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Orbital Mechanics and Formation Flying
A Digital Control Perspective
P A Capó-Lugo (Author), P M Bainum (Author)
9780857090546
Hardback, published 4 October 2011
438 pages
23.3 x 15.6 x 2.8 cm, 1.1 kg
Aimed at students, faculty and professionals in the aerospace field, this book provides practical information on the development, analysis, and control of a single and/or multiple spacecraft in space. This book is divided into two major sections: single and multiple satellite motion. The first section analyses the orbital mechanics, orbital perturbations, and attitude dynamics of a single satellite around the Earth. Using the knowledge of a single satellite motion, the translation of a group of satellites called formation flying or constellation is explained. Formation flying has been one of the main research topics over the last few years and this book explains different control approaches to control the satellite attitude motion and/or to maintain the constellation together. The control schemes are explained in the discrete domain such that it can be easily implemented on the computer on board the satellite. The key objective of this book is to show the reader the practical and the implementation process in the discrete domain.
Dedication List of figures List of tables List of symbols Acknowledgements Preface About the authors Chapter 1: Introduction 1.1 Introduction to the book 1.2 Book division Chapter 2: Two body orbital motion Abstract: 2.1 Introduction to orbital motion 2.2 Constraints and generalized coordinates 2.3 Lagrange’s equation 2.4 System of particles 2.5 Two body orbital motion problem 2.6 Orbital equations of motion 2.7 Energy and velocity of orbiting bodies 2.8 Escape velocity 2.9 Earth Coordinate Inertial (ECI) system 2.10 Period of an orbit 2.11 Development of Kepler’s equation 2.12 Suggested problems Chapter 3: Orbital perturbations in the two body motion Abstract: 3.1 Introduction to disturbance effects 3.2 Lagrange planetary equations 3.3 Perturbation due to the earth oblateness 3.4 The near-Earth atmosphere effects 3.5 Solar radiation pressure force 3.6 Other disturbance effects 3.7 Suggested problems Chapter 4: Frame rotations and quaternions Abstract: 4.1 Introduction to rotations and quaternions 4.2 Two-dimensional frame rotations 4.3 Three-dimensional frame rotations 4.4 Example of frame rotations 4.5 Quaternion definition and rotations 4.6 Quaternion to Euler angle relations 4.7 Suggested problems Chapter 5: Rigid body motion Abstract: 5.1 Introduction to attitude dynamics 5.2 Rate of change of a vector 5.3 Moment of inertia 5.4 Principal moments of inertia 5.5 Energy formulation 5.6 Rate of change of a quaternion 5.7 Ares V equations of motion 5.8 Suggested problems Chapter 6: Environmental and actuator torques Abstract: 6.1 Introduction to torque formulation 6.2 Environmental torques 6.3 Actuator (or control) torques 6.4 Suggested problems Chapter 7: Continuous and digital control systems Abstract: 7.1 Introduction to methods of designing continuous and discrete control systems 7.2 Ares V equations of motion for first stage flight 7.3 Continuous control formulation 7.4 Discrete control formulation 7.5 Adaptive and intelligent controls 7.6 Suggested problems Chapter 8: Example Abstract: 8.1 Introduction to examples in spacecraft attitude dynamics and control 8.2 Nanosatellite problem definition 8.3 B-dot controller for fast corrections 8.4 Linear quadratic regulator for attitude correction 8.5 Linear quadratic regulator control weight design 8.6 Suggested problems Chapter 9: Formation flying Abstract: 9.1 Introduction to formation flying 9.2 Tschauner–Hempel formulation 9.3 Clohessy–Wiltshire formulation 9.4 Earth oblateness and solar effects in formation flying 9.5 Lawden solution 9.6 Discrete optimal control problem for formation flying 9.7 Formation flying controller implementation 9.8 Suggested problems Chapter 10: Deployment procedure for a constellation Abstract: 10.1 Introductory comments 10.2 Desired conditions of the satellites in the proposed tetrahedron constellation 10.3 Transfer from a circular orbit to the elliptical orbit (stage 1) 10.4 Station-keeping procedure (stage 2) 10.5 Deployment procedure for the tetrahedron constellation 10.6 Remarks 10.7 Suggested problems Chapter 11: Reconfiguration procedure for a constellation Abstract: 11.1 Introduction to the reconfiguration process of a constellation 11.2 Data mining process of the Lagrange planetary equations 11.3 Fuzzy logic controller 11.4 Phase I to II in-plane motion fuzzy logic control system 11.5 Phase II to III in-plane motion fuzzy logic controller 11.6 Out-of-plane motion correction 11.7 Some solutions for the reconfiguration procedures 11.8 Implementation of the fuzzy logic controller 11.9 Adaptive control scheme for reconfiguration procedure 11.10 Remarks 11.11 Suggested problems Appendix: Formulae relating to orbital mechanics Index
Subject Areas: Aerospace & aviation technology [TRP]
