Advanced Flight Dynamics with Elements of Flight Control [Kietas viršelis]

, (IDEA Research Co. LTD, Pune, India)
  • Formatas: Hardback, 348 pages, aukštis x plotis: 235x156 mm, weight: 748 g, 20 Tables, black and white; 20 Illustrations, color; 163 Illustrations, black and white
  • Išleidimo metai: 15-Jun-2017
  • Leidėjas: Productivity Press
  • ISBN-10: 1498746047
  • ISBN-13: 9781498746045
Kitos knygos pagal šią temą:
  • Formatas: Hardback, 348 pages, aukštis x plotis: 235x156 mm, weight: 748 g, 20 Tables, black and white; 20 Illustrations, color; 163 Illustrations, black and white
  • Išleidimo metai: 15-Jun-2017
  • Leidėjas: Productivity Press
  • ISBN-10: 1498746047
  • ISBN-13: 9781498746045
Kitos knygos pagal šią temą:

Advanced Flight Dynamics aim to integrate the subjects of aircraft performance, trim and stability/control in a seamless manner. Advanced Flight Dynamics highlights three key and unique viewpoints. Firstly, it follows the revised and corrected aerodynamic modeling presented previously in recent textbook on Elementary Flight Dynamics. Secondly, it uses bifurcation and continuation theory, especially the Extended Bifurcation Analysis (EBA) procedure devised by the authors, to blend the subjects of aircraft performance, trim and stability, and flight control into a unified whole. Thirdly, rather than select one control design tool or another, it uses the generalized Nonlinear Dynamic Inversion (NDI) methodology to illustrate the fundamental principles of flight control.

Advanced Flight Dynamics covers all the standard airplane maneuvers, various types of instabilities normally encountered in flight dynamics and illustrates them with real-life airplane data and examples, thus bridging the gap between the teaching of flight dynamics/ control theory in the university and its practice in airplane design bureaus.

The expected reader group for this book would ideally be senior undergraduate and graduate students, practicing aerospace/flight simulation engineers/scientists from industry as well as researchers in various organizations.

Key Features:

  • Focus on unified nonlinear approach, with nonlinear analysis tools.
  • Provides an up-to-date, corrected, and unified presentation of aircraft trim, stability and control analysis including nonlinear phenomena and closed-loop stability analysis.
  • Contains a computational tool and real-life example carried through the chapters.
  • Includes complementary nonlinear dynamic inversion control approach, with relevant aircraft examples.
  • Fills the gap in the market for a text including non-linear flight dynamics and continuation methods.
Preface xiii
Authors xvii
Chapter 1 Six Degrees of Freedom Equations of Motion 1(54)
1.1 Definition Of Axis Systems
5(5)
1.1.1 Body-Fixed Axis System
5(2)
1.1.2 Earth-Fixed Axis System
7(1)
1.1.3 Wind-Fixed Axis System
7(3)
1.2 Definition Of Variables
10(6)
1.3 3-2-1 Transformation
16(8)
1.3.1 Earth- and Body-Fixed Axes
17(2)
1.3.2 Earth- and Wind-Fixed Axes
19(2)
1.3.3 Wind- and Body-Fixed Axes
21(1)
1.3.4 Relation between the Body-Axis and Wind-Axis Euler Angles
22(2)
1.4 Relation Between Angular Velocity Vector And Euler Angle Rates
24(5)
1.4.1 Relation between Body-Axis Angular Velocity Components (p, q, r) and Euler Angle Rates (phi, theta, psi)
24(3)
1.4.2 Relation between Wind-Axis Angular Velocity Components (pw, qw, rw) and Euler Angle Rates (mu;, gamma, xi)
27(1)
1.4.3 Difference between the Body-Axis Angular Velocity (p, q, r) and Wind-Axis Angular Velocity (pw, qw, rw)
27(2)
1.5 Translational Equations Of Motion
29(5)
1.6 Representation Of Forces Acting On The Airplane
34(4)
1.6.1 Gravity
34(1)
1.6.2 Aerodynamic Force
35(2)
1.6.3 Propulsive Force
37(1)
1.7 Rotational Equations Of Motion
38(4)
1.8 Representation Of Moments Acting On The Airplane
42(2)
1.8.1 Aerodynamic Moment
42(1)
1.8.2 Propulsive Moment
43(1)
1.9 Selection Of Equations For Specific Problems
44(4)
1.9.1 Simulation of Arbitrary Maneuver
45(1)
1.9.2 Steady States Such as Level Flight, Shallow Climb/Descent, Horizontal Turn, Spin, Etc.
45(2)
1.9.3 Longitudinal Flight Steady States
47(1)
1.9.4 Constant-Velocity Flight in the Longitudinal Plane
47(1)
1.9.5 Constant-Velocity Rolling Maneuvers
48(1)
1.10 Equations Of Motion In The Presence Of Wind
48(6)
Reference
54(1)
Chapter 2 Modeling and Interpreting the Aerodynamics 55(48)
2.1 Definition Of Aerodynamic Coefficients
55(2)
2.2 Modeling Of Aerodynamic Coefficients
57(3)
2.3 Static Aerodynamic Coefficient Terms
60(10)
2.3.1 Longitudinal Coefficients with Angle of Attack
60(4)
2.3.2 Lateral Coefficients with Angle of Attack and Sideslip Angle
64(2)
2.3.3 Variation with Mach Number
66(2)
2.3.4 Variation with Control Surface Deflection
68(2)
2.4 Dynamic Aerodynamic Coefficient Terms
70(3)
2.4.1 Pitching Moment Due to Relative Pitch Rate, Cmq1
71(1)
2.4.2 Yawing and Rolling Moment Due to Relative Yaw Rate, Cnr1 and Clr1
72(1)
2.5 Flow Curvature Coefficient Terms
73(3)
2.5.1 Yawing and Rolling Moment Due to Wind-Axis Yaw Rate, Cnr2 and Clr2
73(1)
2.5.2 Pitching Moment Due to Wind-Axis Pitch Rate, Cmq2
74(1)
2.5.3 Rolling Moment Due to Wind-Axis Roll Rate, Clp2
74(2)
2.6 Downwash Lag Terms
76(2)
2.7 Sample Simulation Cases
78(24)
2.7.1 Example Airplane and Aerodynamic Models
82(3)
2.7.1.1 F-18 Low-Angle-of-Attack Model
82(1)
2.7.1.2 F-18/HARV High-Angle-of-Attack Model
83(1)
2.7.1.3 Pseudo-Steady-State Model for Rapid Rolling Maneuvers
83(2)
2.7.2 Example Simulation Results
85(17)
References
102(1)
Chapter 3 Introduction to Dynamical Systems Theory 103(54)
3.1 Types Of Steady States
108(2)
3.1.1 Equilibrium States
109(1)
3.1.2 Periodic States
110(1)
3.1.3 Quasi-Periodic States
110(1)
3.1.4 Chaotic States
110(1)
3.2 Stability Of Steady States
110(12)
3.2.1 Stability of Equilibrium States
111(7)
3.2.2 Stability of Periodic Orbits
118(4)
3.3 Bifurcations Of Steady States
122(14)
3.3.1 Stationary Bifurcations of Equilibrium States
125(6)
3.3.1.1 Saddle-Node Bifurcation
125(3)
3.3.1.2 Transcritical Bifurcation
128(1)
3.3.1.3 Pitchfork Bifurcation
129(1)
3.3.1.4 Perturbation to Transcritical and Pitchfork Bifurcations
130(1)
3.3.2 Hopf Bifurcation of Equilibrium States
131(2)
3.3.3 Bifurcations of Periodic States
133(3)
3.4 Continuation Algorithms
136(8)
3.5 Continuation Framework For Multiparameter Systems
144(12)
3.5.1 Scheduling the Parameters in a Multiparameter System
145(3)
3.5.2 Influence of Aircraft Control Parameters on Constraints
148(8)
References
156(1)
Chapter 4 Longitudinal Flight Dynamics 157(30)
4.1 Longitudinal Steady States (Trims)
160(3)
4.1.1 Modeling Engine Thrust
161(2)
4.2 Longitudinal Trim And Stability Analysis
163(4)
4.2.1 Longitudinal Trim and Stability with Varying Angle of Attack
163(2)
4.2.2 Longitudinal Trim and Stability with Varying Throttle Setting
165(2)
4.3 Level Flight Trim And Stability Analysis
167(6)
4.3.1 Level Flight Airplane Performance
171(2)
4.4 Climbing/Descending Flight Trim And Stability Analysis
173(3)
4.5 Pull-Up And Push-Down Maneuvers
176(6)
4.6 Wind Effects On Longitudinal Dynamic Modes
182(3)
Reference
185(2)
Chapter 5 Longitudinal Feedback Control 187(30)
5.1 Generic Flight Control System
187(1)
5.2 Airframe, Sensor, Filter, Actuator
188(3)
5.3 Generic Longitudinal FCS Structure
191(3)
5.4 Longitudinal Flight Control Modes
194(2)
5.5 Longitudinal Feedback Control Law
196(8)
5.5.1 Gain Scheduling
199(5)
5.6 Dynamic Inversion Control Law
204(3)
5.7 Closed-Loop Stability Analysis
207(8)
5.7.1 With Thrust Vectoring Control Included
212(3)
References
215(2)
Chapter 6 Lateral-Directional Flight Dynamics and Control 217(40)
6.1 Lateral-Directional Modes In Straight And Level Longitudinal Flight
218(7)
6.2 Horizontal Level Turn Trims
225(9)
6.2.1 Formulation and Constraints
226(1)
6.2.2 Parameter Schedules
227(1)
6.2.3 Turn Performance
228(6)
6.3 Nonzero Sideslip Trim And Stability Analysis
234(3)
6.4 Wing Rock Onset And Its Prediction
237(14)
6.4.1 Analytical Criterion for Wing Rock Onset
239(21)
6.4.1.1 Second-Order Form of the Perturbed Lateral-Directional Equations
243(3)
6.4.1.2 Matrix Form of the Perturbed Lateral- Directional Equations
246(1)
6.4.1.3 Static Instability Criterion
246(1)
6.4.1.4 Approximation by Hamiltonian Dynamical System
247(2)
6.4.1.5 Dynamic Instability Mechanism
249(2)
6.5 Lateral-Directional Feedback Control System
251(4)
References
255(2)
Chapter 7 Coupled Lateral-Longitudinal Flight Dynamics 257(46)
7.1 Inertia Coupled Roll Maneuvers
260(12)
7.1.1 Zero-Sideslip Roll Maneuvers
266(3)
7.1.2 Velocity-Vector Roll Maneuvers
269(3)
7.2 High AOA Flight Dynamics And Spin
272(10)
7.2.1 Analytical Criterion for Spin Susceptibility
277(5)
7.2.1.1 Derivation of the Criterion
279(3)
7.3 Bifurcation Tailoring/Trim Shaping As Control Strategy
282(7)
7.3.1 Linear ARI Law for Jump Prevention
283(2)
7.3.2 Trim Shaping for Level Flight Trims
285(2)
7.3.3 Rolling Pull-Down Maneuver with Zero Sideslip
287(2)
7.4 Control Prototyping For Recovery From Spin
289(5)
7.4.1 Spin Recovery Using Sliding Mode Control
293(1)
7.5 Carefree Maneuvering Using Sliding Mode Controller
294(8)
7.5.1 Minimum Radius Turn Maneuver Using Sliding Mode Controller
295(2)
7.5.2 Maneuver Design Based on AER
297(5)
References
302(1)
Chapter 8 Dynamics and Control of a 10-Thruster Flight Vehicle 303(32)
8.1 Flight Dynamics Of The 10-Thruster DACS
303(5)
8.2 Modeling The Thruster Forces And Moments
308(2)
8.3 Modeling The Change In CG And Moments Of Inertia
310(2)
8.4 Modeling The Aerodynamic Forces And Moments
312(2)
8.5 Control And Guidance Framework For 10-Thruster DACS
314(2)
8.6 DACS Control Law
316(6)
8.6.1 Navigation Equations and Flight Path Controller
316(2)
8.6.2 Attitude Equations and Attitude Controller
318(1)
8.6.3 Rate Equations and Rate Controller
319(2)
8.6.4 Issue of Invertibility
321(1)
8.6.5 The Question of Stability
321(1)
8.7 DACS Guidance Law
322(7)
8.7.1 Derivation of Dynamic Inversion-Based Guidance Law
323(6)
8.7.1.1 In Terms of Azimuth and Elevation Angles
325(3)
8.7.1.2 A Question of Invertibility
328(1)
8.7.1.3 Decoding the Inversion-Based Guidance Law
328(1)
8.8 Simulation Of 10-Thruster DACS Flight With Guidance And Control
329(5)
Reference
334(1)
Index 335
Dr. Nandan K Sinha is on the faculty of Department of Aerospace Engineering at the Indian Institute of Technology (IIT) Madras, India, where he is currently a professor since July 2014. Dr. Sinha has Bachelor's, Master's, and PhD degrees in Aerospace Engineering all from IITs and postdoctoral stint during 2003-2006 at the TU-Darmstadt, Germany, before taking up the faculty position at IIT Madras in 2006. Dr. Sinha has over a decade experience of teaching courses in vibrations, flight mechanics & controls, aircraft design, space technology, nonlinear dynamics, etc. His research interests evolve around design, dynamics, control and guidance of aerospace vehicles, working on several funded projects from Indian aerospace industry. He is known for his popular video lecture series on Flight Dynamics available on youtube and web-based lecture series on Introduction to Space Technology, both via NPTEL resources, an initiative of MHRD, Govt of India. He has authored the book "Elementary Flight Dynamics with an Introduction to Bifurcation and Continuation Methods," with Dr. N Ananthkrishnan published by CRC press, Taylor and Francis in 2014. His professional services as subject expert extend to many national committees for various assignments and as reviewers to many international/national journals and conferences. Dr N Ananthkrishnan is an Independent Consultant presently based out of Mumbai (India) with over twenty-two years experience in academia and industry in multi-disciplinary research and development across a wide spectrum from Combustion Systems to Airplane Aerodynamics to Flight Control & Guidance. Over the past decade, he has largely worked with businesses in the Mumbai/Pune area and Bangalore in India, and in Daejeon (South Korea), and with a few select academic institutes. His recent work has focused on the broad area of Aerospace Systems Design & Integration with emphasis on Atmospheric Flight Mechanics & Control and Air-breathing Propulsion Systems. He has previously served on the faculty of Aerospace Engineering at the Indian Institute of Technology, IIT Bombay at Mumbai (India) and as a Visiting Faculty Member at the California Institute of Technology at Pasadena, CA (USA). He received the "Excellence in Teaching" award at IIT Bombay in the year 2000. He has authored a textbook (with NK Sinha), Elementary Flight Dynamics with an Introduction to Bifurcation and Continuation Methods, published by CRC Press, Taylor & Francis (2014). He received his education in Aerospace Engineering at the Indian Institutes of Technology majoring in Flight Mechanics & Control, Aerodynamics, Aircraft Design, and Nonlinear Systems. He is Associate Fellow, American Institute of Aeronautics & Astronautics (AIAA) and has served a term as a member of the AIAA Atmospheric Flight Mechanics Technical Committee.