Overview

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.

Full Product Details

Author:   Pedro A. Capo-Lugo (George C. Marshall Space Flight Center (NASA)) ,  P. M. Bainum (Howard University, USA)
Publisher:   Elsevier Science & Technology
Imprint:   Woodhead Publishing Ltd
Dimensions:   Width: 15.60cm , Height: 2.50cm , Length: 23.40cm
Weight:   1.100kg
ISBN:  

9780857090546

ISBN 10:   0857090542
Pages:   438
Publication Date:   04 October 2011
Audience:   College/higher education ,  Professional and scholarly ,  Undergraduate ,  Postgraduate, Research & Scholarly
Format:   Hardback
Publisher's Status:   Active
Availability:   Manufactured on demand  
We will order this item for you from a manufactured on demand supplier.

Table of Contents

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

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Author Information

Dr Pedro A. Capó-Lugo works as an Aerospace Engineer in the guidance, navigation, and control analysis and design group at NASA George C. Marshall Space Flight Center in Huntsville, Alabama. He has worked in the analysis of control systems of the Ares rockets in the Constellation program, and has analyzed and developed control systems for different satellite missions which include nano and cube satellites. One of his main research interests is formation flying. Dr Peter M. Bainum has 50 years industrial and academic experience. His research in aerospace systems dynamics and control resulted in 220 authored/co-authored publications. His current research interests include: formation flying and dynamics; and control of large flexible space structures. Honours include Fellow AIAA, AAS, AAAS, BIS; Honorary Member Japanese Rocket Society (JRS); IAA Member, and recipient of AIAA International Cooperation, IAF Malina Education, AAS Dirk Brouwer and Sen. Spark Matsunaga International Cooperation Awards. His experience includes participation in the Gemini mission, Apollo program proposal, Department of Defense Gravity Experiment Satellite, Small Astronomy Dual Spin Spacecraft, the Shuttle-Tethered-Subsatellite program, and the NASA proposed Cluster Formation Flying program. Dr. Bainum holds the position of Distinguished Professor of Aerospace Engineering, Emeritus, Howard University, Washington, DC, USA.

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