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Preface to the Second Edition
The second edition of Space Vehicle Dynamics and Controls includes over 260
pages of new material on the recent advances in dynamical modeling and control
of advanced spacecraft such as agile imaging satellites equipped with control
moment gyros, solar sails, and space solar power satellites. All of the new material
contained in the second edition is based on my own or coauthored technical papers
published in the Journal of Guidance, Control, and Dynamics and/or presented at
various technical meetings during the past 10 years. Minor typographical errors of
the first edition have been corrected. All of the material of the first edition, except
the bibliography, has been retained.
The first edition of this book consisted of four parts. The new Part 5 in the second
edition consists of the following four chapters:
Chapter 11 Control Moment Gyros for Agile Imaging Satellites
Chapter 12 Solar-Sail Dynamics and Control
Chapter 13 Solar-Sail Missions for Asteroid Deflection
Chapter 14 Attitude and Orbit Control of Space Solar Power Satellites
Part 5 is a collection of advanced spacecraft control problems and their prac-
tical solutions obtained by applying the fundamental principles and techniques
emphasized throughout the book.
Chapter 11 presents a comprehensive treatment of the geometric singularity
problem inherent to control-moment-gyro (CMG) systems, and it also describes
practical CMG steering algorithms and feedback control logic for large-angle,
rapid multitarget acquisition and pointing control of agile imaging satellites.
Chapter 12 is concerned with various dynamical modeling and control problems
of solar-sail spacecraft, and it also presents the analysis and design of solar-sail
attitude control systems for interplanetary solar-sailing missions as well as a solar-
sail flight validation mission in a sun-synchronous orbit.
Chapter 13 presents solar-sail mission applications to a complex astrodynamical
problem of changing the trajectory of near-Earth objects (NEOs) to mitigate their
impact threat to the Earth. This chapter is intended to provide the reader with an
overview of such a technically challenging, emerging astrodynamical problem of
deflecting NEOs using the nonnuclear alternatives such as the kinetic impactor,
gravity tractor, and solar sail.
Chapter 14 presents a preliminary conceptual design of an attitude and orbit
control system (AOCS) architecture for a very large, space solar power (SSP)
satellite in geostationary orbit.
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