학위논문 (박사)-- 서울대학교 대학원 : 기계항공공학부, 2015. 2. 신상준. ; In this thesis, an eighteen-node solid-shell finite element was used for structural dynamics modeling of rotating composite blades. The analysis model includes the effects of transverse shear deformation, Coriolis effect and elastic couplings due to the anisotropic material behavior. Also, the out of plane warping was included without complicated assumptions for specific beam, plate or shell theories. The incremental total-Lagrangian approach was adopted to allow estimation on arbitrarily large rotations and displacements. The equations of motion for the finite element model were derived using Hamilton’s principle, and the resulting nonlinear equilibrium equations were solved by utilizing Newton-Raphson method combined with the load control. A modified stress-strain relation was adopted to avoid the transverse shear locking problem, and fairly reliable results were obtained with no sign of the locking phenomenon. In order to reduce the computational complexity of the problem, the Guyan and IRS reduction methods were adopted. Those model reduction methods gave not only reliable solutions, but also less computational effort for any geometric configurations and boundary conditions. The present numerical results were compared to the several benchmark problems, and the results show a good correlation with the experimental data and other finite element analysis results. The vibration characteristics of shell and beam type blades were investigated. For the case of shell type blades, blade curvature, pre-twist and geometric nonlinearity may significantly influence the dynamic characteristics, and only the geometric nonlinear analysis model can capture significant drops in frequency and frequency loci veering phenomena. For the case of beam type blades, one-dimensional beam and three-dimensional solid models give comparable prediction for the straight and large aspect ratio blade. As decreasing in the blade aspect ratio, considerable differences appear in bending and torsion modes. The tip sweep angle tends to decrease the flap bending frequencies, but the torsion frequency increases with the tip sweep angle. On the contrary, the tip anhedral enforces to decrease the torsion frequency. ; 1. Introduction 1.1 Background 1.2 Literature Review 1.2.1 Beam Models 1.2.2 Plate and Shell Models 1.3 Objectives and Layout of Thesis 2. Geometrically Nonlinear Formulation 2.1 Introduction 2.2 Strain and Stress Tensors 2.3 Strain Energy 2.4 Kinetic Energy 2.5 Equations of Motion 2.6 Composite Structures 3. Finite Element Formulation 3.1 Coordinate Systems 3.1.1 Global Coordinate System 3.1.2 Local Coordinate System 3.1.3 Natural Coordinate System 3.2 Element Geometry and Displacement Field 3.3 Strain-Displacement Relation 3.4 Derivation of Matrices and Vectors 3.5 Layer-wise Thickness Integration 3.6 Nonlinear Solution Techniques 3.7 Model Reduction Method 3.7.1 Static Reduction 3.7.2 IRS(Improved Reduction System) Reduction 4. Verification Problems 4.1 Static Behavior 4.1.1 Cantilevered Beam under Shear Force 4.1.2 Ring Plate under the Uniform Line Load 4.1.3 Pinched Semi-Cylindrical Shell 4.2 Dynamic Behavior 4.2.1 Plate-Type Blade Model 4.2.2 Shell-Type Blade Model 5. Vibration Analysis of Shell Type Blades 5.1 Effect of Geometric Nonlinearity 5.1.1 Shallow Shell Model 5.1.2 Deep Shell Model 5.2 Effect of Pre-twist 6. Vibration Analysis of Beam Type Blades 6.1 Effect of Tip Sweep Angle 6.1.1 Isotropic Blade Models 6.1.2 Composite Blade Models 6.2 Effect of Tip Sweep Ratio 6.3 Effect of Tip Anhedral 7. Conclusions 7.1 Summary 7.2 Future Works ; Doctor