Wayne Durham

Aircraft Flight Dynamics and Control

• Gebundenes Buch

Produktbeschreibung

Aircraft Flight Dynamics and Control addresses airplane flight dynamics and control in a largely classical manner, but with references to modern treatment throughout. Classical feedback control methods are illustrated with relevant examples, and current trends in control are presented by introductions to dynamic inversion and control allocation.

This book covers the physical and mathematical fundamentals of aircraft flight dynamics as well as more advanced theory enabling a better insight into nonlinear dynamics. This leads to a useful introduction to automatic flight control and stability augmentation systems with discussion of the theory behind their design, and the limitations of the systems. The author provides a rigorous development of theory and derivations and illustrates the equations of motion in both scalar and matrix notation.

Key features:
Classical development and modern treatment of flight dynamics and control
Detailed and rigorous exposition and examples, with illustrations
Presentation of important trends in modern flight control systems
Accessible introduction to control allocation based on the author's seminal work in the field
Development of sensitivity analysis to determine the influential states in an airplane's response modes
End of chapter problems with solutions available on an accompanying website

Written by an author with experience as an engineering test pilot as well as a university professor, Aircraft Flight Dynamics and Control provides the reader with a systematic development of the insights and tools necessary for further work in related fields of flight dynamics and control. It is an ideal course textbook and is also a valuable reference for many of the necessary basic formulations of the math and science underlying flight dynamics and control.

Produktdetails

• Aerospace Series (PEP)
• Verlag: Wiley & Sons
• 1. Auflage
• Seitenzahl: 308
• Erscheinungstermin: 27. September 2013
• Englisch
• Abmessung: 250mm x 175mm x 21mm
• Gewicht: 644g
• ISBN-13: 9781118646816
• ISBN-10: 1118646819
• Artikelnr.: 38410361

Autorenporträt

Wayne Durham, Virginia Polytechnic Institute and State University, USA Wayne Durham is an Associate Professor Emeritus in the College of Engineering at Virginia Polytechnic Institute and State University. His area of research focuses on aircraft flight dynamics and control and he teaches a course (AOE 5214) on this subject at Virginia Tech University. He previously worked as a flight instructor at various Navy Schools in the US.

Inhaltsangabe

Series Preface xiii Glossary xv 1 Introduction 1 1.1 Background 1 1.2
Overview 2 1.3 Customs and Conventions 6 2 Coordinate Systems 7 2.1
Background 7 2.2 The Coordinate Systems 7 2.2.1 The inertial reference
frame, FI 7 2.2.2 The earth-centered reference frame, FEC 8 2.2.3 The
earth-fixed reference frame, FE 8 2.2.4 The local-horizontal reference
frame, FH 8 2.2.5 Body-fixed reference frames, FB 10 2.2.6 Wind-axis
system, FW 12 2.2.7 Atmospheric reference frame 12 2.3 Vector Notation 13
2.4 Customs and Conventions 14 2.4.1 Latitude and longitude 14 2.4.2 Body
axes 14 2.4.3 'The' body-axis system 14 2.4.4 Aerodynamic angles 15 3
Coordinate System Transformations 17 3.1 Problem Statement 17 3.2
Transformations 18 3.2.1 Definitions 18 3.2.2 Direction cosines 18 3.2.3
Euler angles 21 3.2.4 Euler parameters 25 3.3 Transformations of Systems of
Equations 26 3.4 Customs and Conventions 27 3.4.1 Names of Euler angles 27
3.4.2 Principal values of Euler angles 27 4 Rotating Coordinate Systems 31
4.1 General 31 4.2 Direction Cosines 34 4.3 Euler Angles 34 4.4 Euler
Parameters 36 4.5 Customs and Conventions 38 4.5.1 Angular velocity
components 38 5 Inertial Accelerations 43 5.1 General 43 5.2 Inertial
Acceleration of a Point 43 5.2.1 Arbitrary moving reference frame 43 5.2.2
Earth-centered moving reference frame 46 5.2.3 Earth-fixed moving reference
frame 46 5.3 Inertial Acceleration of a Mass 47 5.3.1 Linear acceleration
48 5.3.2 Rotational acceleration 49 5.4 States 53 5.5 Customs and
Conventions 53 5.5.1 Linear velocity components 53 5.5.2 Angular velocity
components 54 5.5.3 Forces 54 5.5.4 Moments 56 5.5.5 Groupings 56 6 Forces
and Moments 59 6.1 General 59 6.1.1 Assumptions 59 6.1.2 State variables 60
6.1.3 State rates 60 6.1.4 Flight controls 60 6.1.5 Independent variables
62 6.2 Non-Dimensionalization 62 6.3 Non-Dimensional Coefficient
Dependencies 63 6.3.1 General 63 6.3.2 Altitude dependencies 64 6.3.3
Velocity dependencies 64 6.3.4 Angle-of-attack dependencies 64 6.3.5
Sideslip dependencies 66 6.3.6 Angular velocity dependencies 68 6.3.7
Control dependencies 69 6.3.8 Summary of dependencies 70 6.4 The Linear
Assumption 71 6.5 Tabular Data 71 6.6 Customs and Conventions 72 7
Equations of Motion 75 7.1 General 75 7.2 Body-Axis Equations 75 7.2.1
Body-axis force equations 75 7.2.2 Body-axis moment equations 76 7.2.3
Body-axis orientation equations (kinematic equations) 77 7.2.4 Body-axis
navigation equations 77 7.3 Wind-Axis Equations 78 7.3.1 Wind-axis force
equations 78 7.3.2 Wind-axis orientation equations (kinematic equations) 80
7.3.3 Wind-axis navigation equations 81 7.4 Steady-State Solutions 81 7.4.1
General 81 7.4.2 Special cases 83 7.4.3 The trim problem 88 8 Linearization
93 8.1 General 93 8.2 Taylor Series 94 8.3 Nonlinear Ordinary Differential
Equations 95 8.4 Systems of Equations 95 8.5 Examples 97 8.5.1 General 97
8.5.2 A kinematic equation 99 8.5.3 A moment equation 100 8.5.4 A force
equation 103 8.6 Customs and Conventions 105 8.6.1 Omission of Delta 105
8.6.2 Dimensional derivatives 105 8.6.3 Added mass 105 8.7 The Linear
Equations 106 8.7.1 Linear equations 106 8.7.2 Matrix forms of the linear
equations 108 9 Solutions to the Linear Equations 113 9.1 Scalar Equations
113 9.2 Matrix Equations 114 9.3 Initial Condition Response 115 9.3.1 Modal
analysis 115 9.4 Mode Sensitivity and Approximations 120 9.4.1 Mode
sensitivity 120 9.4.2 Approximations 123 9.5 Forced Response 124 9.5.1
Transfer functions 124 9.5.2 Steady-state response 125 10 Aircraft Flight
Dynamics 127 10.1 Example: Longitudinal Dynamics 127 10.1.1 System matrices
127 10.1.2 State transition matrix and eigenvalues 127 10.1.3 Eigenvector
analysis 129 10.1.4 Longitudinal mode sensitivity and approximations 132
10.1.5 Forced response 137 10.2 Example: Lateral-Directional Dynamics 140
10.2.1 System matrices 140 10.2.2 State transition matrix and eigenvalues
140 10.2.3 Eigenvector analysis 142 10.2.4 Lateral-directional mode
sensitivity and approximations 144 10.2.5 Forced response 148 11 Flying
Qualities 151 11.1 General 151 11.1.1 Method 152 11.1.2 Specifications and
standards 155 11.2 MIL-F-8785C Requirements 156 11.2.1 General 156 11.2.2
Longitudinal flying qualities 157 11.2.3 Lateral-directional flying
qualitities 158 12 Automatic Flight Control 169 12.1 Simple Feedback
Systems 170 12.1.1 First-order systems 170 12.1.2 Second-order systems 172
12.1.3 A general representation 177 12.2 Example Feedback Control
Applications 178 12.2.1 Roll mode 178 12.2.2 Short-period mode 184 12.2.3
Phugoid 188 12.2.4 Coupled roll-spiral oscillation 198 13 Trends in
Automatic Flight Control 209 13.1 Overview 209 13.2 Dynamic Inversion 210
13.2.1 The controlled equations 212 13.2.2 The kinematic equations 215
13.2.3 The complementary equations 221 13.3 Control Allocation 224 13.3.1
Background 224 13.3.2 Problem statement 225 13.3.3 Optimality 231 13.3.4
Sub-optimal solutions 232 13.3.5 Optimal solutions 235 13.3.6 Near-optimal
solutions 241 Problems 243 References 244 A Example Aircraft 247 Reference
253 B Linearization 255 B.1 Derivation of Frequently Used Derivatives 255
B.2 Non-dimensionalization of the Rolling Moment Equation 257 B.3 Body Axis
Z-Force and Thrust Derivatives 258 B.4 Non-dimensionalization of the
Z-Force Equation 260 C Derivation of Euler Parameters 263 D Fedeeva's
Algorithm 269 Reference 272 E MATLAB Commands Used in the Text 273 E.1
Using MATLAB 273 E.2 Eigenvalues and Eigenvectors 274 E.3 State-Space
Representation 274 E.4 Transfer Function Representation 275 E.5 Root Locus
277 E.6 MATLAB(r) Functions (m-files) 277 E.6.1 Example aircraft 278 E.6.2
Mode sensitivity matrix 278 E.6.3 Cut-and-try root locus gains 278 E.7
Miscellaneous Applications and Notes 280 E.7.1 Matrices 280 E.7.2 Commands
used to create Figures 10.2 and 10.3 281 Index 283