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Introduction to aircraft aeroelasticity and loads
Aircraft performance is influenced significantly both by aeroelastic phenomena, arising from the interaction of elastic, inertial and aerodynamic forces, and by load variations resulting from flight and ground manoeuvres and gust / turbulence encounters. There is a strong link between aeroelasticity...
| Clasificación: | Libro Electrónico |
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| Autor principal: | |
| Otros Autores: | |
| Formato: | Electrónico eBook |
| Idioma: | Inglés |
| Publicado: |
Chichester,England ; Hoboken, NJ :
John Wiley,
c2007.
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| Edición: | 1st edition. |
| Colección: | Aerospace series (Chichester, England)
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| Temas: | |
| Acceso en línea: | Texto completo (Requiere registro previo con correo institucional) |
Tabla de Contenidos:
- Introduction to Aircraft Aeroelasticity and Loads; Contents; Preface; Introduction; Abbreviations; Part I Background Material; 1 Vibration of Single Degree of Freedom Systems; 1.1 Setting up Equations of Motion for Single DoF Systems; 1.2 Free Vibration of Single DoF Systems; 1.3 Forced Vibration of Single DoF Systems; 1.4 Harmonic Forced Vibration
- Frequency Response Functions; 1.5 Transient/Random Forced Vibration
- Time Domain Solution; 1.6 Transient Forced Vibration
- Frequency Domain Solution; 1.7 Random Forced Vibration
- Frequency Domain Solution; 1.8 Examples
- 2 Vibration of Multiple Degree of Freedom Systems2.1 Setting up Equations of Motion; 2.2 Undamped Free Vibration; 2.3 Damped Free Vibration; 2.4 Transformation to Modal Coordinates; 2.5 'Free-Free' Systems; 2.6 Harmonic Forced Vibration; 2.7 Transient/Random Forced Vibration
- Time Domain Solution; 2.8 Transient Forced Vibration
- Frequency Domain Solution; 2.9 Random Forced Vibration
- Frequency Domain Solution; 2.10 Examples; 3 Vibration of Continuous Systems
- Assumed Shapes Approach; 3.1 Rayleigh-Ritz 'Assumed Shapes' Method; 3.2 Generalized Equations of Motion
- Basic Approach
- 3.3 Generalized Equations of Motion
- Matrix Approach3.4 Generating Aircraft 'Free-Free' Modes from 'Branch' Modes; 3.5 Whole Aircraft 'Free-Free' Modes; 3.6 Examples; 4 Vibration of Continuous Systems
- Discretization Approach; 4.1 Introduction to the Finite Element (FE) Approach; 4.2 Formulation of the Beam Bending Element; 4.3 Assembly and Solution for a Structure with Beam Elements; 4.4 Torsion Element; 4.5 Combined Bending/Torsion element; 4.6 Comments on Modelling; 4.7 Examples; 5 Introduction to Steady Aerodynamics; 5.1 The Standard Atmosphere
- 5.2 Effect of Air Speed on Aerodynamic Characteristics5.3 Flows and Pressures Around a Symmetric Aerofoil; 5.4 Forces on an Aerofoil; 5.5 Variation of Lift for an Aerofoil at an Angle of Incidence; 5.6 Pitching Moment Variation and the Aerodynamic Centre; 5.7 Lift on a Three-Dimensional Wing; 5.8 Drag on a Three-Dimensional Wing; 5.9 Control Surfaces; 5.10 Supersonic Aerodynamics
- Piston Theory; 5.11 Transonic Flows; 5.12 Examples; 6 Introduction to Loads; 6.1 Laws of Motion; 6.2 D'Alembert's Principle
- Inertia Forces and Couples; 6.3 Externally Applied/reactive Loads
- 6.4 Free Body Diagrams6.5 Internal Loads; 6.6 Internal Loads for Continuous Representation of a Structure; 6.7 Internal Loads for Discretized Representation of a Structure; 6.8 Intercomponent Loads; 6.9 Obtaining Stresses from Internal Loads
- Structural Members with Simple Load Paths; 6.10 Examples; 7 Introduction to Control; 7.1 Open and Closed Loop Systems; 7.2 Laplace Transforms; 7.3 Modelling of Open and Closed Loop Systems Using Laplace and Frequency Domains; 7.4 Stability of Systems; 7.5 PID Control; 7.6 Examples; Part II Introduction to Aeroelasticity and Loads
- 8 Static Aeroelasticity
- Effect of Wing Flexibility on Lift Distribution and Divergence