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논문 기본 정보
- 자료유형
- 학위논문
- 저자정보
- 발행연도
- 2013
- 저작권
- 서울대학교 논문은 저작권에 의해 보호받습니다.
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Aeroelastic analysis of an aircraft with a high aspect ratio-wing for medium altitude and long endurance capability was attempted in this thesis. In order to achieve such objective, various structural and aerodynamic models were adopted. The traditional approach has been based on an Euler-Bernoulli beam structural model. In addition to that, a geometrically non-linear beam model was adopted. The structural analysis results of the present beam models were obtained and later compared with those by three-dimensional NASTRAN finite element model. The relevant unsteady aerodynamic forces were acquired by two methods. First, a finite state dynamic inflow unsteady aerodynamics model was developed and evaluated. Second, ZAERO, which is based on the doublet-lattice method, was used. These two kinds of aerodynamic forces were compared, and applied to the foregoing flutter analysis. For instance, the structural mode shapes and natural frequencies from both the Euler-Bernoulli beam structural model and the three-dimensional finite element model were transferred to ZAERO, which used the DLM aerodynamics to estimate the flutter. Similarly, flutter prediction was conducted by combining the Euler-Bernoulli beam structural model and the finite state dynamic inflow unsteady aerodynamics. The next phase of the present research will deal with the analysis of the possible interaction between the rigid-body degrees of freedom and the aeroelastic modes.
목차
Chapter 1. Introduction 11.1 MALE Aircraft 11.2 Background and Motivation 41.3 Research Objectives and Approach 101.4 Thesis Organization 11Chapter 2. Structural Modeling 142.1 Euler-Bernoulli Beam Structural Model 142.2 Three-Dimensional Finite Element Model 192.3 Geometrically Non-Linear Beam Model 21Chapter 3. Aerodynamic Modeling 283.1 Doublet Lattice Method (DLM) 283.2 Finite State Dynamic Inflow Unsteady Aerodynamics 31Chapter 4. Flutter Modeling 384.1 Flutter Prediction Based on the Euler-Bernoulli Beam Structural Model and DLM 394.1.1 The k-Method 414.1.2 The g-Method 424.1.3 Wing Flutter Analysis 444.1.4 Complete Aircraft Flutter Analysis 454.2 Flutter Prediction Based on the Geometrically Non-linear BeamModel and Finite State Dynamic Inflow Unsteady Aerodynamics 454.2.1 Steady-state Response 474.2.2 Perturbed Response 47Chapter 5. Numerical Results 515.1 Structural Analysis 515.1.1 Cross-sectional Analysis 515.1.2 Free Vibration Analysis 525.1.3 Mass Density Optimization and ImprovedFree Vibration Analysis 545.2 Aerodynamic Analysis 565.3 Flutter Analysis 57Chapter 6. Conclusion and Future Works 796.1 Summary 796.2 Future Works 80References 83Abstract (Korean) 90
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