Applied Nonsingular Astrodynamics: Optimal Low-Thrust Orbit Transfer

Description

This essential book describes the mathematical formulations and subsequent computer simulations required to accurately project the trajectory of spacecraft and rockets in space, using the formalism of optimal control for minimum-time transfer in general elliptic orbit. The material will aid research students in aerospace engineering, as well as practitioners in the field of spaceflight dynamics, in developing simulation software to carry out trade studies useful in vehicle and mission design. It will teach readers to develop flight software for operational applications in autonomous mode, so to actually transfer space vehicles from one orbit to another. The practical, real-life applications discussed will give readers a clear understanding of the mathematics of orbit transfer, allow them to develop their own operational software to fly missions, and to use the contents as a research tool to carry out even more complex analyses. Cover......Page 1 Front Matter ......Page 3 Cambridge Aerospace Series......Page 4 Applied Nonsingular Astrodynamics: Optimal Low-Thrust Orbit Transfer......Page 5 Copyright ......Page 6 Dedication ......Page 7 Contents ......Page 9 Preface......Page 15 Nomenclature......Page 18 1 The Fundamental Classic Analysis of Edelbaum, Sackett and Malchow, with Additional Detailed Derivations and Extensions......Page 21 2 The Analysis of the Six-Element Formulation......Page 70 3 Optimal Low-Thrust Rendezvous Using Equinoctial Orbit Elements......Page 122 4 Optimal Low-Thrust Transfer Using Variable Bounded Thrust......Page 155 5 Minimum-Time Low-Thrust Rendezvous and Transfer Using Epoch Mean Longitude Formulation......Page 174 6 Trajectory Optimization Using Eccentric Longitude Formulation......Page 200 7 Low-Thrust Trajectory Optimization Based on Epoch Eccentric Longitude Formulation......Page 222 8 Mechanics of Trajectory Optimization Using Nonsingular Variational Equations in Polar Coordinates......Page 247 9 Trajectory Optimization Using Nonsingular Orbital Elements and True Longitude......Page 263 10 The Treatment of the Earth Oblateness Effect in Trajectory Optimization in Equinoctial Coordinates......Page 280 11 Minimum-Time Constant Acceleration Orbit Transfer with First-Order Oblateness Effect......Page 301 12 The Streamlined and Complete Set of the Nonsingular J 2-Perturbed Dynamic and Adjoint Equations for Trajectory Optimization in Terms of Eccentric Longitude......Page 324 13 The Inclusion of the Higher-Order Harmonics in the Modeling of Optimal Low-Thrust Orbit Transfer......Page 348 14 Analytic Expansions of Luni-Solar Gravity Perturbations Along Rotating Axes for Trajectory Optimization: The Dynamic System......Page 381 15 Analytic Expansions of Luni-Solar Gravity Perturbations Along Rotating Axes for Trajectory Optimization: The Multipliers System and Simulations......Page 411 16 Fourth-Order Expansions of the Luni-Solar Gravity Perturbations along Rotating Axes for Trajectory Optimization......Page 444 Index......Page 478