Fundamentals of AstrodynamicsCourier Dover Publications, 15 jan 2020 - 432 pagina's Developed at the U.S. Air Force Academy, this teaching text is widely known and used throughout the astrodynamics and aerospace engineering communities. Completely revised and updated, this second edition takes into account new developments of the past four decades, especially regarding information technology. Central emphasis is placed on the use of the universal variable formulation, although classical methods are also discussed. The development of the basic two-body and n-body equations of motion serves as a foundation for all that follows. Subsequent topics include orbit determination and the classical orbital elements, coordinate transformations, and differential correction. The Kepler and Gauss problems are treated in detail, and two-body mechanics are applied to the ballistic missile problem. Perturbations, integration schemes and error, and analytic formulations of several common perturbations are introduced. Example problems and exercises appear throughout the text, along with photographs, diagrams, and drawings. Four helpful appendixes conclude the book. Revised and updated reprint of the 1971 Dover original publication. www.doverpublications.com |
Inhoudsopgave
Orbit Determination from Observations | 41 |
Basic Orbital Maneuvers | 123 |
Position and Velocity as a Function | 143 |
Orbit Determination from | 191 |
Ballistic Missile Trajectories | 233 |
Lunar Trajectories | 269 |
Interplanetary Trajectories | 297 |
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Fundamentals of Astrodynamics Roger R. Bate,Donald D. Mueller,Jerry E. White,William W. Saylor Gedeeltelijke weergave - 2020 |
Veelvoorkomende woorden en zinsdelen
altitude angle anomaly Answer approach approximately assume axis ballistic body burnout calculate called Chapter circular orbit components compute conic constant coordinate coordinate system correct defined definition derivative described determine developed difference differential direction distance Earth eccentricity effect ellipse energy equal Equation error example expression Figure flight Force frame function Gauss given gives gravitational hyperbolic inclination injection integration iteration Kepler km/s known launch lunar mass mean measured method missile Moon Moon’s motion moving Note object observations obtain orbit orbital elements parameters period perturbation planet position possible problem radius range reference relative represents result rotation satellite simple solution solve space speed step Substituting trajectory transfer trial true unit universal variable vector velocity zero