Spacecraft Dynamics and Control: An Introduction
Preț: 375,00 lei
Disponibilitate: la comandă
ISBN: 9781118342367
Editura: Wiley
Anul publicării: 2013
Pagini: 592
DESCRIERE
Provides the basics of spacecraft orbital dynamics plus attitude dynamics and control, using vectrix notation
Spacecraft Dynamics and Control: An Introduction presents the fundamentals of classical control in the context of spacecraft attitude control. This approach is particularly beneficial for the training of students in both of the subjects of classical control as well as its application to spacecraft attitude control. By using a physical system (a spacecraft) that the reader can visualize (rather than arbitrary transfer functions), it is easier to grasp the motivation for why topics in control theory are important, as well as the theory behind them. The entire treatment of both orbital and attitude dynamics makes use of vectrix notation, which is a tool that allows the user to write down any vector equation of motion without consideration of a reference frame. This is particularly suited to the treatment of multiple reference frames. Vectrix notation also makes a very clear distinction between a physical vector and its coordinate representation in a reference frame. This is very important in spacecraft dynamics and control problems, where often multiple coordinate representations are used (in different reference frames) for the same physical vector.
Provides an accessible, practical aid for teaching and self-study with a layout enabling a fundamental understanding of the subject
Fills a gap in the existing literature by providing an analytical toolbox offering the reader a lasting, rigorous methodology for approaching vector mechanics, a key element vital to new graduates and practicing engineers alike
Delivers an outstanding resource for aerospace engineering students, and all those involved in the technical aspects of design and engineering in the space sector
Contains numerous illustrations to accompany the written text. Problems are included to apply and extend the material in each chapter
Essential reading for graduate level aerospace engineering students, aerospace professionals, researchers and engineers.
Dedication iii
Preface xiii
1 Kinematics 1
1.1 Physical vectors 1
1.1.1 Scalar Product 2
1.1.2 Vector Cross Product 3
1.1.3 Other Useful Vector Identities 5
1.2 Reference Frames and Physical Vector Coordinates 5
1.2.1 Vector Addition and Scalar Multiplication 7
1.2.2 Scalar Product 7
1.2.3 Vector Cross Product 8
1.2.4 Column Matrix Identities 9
1.3 Rotation Matrices 9
1.3.1 Principal Rotations 12
1.3.2 General Rotations 13
1.3.3 Euler Angles 19
1.3.4 Quaternions 20
1.4 Derivatives of Vectors 27
1.4.1 Angular Velocity 28
1.4.2 Angular Velocity in Terms of Euler Angle Rates 31
1.4.3 Angular Velocity in Terms of Quaternion Rates 32
1.5 Velocity and Acceleration 34
1.6 More Rigorous Definition of Angular Velocity 35
References 37
2 Rigid Body Dynamics 39
2.1 Dynamics of a Single Particle 39
2.2 Dynamics of a System of Particles 41
2.3 Rigid Body Dynamics 44
2.3.1 Translational Dynamics 44
2.3.2 Rotational Dynamics 45
2.4 The Inertia Matrix 47
2.4.1 A Parallel Axis Theorem 48
2.4.2 A Rotational Transformation Theorem 49
2.4.3 Principal Axes 49
2.5 Kinetic Energy of a Rigid Body 51
References 53
3 The Keplerian Two-Body Problem 55
3.1 Equations of motion 55
3.2 Constants of the motion 56
3.2.1 Orbital Angular Momentum 56
3.2.2 Orbital Energy 57
3.2.3 The Eccentricity Vector 58
3.3 Shape of a Keplerian orbit 59
3.3.1 Perifocal Coordinate System 61
3.4 Kepler’s Laws 68
3.5 Time of Flight 71
3.5.1 Circular Orbits 71
3.5.2 Elliptical Orbits 71
3.5.3 Parabolic Orbits 75
3.5.4 Hyperbolic Orbits 75
3.6 Orbital Elements 75
3.6.1 Heliocentric-Ecliptic Coordinate System 76
3.6.2 Geocentric-Equatorial Coordinate System 77
3.7 Orbital Elements given Position and Velocity 78
3.8 Position and Velocity given Orbital Elements 80
References 84
4 Preliminary Orbit Determination 85
4.1 Orbit Determination from Three Position Vectors 85
4.2 Orbit Determination from Three Line-of-Sight Vectors 88
4.3 Orbit Determination from Two Position Vectors and Time (Lambert’s Problem) 94
4.3.1 The Lagrangian Coefficients 94
References 98
5 Orbital Maneuvers 99
5.1 Simple ImpulsiveManeuvers 99
5.2 Coplanar Maneuvers 100
5.2.1 Hohmann Transfers 102
5.2.2 Bi-Elliptic Transfers 104
5.3 Plane Change Maneuvers 106
5.4 Combined Maneuvers 108
5.5 Rendezvous 110
References 111
6 Interplanetary Trajectories 113
6.1 Sphere of Influence 113
6.2 Interplanetary Hohmann Transfers 116
6.3 Patched Conics 120
6.3.1 Departure Hyperbola 121
6.3.2 Arrival Hyperbola 123
6.4 Planetary Flyby 126
6.5 Planetary Capture 127
References 129
7 Orbital Perturbations 131
7.1 Special Perturbations 132
7.1.1 Cowell’s Method 132
7.1.2 Encke’s Method 133
7.2 General Perturbations 134
7.3 Gravitational Perturbations due to a Non-Spherical Primary Body 137
7.3.1 The Perturbative Force Per Unit Mass Due to J2 142
7.4 Effect of J2 on the orbital elements 143
7.5 Special Types of Orbits 146
7.5.1 Sun-synchronous orbits 147
7.5.2 Molniya Orbits 147
7.6 Small Impulse Form of the Gauss Variational Equations 148
7.7 Derivation of the Remaining Gauss Variational Equations 149
References 156
8 Low Thrust Trajectory Analysis and Design 157
8.1 Problem Formulation 157
8.2 Coplanar Circle to Circle Transfers 158
8.3 Plane Change Maneuver 160
References 161
9 Spacecraft Formation Flying 163
9.1 Mathematical Description 164
9.2 Relative Motion Solutions 168
9.2.1 Out-of-PlaneMotion 168
9.2.2 In-Plane Motion 168
9.2.3 Alternative Description for In-Plane Relative Motion 170
9.2.4 Further Examination of In-Plane Motion 172
9.2.5 Out-of-PlaneMotion - Revisited 174
9.3 Special Types of Relative Orbits 175
9.3.1 Along-Track Orbits 175
9.3.2 Projected Elliptical Orbits 176
9.3.3 Projected Circular Orbits 178
References 178
10 The Restricted Three-Body Problem 179
10.1 Formulation 179
10.1.1 Equations of Motion 181
10.2 The Lagrangian Points 182
10.2.1 Case (i) 182
10.2.2 Case (ii) 182
10.3 Stability of the Lagrangian Points 183
10.3.1 Comments 184
10.4 Jacobi’s Integral 185
10.4.1 Hill’s Curves 185
10.4.2 Comments on Figure 10.5 187
References 187
11 Introduction to Spacecraft Attitude Stabilization 189
11.1 Introduction to Control Systems 190
11.2 Overview of Attitude Representation and Kinematics 192
11.3 Overview of Spacecraft Attitude Dynamics 193
12 Disturbance Torques on a Spacecraft 195
12.1 Magnetic Torque 195
12.2 Solar Radiation Pressure Torque 195
12.3 Aerodynamic Torque 197
12.4 Gravity-Gradient Torque 199
References 202
13 Torque-Free Attitude Motion 203
13.1 Solution for an Axisymmetric Body 203
13.2 Physical Interpretation of the Motion 209
References 212
14 Spin Stabilization 213
14.1 Stability 213
14.2 Spin Stability of Torque-FreeMotion 215
14.3 Effect of Internal Energy Dissipation 217
References 218
15 Dual-Spin Stabilization 219
15.1 Equations of Motion 219
15.2 Stability of Dual-Spin Torque-FreeMotion 220
15.3 Effect of Internal Energy Dissipation 222
References 228
16 Gravity-Gradient Stabilization 229
16.1 Equations of Motion 230
16.2 Stability Analysis 233
16.2.1 Pitch Motion 233
16.2.2 Roll-Yaw Motion 234
16.2.3 Combined Pitch and Roll/Yaw 237
References 238
17 Active Spacecraft Attitude Control 239
17.1 Attitude Control for a Nominally Inertially Fixed Spacecraft 240
17.2 Transfer Function Representation of a System 241
17.3 System Response to an Impulsive Input 242
17.4 Block Diagrams 243
17.5 The Feedback Control Problem 246
17.6 Typical Control Laws 248
17.6.1 Proportional “P” Control 248
17.6.2 Proportional Derivative “PD” Control 249
17.6.3 Proportional Integral Derivative “PID” Control 250
17.7 Time-Domain Specifications 251
17.7.1 Transient Specifications 252
17.8 Factors that Modify the Transient Behavior 265
17.8.1 Effect of Zeros 265
17.8.2 Effect of Additional Poles 267
17.9 Steady-State Specifications and System Type 268
17.10Effect of Disturbances 274
17.11Actuator Limitations 275
References 277
18 Routh’s Stability Criterion 279
18.1 Proportional-Derivative Control with Actuator Dynamics 280
18.2 Active Dual-Spin Stabilization 282
References 287
19 The Root Locus 289
19.1 Rules for Constructing the Root Locus 290
19.2 PD Attitude Control with Actuator Dynamics - Revisited 297
19.3 Derivation of the Rules for Constructing the Root Locus 301
References 309
20 Control Design by the Root Locus Method 311
20.1 Typical Types of Controllers 313
20.2 PID Design for Spacecraft Attitude Control 317
References 324
21 Frequency Response 327
21.1 Frequency Response and Bode Plots 328
21.1.1 Plotting the Frequency Response as a Function of ω (Bode Plots) 330
21.2 Low-Pass Filter Design 338
References 339
22 Relative Stability 341
22.1 Polar Plots 341
22.2 Nyquist Stability Criterion 343
22.2.1 Argument Principle 344
22.2.2 Stability Analysis of the Closed-Loop System 346
22.3 Stability Margins 352
22.3.1 Stability Margin Definitions 354
References 362
23 Control Design in the Frequency Domain 363
23.1 Feedback Control Problem - Revisited 368
23.1.1 Closed-Loop Tracking Error 369
23.1.2 Closed-Loop Control Effort 370
23.1.3 Modified Control Implementation 371
23.2 Control Design 372
23.2.1 Frequency Responses for Common Controllers 375
23.3 Example - PID Design for Spacecraft Attitude Control 380
References 385
24 Nonlinear Spacecraft Attitude Control 387
24.1 State-Space Representation of the Spacecraft Attitude Equations 387
24.2 Stability Definitions 390
24.2.1 Equilibrium Points 390
24.2.2 Stability of Equilibria 390
24.3 Stability Analysis 392
24.3.1 Detumbling of a Rigid Spacecraft 392
24.3.2 Lyapunov Stability Theorems 395
24.4 LaSalle’s Theorem 397
24.5 Spacecraft Attitude Control with Quaternion and Angular Rate Feedback 399
24.5.1 Controller Gain Selection 401
References 404
25 Spacecraft Navigation 405
25.1 Review of Probability Theory 405
25.1.1 Continuous Random Variables and Probability Density Functions 405
25.1.2 Mean and Covariance 407
25.1.3 Gaussian Probability Density Functions 409
25.1.4 Discrete-TimeWhite Noise 411
25.1.5 Simulating Noise 411
25.2 Batch Approaches for Spacecraft Attitude Estimation 412
25.2.1 Wahba’s Problem 413
25.2.2 Davenport’s q-Method 413
25.2.3 The QUEST Algorithm 416
25.2.4 The TRIAD Algorithm 418
25.2.5 Example 419
25.3 The Kalman Filter 421
25.3.1 The Discrete-Time Kalman Filter 421
25.3.2 The Norm-Constrained Kalman Filter 425
25.3.3 Spacecraft Attitude Estimation Using the Norm-Constrained
Extended Kalman Filter 431
References 438
26 Practical Spacecraft Attitude Control Design Issues 441
26.1 Attitude Sensors 441
26.1.1 Sun-Sensors 441
26.1.2 Three-AxisMagnetometers 443
26.1.3 Earth Sensors 444
26.1.4 Star Trackers 446
26.1.5 Rate Sensors 447
26.2 Attitude Actuators 447
26.2.1 Thrusters 448
26.2.2 Magnetic Torquers 450
26.2.3 ReactionWheels 450
26.2.4 MomentumWheels 452
26.2.5 Control Moment Gyroscopes 452
26.3 Control Law Implementation 453
26.3.1 Time-Domain Representation of a Transfer Function 453
26.3.2 Control Law Digitization 455
26.3.3 Closed-Loop Stability Analysis 458
26.3.4 Sampling Considerations 460
26.4 Unmodeled dynamics 464
26.4.1 Effects of Spacecraft Flexibility 464
26.4.2 Effects of Propellant Sloshing 477
References 478
INDEX 495
Spacecraft Dynamics and Control: An Introduction presents the fundamentals of classical control in the context of spacecraft attitude control. This approach is particularly beneficial for the training of students in both of the subjects of classical control as well as its application to spacecraft attitude control. By using a physical system (a spacecraft) that the reader can visualize (rather than arbitrary transfer functions), it is easier to grasp the motivation for why topics in control theory are important, as well as the theory behind them. The entire treatment of both orbital and attitude dynamics makes use of vectrix notation, which is a tool that allows the user to write down any vector equation of motion without consideration of a reference frame. This is particularly suited to the treatment of multiple reference frames. Vectrix notation also makes a very clear distinction between a physical vector and its coordinate representation in a reference frame. This is very important in spacecraft dynamics and control problems, where often multiple coordinate representations are used (in different reference frames) for the same physical vector.
Provides an accessible, practical aid for teaching and self-study with a layout enabling a fundamental understanding of the subject
Fills a gap in the existing literature by providing an analytical toolbox offering the reader a lasting, rigorous methodology for approaching vector mechanics, a key element vital to new graduates and practicing engineers alike
Delivers an outstanding resource for aerospace engineering students, and all those involved in the technical aspects of design and engineering in the space sector
Contains numerous illustrations to accompany the written text. Problems are included to apply and extend the material in each chapter
Essential reading for graduate level aerospace engineering students, aerospace professionals, researchers and engineers.
Dedication iii
Preface xiii
1 Kinematics 1
1.1 Physical vectors 1
1.1.1 Scalar Product 2
1.1.2 Vector Cross Product 3
1.1.3 Other Useful Vector Identities 5
1.2 Reference Frames and Physical Vector Coordinates 5
1.2.1 Vector Addition and Scalar Multiplication 7
1.2.2 Scalar Product 7
1.2.3 Vector Cross Product 8
1.2.4 Column Matrix Identities 9
1.3 Rotation Matrices 9
1.3.1 Principal Rotations 12
1.3.2 General Rotations 13
1.3.3 Euler Angles 19
1.3.4 Quaternions 20
1.4 Derivatives of Vectors 27
1.4.1 Angular Velocity 28
1.4.2 Angular Velocity in Terms of Euler Angle Rates 31
1.4.3 Angular Velocity in Terms of Quaternion Rates 32
1.5 Velocity and Acceleration 34
1.6 More Rigorous Definition of Angular Velocity 35
References 37
2 Rigid Body Dynamics 39
2.1 Dynamics of a Single Particle 39
2.2 Dynamics of a System of Particles 41
2.3 Rigid Body Dynamics 44
2.3.1 Translational Dynamics 44
2.3.2 Rotational Dynamics 45
2.4 The Inertia Matrix 47
2.4.1 A Parallel Axis Theorem 48
2.4.2 A Rotational Transformation Theorem 49
2.4.3 Principal Axes 49
2.5 Kinetic Energy of a Rigid Body 51
References 53
3 The Keplerian Two-Body Problem 55
3.1 Equations of motion 55
3.2 Constants of the motion 56
3.2.1 Orbital Angular Momentum 56
3.2.2 Orbital Energy 57
3.2.3 The Eccentricity Vector 58
3.3 Shape of a Keplerian orbit 59
3.3.1 Perifocal Coordinate System 61
3.4 Kepler’s Laws 68
3.5 Time of Flight 71
3.5.1 Circular Orbits 71
3.5.2 Elliptical Orbits 71
3.5.3 Parabolic Orbits 75
3.5.4 Hyperbolic Orbits 75
3.6 Orbital Elements 75
3.6.1 Heliocentric-Ecliptic Coordinate System 76
3.6.2 Geocentric-Equatorial Coordinate System 77
3.7 Orbital Elements given Position and Velocity 78
3.8 Position and Velocity given Orbital Elements 80
References 84
4 Preliminary Orbit Determination 85
4.1 Orbit Determination from Three Position Vectors 85
4.2 Orbit Determination from Three Line-of-Sight Vectors 88
4.3 Orbit Determination from Two Position Vectors and Time (Lambert’s Problem) 94
4.3.1 The Lagrangian Coefficients 94
References 98
5 Orbital Maneuvers 99
5.1 Simple ImpulsiveManeuvers 99
5.2 Coplanar Maneuvers 100
5.2.1 Hohmann Transfers 102
5.2.2 Bi-Elliptic Transfers 104
5.3 Plane Change Maneuvers 106
5.4 Combined Maneuvers 108
5.5 Rendezvous 110
References 111
6 Interplanetary Trajectories 113
6.1 Sphere of Influence 113
6.2 Interplanetary Hohmann Transfers 116
6.3 Patched Conics 120
6.3.1 Departure Hyperbola 121
6.3.2 Arrival Hyperbola 123
6.4 Planetary Flyby 126
6.5 Planetary Capture 127
References 129
7 Orbital Perturbations 131
7.1 Special Perturbations 132
7.1.1 Cowell’s Method 132
7.1.2 Encke’s Method 133
7.2 General Perturbations 134
7.3 Gravitational Perturbations due to a Non-Spherical Primary Body 137
7.3.1 The Perturbative Force Per Unit Mass Due to J2 142
7.4 Effect of J2 on the orbital elements 143
7.5 Special Types of Orbits 146
7.5.1 Sun-synchronous orbits 147
7.5.2 Molniya Orbits 147
7.6 Small Impulse Form of the Gauss Variational Equations 148
7.7 Derivation of the Remaining Gauss Variational Equations 149
References 156
8 Low Thrust Trajectory Analysis and Design 157
8.1 Problem Formulation 157
8.2 Coplanar Circle to Circle Transfers 158
8.3 Plane Change Maneuver 160
References 161
9 Spacecraft Formation Flying 163
9.1 Mathematical Description 164
9.2 Relative Motion Solutions 168
9.2.1 Out-of-PlaneMotion 168
9.2.2 In-Plane Motion 168
9.2.3 Alternative Description for In-Plane Relative Motion 170
9.2.4 Further Examination of In-Plane Motion 172
9.2.5 Out-of-PlaneMotion - Revisited 174
9.3 Special Types of Relative Orbits 175
9.3.1 Along-Track Orbits 175
9.3.2 Projected Elliptical Orbits 176
9.3.3 Projected Circular Orbits 178
References 178
10 The Restricted Three-Body Problem 179
10.1 Formulation 179
10.1.1 Equations of Motion 181
10.2 The Lagrangian Points 182
10.2.1 Case (i) 182
10.2.2 Case (ii) 182
10.3 Stability of the Lagrangian Points 183
10.3.1 Comments 184
10.4 Jacobi’s Integral 185
10.4.1 Hill’s Curves 185
10.4.2 Comments on Figure 10.5 187
References 187
11 Introduction to Spacecraft Attitude Stabilization 189
11.1 Introduction to Control Systems 190
11.2 Overview of Attitude Representation and Kinematics 192
11.3 Overview of Spacecraft Attitude Dynamics 193
12 Disturbance Torques on a Spacecraft 195
12.1 Magnetic Torque 195
12.2 Solar Radiation Pressure Torque 195
12.3 Aerodynamic Torque 197
12.4 Gravity-Gradient Torque 199
References 202
13 Torque-Free Attitude Motion 203
13.1 Solution for an Axisymmetric Body 203
13.2 Physical Interpretation of the Motion 209
References 212
14 Spin Stabilization 213
14.1 Stability 213
14.2 Spin Stability of Torque-FreeMotion 215
14.3 Effect of Internal Energy Dissipation 217
References 218
15 Dual-Spin Stabilization 219
15.1 Equations of Motion 219
15.2 Stability of Dual-Spin Torque-FreeMotion 220
15.3 Effect of Internal Energy Dissipation 222
References 228
16 Gravity-Gradient Stabilization 229
16.1 Equations of Motion 230
16.2 Stability Analysis 233
16.2.1 Pitch Motion 233
16.2.2 Roll-Yaw Motion 234
16.2.3 Combined Pitch and Roll/Yaw 237
References 238
17 Active Spacecraft Attitude Control 239
17.1 Attitude Control for a Nominally Inertially Fixed Spacecraft 240
17.2 Transfer Function Representation of a System 241
17.3 System Response to an Impulsive Input 242
17.4 Block Diagrams 243
17.5 The Feedback Control Problem 246
17.6 Typical Control Laws 248
17.6.1 Proportional “P” Control 248
17.6.2 Proportional Derivative “PD” Control 249
17.6.3 Proportional Integral Derivative “PID” Control 250
17.7 Time-Domain Specifications 251
17.7.1 Transient Specifications 252
17.8 Factors that Modify the Transient Behavior 265
17.8.1 Effect of Zeros 265
17.8.2 Effect of Additional Poles 267
17.9 Steady-State Specifications and System Type 268
17.10Effect of Disturbances 274
17.11Actuator Limitations 275
References 277
18 Routh’s Stability Criterion 279
18.1 Proportional-Derivative Control with Actuator Dynamics 280
18.2 Active Dual-Spin Stabilization 282
References 287
19 The Root Locus 289
19.1 Rules for Constructing the Root Locus 290
19.2 PD Attitude Control with Actuator Dynamics - Revisited 297
19.3 Derivation of the Rules for Constructing the Root Locus 301
References 309
20 Control Design by the Root Locus Method 311
20.1 Typical Types of Controllers 313
20.2 PID Design for Spacecraft Attitude Control 317
References 324
21 Frequency Response 327
21.1 Frequency Response and Bode Plots 328
21.1.1 Plotting the Frequency Response as a Function of ω (Bode Plots) 330
21.2 Low-Pass Filter Design 338
References 339
22 Relative Stability 341
22.1 Polar Plots 341
22.2 Nyquist Stability Criterion 343
22.2.1 Argument Principle 344
22.2.2 Stability Analysis of the Closed-Loop System 346
22.3 Stability Margins 352
22.3.1 Stability Margin Definitions 354
References 362
23 Control Design in the Frequency Domain 363
23.1 Feedback Control Problem - Revisited 368
23.1.1 Closed-Loop Tracking Error 369
23.1.2 Closed-Loop Control Effort 370
23.1.3 Modified Control Implementation 371
23.2 Control Design 372
23.2.1 Frequency Responses for Common Controllers 375
23.3 Example - PID Design for Spacecraft Attitude Control 380
References 385
24 Nonlinear Spacecraft Attitude Control 387
24.1 State-Space Representation of the Spacecraft Attitude Equations 387
24.2 Stability Definitions 390
24.2.1 Equilibrium Points 390
24.2.2 Stability of Equilibria 390
24.3 Stability Analysis 392
24.3.1 Detumbling of a Rigid Spacecraft 392
24.3.2 Lyapunov Stability Theorems 395
24.4 LaSalle’s Theorem 397
24.5 Spacecraft Attitude Control with Quaternion and Angular Rate Feedback 399
24.5.1 Controller Gain Selection 401
References 404
25 Spacecraft Navigation 405
25.1 Review of Probability Theory 405
25.1.1 Continuous Random Variables and Probability Density Functions 405
25.1.2 Mean and Covariance 407
25.1.3 Gaussian Probability Density Functions 409
25.1.4 Discrete-TimeWhite Noise 411
25.1.5 Simulating Noise 411
25.2 Batch Approaches for Spacecraft Attitude Estimation 412
25.2.1 Wahba’s Problem 413
25.2.2 Davenport’s q-Method 413
25.2.3 The QUEST Algorithm 416
25.2.4 The TRIAD Algorithm 418
25.2.5 Example 419
25.3 The Kalman Filter 421
25.3.1 The Discrete-Time Kalman Filter 421
25.3.2 The Norm-Constrained Kalman Filter 425
25.3.3 Spacecraft Attitude Estimation Using the Norm-Constrained
Extended Kalman Filter 431
References 438
26 Practical Spacecraft Attitude Control Design Issues 441
26.1 Attitude Sensors 441
26.1.1 Sun-Sensors 441
26.1.2 Three-AxisMagnetometers 443
26.1.3 Earth Sensors 444
26.1.4 Star Trackers 446
26.1.5 Rate Sensors 447
26.2 Attitude Actuators 447
26.2.1 Thrusters 448
26.2.2 Magnetic Torquers 450
26.2.3 ReactionWheels 450
26.2.4 MomentumWheels 452
26.2.5 Control Moment Gyroscopes 452
26.3 Control Law Implementation 453
26.3.1 Time-Domain Representation of a Transfer Function 453
26.3.2 Control Law Digitization 455
26.3.3 Closed-Loop Stability Analysis 458
26.3.4 Sampling Considerations 460
26.4 Unmodeled dynamics 464
26.4.1 Effects of Spacecraft Flexibility 464
26.4.2 Effects of Propellant Sloshing 477
References 478
INDEX 495
Accesul clienţilor
-Top 10
-Cărţi noi
-
344,25 leiPRP: 382,50 lei
1505,52 leiPRP: 1672,80 lei
546,21 leiPRP: 606,90 lei
Promoţii
-
280,00 leiPRP: 350,00 lei
29,25 leiPRP: 45,00 lei
29,25 leiPRP: 45,00 lei
RECENZII