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Steady Glide Dynamics and Guidance of Hypersonic Vehicle 2021 ed. [Kõva köide]

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  • Formaat: Hardback, 461 pages, kõrgus x laius: 235x155 mm, kaal: 904 g, 97 Illustrations, color; 221 Illustrations, black and white; XXXII, 461 p. 318 illus., 97 illus. in color., 1 Hardback
  • Ilmumisaeg: 08-Nov-2020
  • Kirjastus: Springer Verlag, Singapore
  • ISBN-10: 9811589003
  • ISBN-13: 9789811589003
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Steady Glide Dynamics and Guidance of Hypersonic Vehicle 2021 ed.Suurem pilt
  • Formaat: Hardback, 461 pages, kõrgus x laius: 235x155 mm, kaal: 904 g, 97 Illustrations, color; 221 Illustrations, black and white; XXXII, 461 p. 318 illus., 97 illus. in color., 1 Hardback
  • Ilmumisaeg: 08-Nov-2020
  • Kirjastus: Springer Verlag, Singapore
  • ISBN-10: 9811589003
  • ISBN-13: 9789811589003
Teised raamatud teemal:
Püsilink: https://www.kriso.ee/db/9789811589003.html
This book presents the latest researches on hypersonic steady glide dynamics and guidance, including the concept of steady glide reentry trajectory and the stability of its regular perturbation solutions, trajectory damping control technique for hypersonic glide reentry, singular perturbation guidance of hypersonic glide reentry, trajectory optimization based on steady glide, linear pseudospectral generalized nominal effort miss distance guidance, analytical entry guidance and trajectory-shaping guidance with final speed and load factor constraints. They can be used to solve many new difficult problems in entry guidance. And many practical engineering cases are provided for the readers for better understanding. Researchers and students in the fields of flight vehicle design or flight dynamics, guidance and control could use the book as valuable reference.
1 Introduction 1(10)
1.1 Problem Description
1(1)
1.2 Research Significance
2(2)
1.3 Research Progress
4(4)
References
8(3)
2 Mathematical Fundamentals 11(30)
2.1 Regular Perturbation Method
11(2)
2.2 Singular Perturbation Method
13(3)
2.3 Spectral Decomposition Method
16(3)
2.3.1 Idempotent Matrix
16(1)
2.3.2 Spectral Decomposition Theorem
16(1)
2.3.3 Inference
17(2)
2.3.4 Example
19(1)
2.4 Pseudospectral Method
19(14)
2.4.1 Introduction of Method
19(4)
2.4.2 Pseudospectral Discrete Process
23(10)
2.5 Linear Gauss Pseudospectral Model Predictive Control
33(5)
References
38(3)
3 Mathematical Modeling for Hypersonic Glide Problem 41(12)
3.1 The Coordinate System Adopted in This Book
41(2)
3.1.1 Geocentric Inertial Coordinate System (I)
41(1)
3.1.2 Geographic Coordinate System (T)
41(1)
3.1.3 Orientation Coordinate System (0)
42(1)
3.1.4 Velocity Coordinate System (V)
42(1)
3.1.5 Half-Velocity Coordinate System (H)
42(1)
3.1.6 Body Coordinate System (B)
43(1)
3.2 Transformation Between Coordinate Systems
43(2)
3.2.1 Transformation Between the Orientation Coordinate System and the Half-Velocity Coordinate System
43(1)
3.2.2 Transformation Between the Velocity Coordinate System and the Half-Velocity Coordinate System
43(1)
3.2.3 Transformation Between the Velocity Coordinate System and the Body Coordinate System
44(1)
3.2.4 Transformation Between the Body Coordinate System and the Half-Velocity Coordinate System
45(1)
3.3 Dynamic Equations of Hypersonic Vehicle in Half-Velocity Coordinate System
45(8)
3.3.1 Dynamics Equations of the Center of Mass in Half-Velocity Coordinate System
45(3)
3.3.2 The Dynamic Equations of the Center of Mass of the Vehicle
48(1)
3.3.3 Dynamic Equations of Hypersonic Gliding Vehicle Based on BIT Control
48(1)
3.3.4 Dynamic Equations of Hypersonic Vehicle in Vertical Plane
49(1)
3.3.5 Atmospheric Model
50(1)
3.3.6 Aerodynamic Model
50(1)
3.3.7 The Stagnation Point Heat Flow, Overload and Dynamic Pressure
50(3)
4 Mathematical Description of Glide-Trajectory Optimization Problem 53(12)
4.1 Mathematical Description for Optimal Control Problem
53(8)
4.1.1 Performance Index of Optimal Control Problem
53(1)
4.1.2 Description of Optimal Control Problem
54(1)
4.1.3 The Minimum Principle
55(1)
4.1.4 Final Value Performance Index of Time-Invariant Systems
56(1)
4.1.5 Integral Performance Index of Time-Invariant Systems
57(1)
4.1.6 Optimal Control Problem with Inequality Constraints
58(1)
4.1.7 Methods for Solving Optimal Control Problems
58(3)
4.2 Mathematical Description of Optimal Control Problem for Hypersonic Vehicle Entry Glide
61(4)
4.2.1 Maximum Final Speed Problem
61(1)
4.2.2 Maximum Range Problem
62(1)
4.2.3 Shortest Time Problem
62(1)
4.2.4 Optimal Trajectory Problem with Heating Rate Constraint
63(1)
4.2.5 Optimal Trajectory Problem with Heating Rate and Load Factor Constraints
64(1)
5 Indirect Approach to the Optimal Glide Trajectory Problem 65(38)
5.1 Combined Optimization Strategy for Solving the Optimal Gliding Trajectory of Hypersonic Aircraft
67(7)
5.1.1 Mathematical Model of Hypersonic Gliding
67(1)
5.1.2 Necessary Conditions for Optimal Gliding Trajectory
68(1)
5.1.3 Solving Two-Point Boundary Value Problem by Combination Optimization Strategy
69(1)
5.1.4 Numerical Calculation Results
70(3)
5.1.5 Conclusion
73(1)
5.2 Trajectory Optimization of Transition Section of Gliding Hypersonic Flight Vehicle
74(10)
5.2.1 Aerodynamic Data for the Transition Section
74(1)
5.2.2 Unconstrained Trajectory of Maximum Terminal Velocity
75(1)
5.2.3 Heat Flow Constrained Trajectory of Maximum Terminal Velocity
76(1)
5.2.4 Solving the Two-Point Boundary Value Problem for the Transition Section
77(1)
5.2.5 Optimizing the Transition Trajectory with Direct Method
77(1)
5.2.6 Steps for Solving the Optimal Transition Trajectory
78(3)
5.2.7 Transitional Trajectory Obtained by Indirect Method
81(3)
5.3 The Maximum Range Gliding Trajectory of the Hypersonic Aircraft
84(17)
5.3.1 Guess Initial Values for Optimal Control Problem by Direct Method
84(5)
5.3.2 Indirect Method for Solving Optimal Control Problems
89(5)
5.3.3 The Maximum Range Gliding Trajectory of the Hypersonic Aircraft
94(7)
References
101(2)
6 Direct Method for Gliding Trajectory Optimization Problem 103(22)
6.1 Direct Method for Solving Optimal Control Problems
103(1)
6.2 Direct Shooting Method
104(3)
6.2.1 Direct Multiple Shooting Method
104(1)
6.2.2 Direct Method of Discrete Control
105(1)
6.2.3 Gradual Subdividing Optimization Strategy
106(1)
6.3 Direct Collocation Method
107(4)
6.3.1 General Form of Direct Collocation Method
107(1)
6.3.2 Direct Transcription
108(1)
6.3.3 Implicit Integral Method
109(1)
6.3.4 Solving Optimal Trajectory Problems with NLP
110(1)
6.4 Direct Collocating Method for Trajectory with Maximum Gliding Cross Range of Hypersonic Aircraft
111(8)
6.4.1 Mathematical Model
111(2)
6.4.2 Re-entry Flight Control Law with Given Angle of Attack Profile
113(1)
6.4.3 Solution of Maximum Cross Range Problem by Direct Collocation Method
113(3)
6.4.4 Optimization Example
116(2)
6.4.5 Summary
118(1)
6.5 Pseudo-spectral Method for the Optimal Trajectory of the Hypersonic Vehicle with the Longest Cross-Range
119(6)
6.5.1 Introduction of Pseudo-spectral Method
119(3)
6.5.2 Optimization Examples and Results
122(3)
7 Concept of Steady Glide Reentry Trajectory and Stability of Its Regular Perturbation Solutions 125(24)
7.1 Introduction
125(1)
7.2 Kinetic Equations
126(1)
7.3 Definition of the Steady Glide Trajectory
127(1)
7.4 Effects of Control Variable on SGT
128(1)
7.5 Effects of Initial Value on SGT
129(1)
7.6 Analytical Solution of SGT
129(6)
7.6.1 Altitude Dynamic Differential Equation
129(2)
7.6.2 Analytical Steady Glide Altitude
131(2)
7.6.3 Second-Order Item
133(1)
7.6.4 Analytical Solutions of Flight Path Angle and Vertical Acceleration
134(1)
7.7 Dynamic Characteristics of SGT
135(5)
7.7.1 Stability Analysis
135(2)
7.7.2 Natural Frequency and Damping
137(3)
7.8 Feedback Control of SGT
140(7)
7.8.1 Feedback Design
140(4)
7.8.2 Fixed-Damping Differential Feedback Method
144(3)
7.9 Conclusions
147(1)
References
147(2)
8 Analytical Solutions of Steady Glide Reentry Trajectory in Three Dimensions and Their Application to Trajectory Planning 149(18)
8.1 Introduction
149(1)
8.2 Mathematical Model
150(3)
8.2.1 Definition of Coordinate Frame
150(1)
8.2.2 Kinematic Equations
150(2)
8.2.3 Decoupling of Equations
152(1)
8.3 Analytical Solution of Glide Trajectory
153(4)
8.3.1 Analytical Solution of Altitude
153(1)
8.3.2 Analytical Solution of Range
154(1)
8.3.3 Analytical Solution of Heading Angle
154(1)
8.3.4 Analytical Solution of Longitude and Latitude
155(1)
8.3.5 Analytical Solution of Velocity
156(1)
8.3.6 Optimal Initial Glide Angle
157(1)
8.4 Simulation
157(7)
8.4.1 Comparison Between Analytical Solution and Numerical Integral
157(1)
8.4.2 Comparison with Bell Analytical Solution
157(3)
8.4.3 Application of Analytic Solutions in Trajectory Planning
160(4)
8.5 Summary
164(1)
References
164(3)
9 Trajectory Damping Control Technique for Hypersonic Glide Reentry 167(24)
9.1 Introduction
167(1)
9.2 Guidance Scheme
168(6)
9.2.1 Mathematical Proof
168(2)
9.2.2 Command Flight-Path Angle for L/Dmax
170(2)
9.2.3 Guidance Scheme for Range Maximization and Trajectory Damping Control
172(1)
9.2.4 Extended Guidance Scheme for Glide Range Control
173(1)
9.3 Hypersonic Vehicle Model
174(2)
9.4 Results and Discussion
176(13)
9.4.1 Performance of Guidance Scheme
176(7)
9.4.2 Application of the Extended Guidance Scheme
183(6)
9.5 Conclusions
189(1)
References
189(2)
10 Steady Glide Dynamic Modeling and Trajectory Optimization for High Lift-To-Drag Ratio Reentry Vehicle 191(22)
10.1 Introduction
191(2)
10.2 Dynamics and Vehicle Description
193(2)
10.2.1 Entry Dynamics
193(1)
10.2.2 Entry Trajectory Constraints
194(1)
10.2.3 Vehicle Description and Model Assumption
194(1)
10.3 Trajectory-Oscillation Suppressing Scheme
195(3)
10.3.1 Generic Theory for the Oscillation Suppressing Scheme
195(2)
10.3.2 Performance of the Trajectory-Oscillation Suppressing Scheme
197(1)
10.4 Steady Glide Dynamic Modeling and Trajectory Optimization
198(11)
10.4.1 Steady Glide Dynamic Modeling
199(1)
10.4.2 Hp-Adaptive Gaussian Quadrature Collocation Method
200(1)
10.4.3 Numerical Example of Trajectory Optimization Without Bank Reversal
201(4)
10.4.4 Numerical Example of Trajectory Optimization with Bank Reversal
205(1)
10.4.5 Verification of Feasibility for the Pseudospectral Solution
206(3)
10.5 Conclusion
209(1)
References
210(3)
11 Singular Perturbation Guidance of Hypersonic Glide Reentry 213(20)
11.1 Singular Perturbation Guidance for Range Maximization of a Hypersonic Glider
213(12)
11.1.1 Problem Formulation (Dimensionless Model)
213(2)
11.1.2 Reduced-Order System Solutions
215(1)
11.1.3 Slow-Boundary Layer Solutions
216(2)
11.1.4 Fast-Boundary Layer Solutions
218(2)
11.1.5 Simulation Results
220(1)
11.1.6 Comparison and Analysis
221(4)
11.2 Improved Singular Perturbation Guidance for Maximum Glide Range
225(7)
11.2.1 Dynamic Model and Solutions to the Reduced-Order System
226(1)
11.2.2 Boundary Layer Correction
227(1)
11.2.3 Slow Boundary-Layer Correction
227(1)
11.2.4 Fast Boundary-Layer Correction
228(1)
11.2.5 Guidance Law Derivation
228(1)
11.2.6 Simulation Results and Analyses
229(3)
11.3 Summary
232(1)
References
232(1)
12 3-D Reentry Guidance with Real-Time Planning of Reference using New Analytical Solutions Based on Spectral Decomposition Method 233(44)
12.1 Introduction
233(2)
12.2 Equations of Motion
235(2)
12.3 Entry Trajectory Constraints
237(1)
12.3.1 Path Constraints
237(1)
12.3.2 Terminal Conditions
237(1)
12.4 Analytical Solutions to Hypersonic Gliding Problem
237(11)
12.4.1 Auxiliary Geocentric Inertial (AGI) Frame
237(2)
12.4.2 Linearization of the Equations of Motion
239(2)
12.4.3 Analytical Solutions
241(4)
12.4.4 Example for Accuracy Verification
245(3)
12.5 Entry Guidance
248(25)
12.5.1 Descent Phase
248(1)
12.5.2 Quasi-Equilibrium Glide Phase
249(11)
12.5.3 Altitude Adjustment Phase
260(2)
12.5.4 Results and Discussion
262(1)
12.5.5 Nominal Cases
262(11)
12.6 Conclusions
273(1)
Appendix
273(2)
References
275(2)
13 Omnidirectional Autonomous Reentry Guidance Based on 3-D Analytical Glide Formulae Considering Influence of Earth's Rotation 277(46)
13.1 Introduction
277(3)
13.2 Entry Guidance Problem
280(2)
13.2.1 Equations of Motion
280(1)
13.2.2 Path Constraints
281(1)
13.2.3 Terminal Conditions
282(1)
13.3 Omnidirectional Autonomous Entry Guidance
282(18)
13.3.1 Overview
282(3)
13.3.2 Descent Phase
285(1)
13.3.3 Steady Glide Phase
286(14)
13.4 Altitude Adjustment Phase
300(6)
13.4.1 Correction of Baseline AOA Profile and Second Bank Reversal
300(4)
13.4.2 Baseline Bank Angle in AAP
304(1)
13.4.3 AOA and Bank Angle Commands in AAP
305(1)
13.5 Results and Discussion
306(8)
13.5.1 Nominal Cases
306(3)
13.5.2 Monte Carlo Simulations
309(5)
13.6 Conclusions
314(1)
Appendix 1: Generalized States of Motion
315(3)
Appendix 2: Generalized Aerodynamic Forces
318(1)
References
319(4)
14 Analytical Steady-Gliding Guidance Employing Pseudo-Aerodynamic Profiles 323(42)
14.1 Introduction
323(2)
14.2 Entry Guidance Problem
325(2)
14.2.1 Equations of Motion
325(1)
14.2.2 Path Constraints
326(1)
14.2.3 Terminal Conditions
327(1)
14.3 Analytical Entry Guidance Design
327(22)
14.3.1 Descent Phase
328(1)
14.3.2 Steady Glide Phase
328(16)
14.3.3 Altitude Adjustment Phase
344(5)
14.4 Results and Discussion
349(12)
14.4.1 Nominal Cases
349(5)
14.4.2 Monte Carlo Simulations
354(7)
14.5 Conclusions
361(3)
References
364(1)
15 Linear Pseudospectral Guidance Method for Eliminating General Nominal Effort Miss Distance 365(24)
15.1 Introduction
365(1)
15.2 Generic Theory of LGPMPC
366(11)
15.2.1 Linearization of Nonlinear Dynamic System and Formulation of Linear Optimal Control Problem
367(2)
15.2.2 Linear Gauss Pseudospectral Method
369(5)
15.2.3 Singularity of Differential Approximation Matrices for Different Pseudospctral Methods
374(1)
15.2.4 Boundary Control of Linear Gauss Pseudospctral Method
374(1)
15.2.5 Implementation of LGPMPC
375(2)
15.3 Application to Terminal Guidance
377(9)
15.3.1 Terminal Guidance Problem and Three-Dimensional Mode
377(2)
15.3.2 Initial Guess and Target Model
379(1)
15.3.3 Cases for Target with Straight-Line Movements
380(4)
15.3.4 Comparison with Adaptive Terminal Guidance
384(2)
15.4 Conclusion
386(1)
Appendix
387(1)
References
388(1)
16 Linear Pseudospectral Reentry Guidance with Adaptive Flight Phase Segmentation and Eliminating General Nominal Effort Miss Distance 389(44)
16.1 Introduction
389(2)
16.2 Entry Dynamics, Entry Trajectory Constraints and Vehicle Description
391(3)
16.2.1 Entry Dynamics
391(1)
16.2.2 Entry Trajectory Constraints
392(1)
16.2.3 Vehicle Description and Model Assumption
393(1)
16.2.4 Auxiliary Geocentric Inertial Frame and Emotion Dynamics
393(1)
16.3 Linear Pseudospectral Model Predictive Entry Guidance
394(23)
16.3.1 Descent Phase Guidance
395(1)
16.3.2 Glide Phase Entry Guidance
395(16)
16.3.3 Terminal Adjustment Phase
411(5)
16.3.4 Implementation of the Proposed Method
416(1)
16.4 Numeric Results and Discussion
417(13)
16.4.1 Normal Cases for Various Destinations
417(6)
16.4.2 Monte Carlo Simulations
423(7)
16.5 Conclusion
430(1)
References
431(2)
17 Trajectory-shaping Guidance with Final Speed and Load Factor Constraints 433
17.1 Introduction
433(2)
17.2 Equations of Motion
435(2)
17.3 Guidance Law Overview
437(1)
17.4 Trajectory Shaping Guidance
437(15)
17.4.1 Guidance Form
437(1)
17.4.2 Generalized Closed Form Solutions for TSG
438(10)
17.4.3 Stability Domain of Guidance Coefficients
448(4)
17.5 Final Speed Control Scheme
452(1)
17.6 Model of CAV-H
453(1)
17.7 Results and Discussion
454(6)
17.8 Conclusions
460(1)
References
460
Wanchun Chen is a Professor and Doctoral Supervisor of Beihang University, Beijing, China. He received B.E. and M.E. in flight vehicle design and Ph.D. in flight dynamics and control from Beijing University of Aeronautics and Astronautics (now named Beihang University) in 1986, 1989 and 1995, respectively. His research interests are in the area of flight dynamics, guidance and control of aerospace vehicle, aerospace vehicle integrated design and analysis.  Hao Zhou is a Lecturer and masters Supervisor of Beihang University, Beijing, China. He received B.E. in aerodynamics from National University of Defense Technology and Ph.D. in flight vehicle design from Beijing University of Aeronautics and Astronautics (now named Beihang University) in 1998 and 2006, respectively. His research interests are in the area of flight dynamics, guidance and control of aerospace vehicle, aerospace vehicle integrated design and analysis. Wenbin Yu is an Associate Professor and Doctoral Supervisor of Beihang University, Beijing, China. He received B.E. and Ph.D. in flight vehicle design from Beihang University in 2010 and 2016, respectively. His research interests are in the area of flight dynamics, guidance and control of aerospace vehicle, aerospace vehicle integrated design and analysis.  Liang Yang is a Lecturer and masters Supervisor of Beihang University, Beijing, China. He received B.E. in mechanical engineering and automation from Hunan Agricultural University and Ph.D. in flight vehicle design from Beihang University in 2008 and 2016, respectively. His research interests are in the area of flight dynamics, guidance and control of aerospace vehicle, aerospace vehicle integrated design and analysis.