Hamiltonian Perturbation Solutions for Spacecraft Orbit Prediction
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Martín Lara
About this book
Analytical solutions to the orbital motion of celestial objects have been nowadays mostly replaced by numerical solutions, but they are still irreplaceable whenever speed is to be preferred to accuracy, or to simplify a dynamical model. In this book, the most common orbital perturbations problems are discussed according to the Lie transforms method, which is the de facto standard in analytical orbital motion calculations.
Due to an oversight, an error slipped in Section 4.1 of the book, where it is implicitly assumed the case of the Kepler problem. The following text should replace Sections 4.1 and 4.2 of the book. Cross-references may be affected with the new writing. In particular, former crossed references to Eq.(4.3) should now point to current Eq.(4.12). Please find the Erratum below.
- Discuss perturbations originated from the non-homogeneous distribution of the mass of the Earth and lunisolar perturbations.
- Illustrates the Lie transforms method through several different solutions to the restricted three-body problem.
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Supplementary Materials
Topics
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Frontmatter
I -
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Preface
V -
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Contents
IX -
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1 Introduction
1 - Part I: Hamiltonian perturbations by Lie transforms
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2 The method of Lie transforms
29 -
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3 Application to integrable problems
45 - Part II: Perturbed elliptic motion: Artificial satellite theory
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4 The Kepler problem
77 -
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5 The main problem of the artificial satellite
92 -
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6 Zonal perturbations
124 -
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7 Tesseral perturbations
176 -
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8 Lunisolar perturbations
203 -
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9 Non-conservative effects
235 - Part III: Relative motion and perturbed non-Keplerian motion
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10 The Hill problem
253 -
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11 Motion inside Hill’s sphere
265 -
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12 Motion about the libration points
295 -
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13 Quasi-satellite orbits
313 -
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Bibliography
337 -
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Index
371
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