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Development of the snapshot method for six degree-of-freedom flight dynamics simulation for a high aspect ratio wing aerial vehicle
고세장비 날개를 가지는 항공기의 6 자유도 비행동역학 시뮬레이션을 스냅샷 기법의 개발

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dc.contributor.advisor신상준-
dc.contributor.author빈영빈-
dc.date.accessioned2017-07-14T03:43:51Z-
dc.date.available2017-07-14T03:43:51Z-
dc.date.issued2017-02-
dc.identifier.other000000140935-
dc.identifier.urihttp://hdl.handle.net/10371/123927-
dc.description학위논문 (석사)-- 서울대학교 대학원 : 기계항공공학부, 2017. 2. 신상준.-
dc.description.abstractIn this thesis, a six degree-of-freedom flight simulation was developed considering the flexibility of an aircraft with high aspect ratio wings. A full three-dimensional finite element model of unmanned aerial vehicles was used. The object aircraft has main wings with aspect ratio over 20, and flight for long endurance in high altitude. To consider the flexibility of these aircraft, the present 'snapshot method' was developed that combines aerodynamic - structural dynamics - flight dynamics to analyze dynamic response. By applying this method, MATLAB/Simulink, which calculates the rigid body motion, and MSC.FlightLoads, which is responsible for aeroelastic trim analysis, were tightly linked into the present simulation framework.
Using the present simulation, aircraft response under various maneuver conditions was simulated. First, the trim analysis for the level cruise was performed. And the trim parameters, the stability derivative coefficients, and the moment of inertia were determined. Based on these results, the flight dynamics of the aircraft was simulated according to the operation of the rudder and the aileron control surface. And the effect of the rigid and flexible body assumptions were confirmed. Also, these results were compared with the other existing simulation results based on the multibody dynamics under the same conditions. In order to predict the response of the aircraft under the gust, the simulation was performed by applying the two-dimensional 1-cosine discrete gust profile.
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dc.description.tableofcontentsI. Introduction 1
1.1 Motivations 1
1.2 Research Backgrounds 2
1.3 Previous Researches 4
1.4 Research Objectives and Thesis Outline 11
II. Theoretical Background 15
2.1 Snapshot Method 15
2.2 Flight Dynamics Solver 18
2.2.1 Rigid Body Motion 18
2.2.2 Wind Axis Coordinate System 18
2.2.3 Formulation of Wind Axis Equation of Motion 20
2.2.4 Implementation by using MATLAB/Simulink 28
2.3 Aerodynamics Solver 30
2.3.1 Aerodynamic Finite Element Model for Flow Field 30
2.3.2 Doublet-Lattice Method Subsonic Lifting Surface Theory 31
2.3.3 Formulation of Doublet Lattice Method 31
2.4 Structure Dynamics Solver 33
2.4.1 Linear Static Analysis using Finite Element Model 33
2.5 Coupling Aerodynamic and Structure Dynamics Solver 34
2.5.1 Interconnection of the Structural Analysis with Aerodynamic Model 34
2.5.2 Formulation of the Spline Method 35
2.5.3 Quasi-steady Aeroelastic Analysis 36
2.5.4 Formulation of Aeroelasticity Trim Analysis 36
2.5.5 Implementation by using MSC.FlightLoads 41
2.6 Coupling Aerodynamic, Structure, and Flight Dynamic Solver 43
2.6.1 1 Aeroelastic and Rigid Body Motion Coupled Analysis 43
2.6.2 Implementation of the Simulation Framework 44
III. Results 47
3.1 Flight Simulation for Maneuver 47
3.1.1 Trim Analysis and Simulation Results for Level Cruise 47
3.1.2 Simulation Results of Response to Elevator Control Input 57
3.1.3 Simulation Results of Response to Aileron Control Input 60
3.2 Simulation of Response under Gust 63
3.2.1 Two-Dimensional Discrete Gust Profile 63
3.2.2 Simulation Results of Response under Gust 64
3.2.3 Structural Deformation of UAV under Gust 67
IV. Conclusions 69
4.1 Summary 69
4.2 Future Works 71
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dc.formatapplication/pdf-
dc.format.extent3455819 bytes-
dc.format.mediumapplication/pdf-
dc.language.isoen-
dc.publisher서울대학교 대학원-
dc.subjectHigh aspect ratio wing-
dc.subjectFlight simulation-
dc.subjectFlow field-structure-rigid body motion coupled analysis-
dc.subjectFlight dynamics-
dc.subjectAeroelasticity-
dc.subjectMATLAB/Simulink-
dc.subjectMSC.FlightLoads-
dc.subject.ddc621-
dc.titleDevelopment of the snapshot method for six degree-of-freedom flight dynamics simulation for a high aspect ratio wing aerial vehicle-
dc.title.alternative고세장비 날개를 가지는 항공기의 6 자유도 비행동역학 시뮬레이션을 스냅샷 기법의 개발-
dc.typeThesis-
dc.description.degreeMaster-
dc.citation.pages76-
dc.contributor.affiliation공과대학 기계항공공학부-
dc.date.awarded2017-02-
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College of Engineering/Engineering Practice School (공과대학/대학원)Dept. of Mechanical Aerospace Engineering (기계항공공학부)Theses (Master's Degree_기계항공공학부)
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