-1A Predator Selection of Applicable Airworthiness 30
Figure 8. A stable short period pitching oscillation 31
Figure 9. The aircraft KLA-100 3 sides sketch 32
Figure 10. Propeller characteristics : advanced ratio vs CP and CT[이미지참조] 33
Figure 11. Single value aero db components 36
Figure 12. 1D data table aero db components 36
Figure 13. 2D data table aero db components 37
Figure 14. 3D data table aero db components 38
Figure 15. Linear and non-linear model of aerodynamic behaviour 39
Figure 16. Empirical Formula forCₘₐ[reference][이미지참조] 43
Figure 17. Interpolation process from W/T to .xml format 44
Figure 18. W/T data (left) & Interpolation result (right) 45
Figure 19. Model tuning procedure using flight test data 46
Figure 20. Maximum Likelihood estimation concept 47
Figure 21. Flight test input parameters for estimation program 49
Figure 22. Convergence of model derivatives in short-period mode 50
Figure 23. Application of filtering technique on raw flight test data 53
Figure 24. Illustration of maneuver extraction 54
Figure 25. Flight test maneuver identification flowchart 55
Figure 26. Typical behavior of control input for different maneuvers 55
Figure 27. Flight simulation validation procedure 56
Figure 28. Transient Peak Ratio Method 59
Figure 29. Damping ratio chart for the TPR method 59
Figure 30. Update value of CLₐ at δᵳ=0⁰[이미지참조] 61
Figure 31. XML format for adding value of CLq[이미지참조] 61
Figure 32. CLδₑ behavior in linear region and high AOA region[이미지참조] 62
Figure 33. Update result of CLδₑ[이미지참조] 62
Figure 34. Update result of Cₘₐδₑ[이미지참조] 63
Figure 35. Primary simulation model responses and flight test data comparison 64
Figure 36. The trend of motion characteristics (ζsp,ωsp) with variation of effected parameters...[이미지참조] 65
Figure 37. Comparison of simulation model with and without parameter modification in short-period... 66
Figure 38. Comparison between modified simulation and modified simulation with AeroDB updated... 66
Figure 39. A stable short period pitching oscillation 68
Figure 40. Short period response to a doublet input 69
Figure 41. Flowchart of UAV flight data verification procedure 70
Figure 42. KLA 100 configuration 73
Figure 43. Cessna 172 configuration 74
Figure 44. Simulation aircraft station coordinates 75
Figure 45. Aerodynamic force and moment coefficient equation inputs 75
Figure 46. Defining aerodynamic curves and parameters 76
Figure 47. Simulated flight in run-time 77
Figure 48. Flowchart showing steps and input of running successful aircraft simulation 77
Figure 49. Commercial software flight data analysis 78
Figure 50. Location tracking of simulated flight 79
Figure 51. Steps for Flight Simulation Build-up 80
Figure 52. FS (Fuselage Station), BL (Butt Line), WL (Water Line) coordinate definitions 81
Figure 53. Cessna 172 dimensions, with approximated location of the center of gravity of the aircraft... 82
Figure 54. Top view of Cessna 172 with marked fuel tanks locations. The fuel tanks are located under... 83
Figure 55. Cessna 172 Landing gear geometry in FS, WL plane 84
Figure 56. Cessna 172 Landing gear geometry 85
Figure 57. Cessna 172 Main Landing Gear geometry 86
Figure 58. The location of components of Cessna 172S 87
Figure 59. Aerodynamic Modelling in Flight Simulation Software 91
Figure 60. Data set for CLₐ derivative[이미지참조] 92
Figure 61. Trim-Cruise: Plots state variables vs. Time 94
Figure 62. Roll-response: Plots State Variables vs. Time 95
Figure 63. Plots State Variables vs. Time 96
Figure 64. Pressure altitudes vs. Time for gliding 97
Figure 65. Aerodynamic coefficients vs. Time for gliding in Simulation 98
Figure 66. Normalized flight speed vs. Time for Phugoid motion 99
Figure 67. Atmospheric condition setup on run-time 100
Figure 68. Turbulence modelling and positioning on flightpath 101
Figure 69. Wind shear condition setup on run-time 101
Figure 70. Reconfigurable ground control station hardware 102
Figure 71. User interface designing software 103
Figure 72. Aircraft general parameter instrument panel 104
Figure 73. Angle of attack gauge 105
Figure 74. Autopilot/waypoint controller 105
Figure 75. Detailed engine monitor instrument panel 106
Figure 76. Flap controller instrument panel 106
Figure 77. Fuel gauge 107
Figure 78. Gesture controlled map 107
Figure 79. Non-gesture controlled map 108
Figure 80. Payload controller 108
Figure 81. Primary flight display 109
Figure 82. Simple engine monitor 109
Figure 83. Throttle and gear controller 110
Figure 84. Flowchart of virtual UAS certification 111