Fundamental Spacecraft Dynamics and Control

An extensive text reference includes around an asteroid – a new and important topic
• Covers the most updated contents in spacecraft dynamics and control, both in theory and application
• Introduces the application to motion around asteroids – a new and important topic
• Written by a very experienced researcher in this area

Autorentext

WEIDUO HU, Beihang University, P. R. China

Klappentext
FUNDAMENTAL SPACECRAFT DYNAMICS AND CONTROL One of the most important topics in aerospace engineering, orbital mechanics is the focus of this comprehensive reference text that includes the astrodynamics around an asteroid, an emergent and increasingly crucial field for next generation space research. Readers are first introduced to the fundamentals before learning advanced concepts such as periodic orbit, the Poincaré map, Lagrange bracket, three body problems, the Lambert problem, and orbital determination. Other relevant topics including perturbed orbit motion and spacecraft control, optimal orbit control and attitude capture are clearly detailed and explained.

• Covers the most updated contents in spacecraft dynamics and control, both in theory and application, with many special simulation examples and figures
• Introduces the astrodynamics around asteroids and perturbed orbit motions, concepts increasingly used in space missions
• Written by an experienced researcher in the field
• Includes an appendix explaining the basics of attitude dynamics and also exercise problems at the end of every chapter Fundamental Spacecraft Dynamics and Control is a systematic guide based on years of teaching and research on orbital mechanics and attitude control. It will serve as a useful reference for graduate and advanced students of aerospace engineering.

Zusammenfassung
An extensive text reference includes around an asteroid a new and important topic

• Covers the most updated contents in spacecraft dynamics and control, both in theory and application
• Introduces the application to motion around asteroids a new and important topic
• Written by a very experienced researcher in this area

Inhalt

Preface xi

Acknowledgments xiii

About the Author xv

Part I Orbital Mechanics

1 Introduction 3

1.1 History 3

1.1.1 Kepler's Laws 3

1.1.2 Newton's Laws 4

1.1.3 Space Missions 5

1.2 Coordinate Systems 6

1.2.1 Earth Reference Frame 6

1.2.2 Sun-centered Frame 8

1.2.3 Right Ascension-Declination System 8

1.2.4 Perifocal Coordinate System 9

1.2.5 Satellite Coordinate System 9

1.2.6 Topo-centric-horizon Coordinate System 9

1.3 Time System 10

1.3.1 Clocks 10

1.3.2 Time 11

1.3.3 Reference Motions 14

1.4 References and Further Reading 16

1.5 Summary and Keywords 16

Problems 17

References 17

2 Keplerian Motion 19

2.1 N-body System 19

2.2 The Two-body Problem 21

2.2.1 Geometry for Two Bodies in an Inertial Reference Frame 21

2.2.2 Relative Motion of Two Bodies 21

2.2.3 Constants of the Motion 23

2.2.4 Orbital Path 27

2.3 Orbital Elements 36

2.3.1 Kepler's COEs 36

2.3.2 Alternate Orbital Element Quantities 38

2.3.3 A Calculation Example 38

2.4 Coordinate Transformations 40

2.4.1 Rotation 41

2.4.2 From PQW to IJK 41

2.4.3 From IJK to SEZ 43

2.4.4 Single Radar Observation 45

2.4.5 Summary of the Transformation 48

2.4.6 Three Position Vectors (Gibbs Method) 50

2.5 Time of Flight (TOF) 51

2.5.1 Kepler's Equation (Elliptical Orbits) 51

2.5.2 Numerical Solution 53

2.5.3 Universal Variable X 56

2.5.4 f and g Expansion 60

2.6 Summary and Keywords 62

Problems 63

References 67

3 Orbit Maneuver 69

3.1 Basic Orbital Transfer 69

3.1.1 In-plane (Coplanar) Changes 69

3.1.2 Out-of-plane (Non-coplanar) Changes 71

3.1.3 The Phase Angle 72

3.2 Ballistic Missiles 73

3.2.1 Ballistic Missile Trajectory 74

3.2.2 Effect of the Earth's Rotation 77

3.3 Lunar Missions 80

3.3.1 Possibility of Transfer 80

3.3.2 More Practical Scenario 83

3.4 Interplanetary Travel 87

3.4.1 Sphere of Influence (SOI) 88

3.4.2 Scenario 89

3.4.3 Gravity Assist 93

3.5 Launch Issues, Starting the Mission 96

3.5.1 Launch Time 96

3.5.2 When and Where to Launch 97

3.5.3 Launch Velocity 98

3.5.4 Rockets and Launch Vehicles 100

3.5.5 Reentry 101

3.6 Summary and Keywords 102

Problems 102

References 106

4 Special Topics 107

4.1 Relative Motion CW Equation 107

4.1.1 Equations of Motion 107

4.1.2 Examples 110

4.1.3 J2 Perturbed No-circular Target Orbit 112

4.2 Lambert Problem 113

4.2.1 Lambert's Theorem 114

4.2.2 Culp's Proof of Lambert's Theorem 117

4.2.3 f , g Function Algorithm 119

4.2.4 Examples 120

4.2.5 Comparison of CW and Nonlinear Lambert Analysis 122

4.3 Orbit Determination 123

4.4 Optimal Control 127

4.5 Three-Body Problem CRTBP 132

4.5.1 Equations of Motion 134

4.5.2 Lagrange Points 135

4.5.3 Examples of CRTBP 137

4.6 Summary and Keywords 139

Problems 141

References 145

5 Perturbed Orbital Motions 147

5.1 Special Perturbation 147

5.1.1 General Concept of Perturbation 147

5.1.2 Cowell's Method 148

5.1.3 Encke's Method 148

5.1.4 Variation of Parameters (COEs) 149

5.2 Systematic Method to Derive VOP 151 5.2.1 Variation of Orbital...