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Author: Publisher: ISBN: Category : Languages : en Pages : 45
Book Description
The object of this study is to derive a set of equations which predict the results of orbital maneuvers of vehicles using constant low thrust. These equations are developed by simplifying the problem to circular orbits in a two-body dynamic system. The results are presented in three parts. The first part solves for the equation of the coplanar radius change problem. The second finds the equation for the minimum fuel inclination change problem. The third part of this study puts the equations from the first two parts together to solve a minimum fuel transfer problem involving both radius and inclination changes. The solution of the minimum fuel transfer problem is not to perform the total radius change and then perform the total inclination change. Instead, the solution is to perform both radius and inclination changes on a per orbit basis.
Author: Publisher: ISBN: Category : Languages : en Pages : 45
Book Description
The object of this study is to derive a set of equations which predict the results of orbital maneuvers of vehicles using constant low thrust. These equations are developed by simplifying the problem to circular orbits in a two-body dynamic system. The results are presented in three parts. The first part solves for the equation of the coplanar radius change problem. The second finds the equation for the minimum fuel inclination change problem. The third part of this study puts the equations from the first two parts together to solve a minimum fuel transfer problem involving both radius and inclination changes. The solution of the minimum fuel transfer problem is not to perform the total radius change and then perform the total inclination change. Instead, the solution is to perform both radius and inclination changes on a per orbit basis.
Author: T. G. Black Publisher: ISBN: Category : Languages : en Pages : 43
Book Description
An analytic solution to the optimal low thrust problem is developed using a first-order perturbation approach for planar orbit transfers. This solution is verified by comparison with the solution obtained by integrating the equations of motion. For low vehicle accelerations the analytic solution yields results quite close to those obtained by the integrated solution. At higher acceleration levels, however, the analytic solution diverges from the integrated solution. For very low acceleration levels the analytic solution approachs the limiting case of the infinitesimally low thrust spiral solution. Keywords include: Low thrust; Orbit transfer; Perturbation; Optimization.
Author: Howard D. Curtis Publisher: Elsevier ISBN: 0080887848 Category : Technology & Engineering Languages : en Pages : 740
Book Description
Orbital Mechanics for Engineering Students, Second Edition, provides an introduction to the basic concepts of space mechanics. These include vector kinematics in three dimensions; Newton’s laws of motion and gravitation; relative motion; the vector-based solution of the classical two-body problem; derivation of Kepler’s equations; orbits in three dimensions; preliminary orbit determination; and orbital maneuvers. The book also covers relative motion and the two-impulse rendezvous problem; interplanetary mission design using patched conics; rigid-body dynamics used to characterize the attitude of a space vehicle; satellite attitude dynamics; and the characteristics and design of multi-stage launch vehicles. Each chapter begins with an outline of key concepts and concludes with problems that are based on the material covered. This text is written for undergraduates who are studying orbital mechanics for the first time and have completed courses in physics, dynamics, and mathematics, including differential equations and applied linear algebra. Graduate students, researchers, and experienced practitioners will also find useful review materials in the book. NEW: Reorganized and improved discusions of coordinate systems, new discussion on perturbations and quarternions NEW: Increased coverage of attitude dynamics, including new Matlab algorithms and examples in chapter 10 New examples and homework problems
Author: Lawrence H. Hoffman Publisher: ISBN: Category : Newton-Raphson method Languages : en Pages : 60
Book Description
"A computer program has been designed which determines the minimum-burn-time, thrusting, transfer trajectory between two Keplerian orbits. The minimization equations are formulated with constant Lagrange multipliers and solved numerically with the Newton-Raphson method. The solution obtained in this paper is not truly optimum because the control vector has been restricted to constant values (i.e., to be optimum the control vector should be a function of time)."--Page i
Author: Jean Albert Kéchichian Publisher: Springer Nature ISBN: 3030646572 Category : Technology & Engineering Languages : en Pages : 417
Book Description
This book provides a comprehensive analysis of time-fixed terminal rendezvous around the Earth using chemical propulsion. The book has two main objectives. The first is to derive the mathematics of relative motion in near-circular orbit when subjected to perturbations emanating from the oblateness of the Earth, third-body gravity, and atmospheric drag. The mathematics are suitable for quick trajectory prediction and the creation of computer codes and efficient software to solve impulsive maneuvers and fly rendezvous missions. The second objective of this book is to show how the relative motion theory is applied to the exact precision-integrated, long-duration, time-fixed terminal rendezvous problem around the oblate Earth for the general elliptic orbit case. The contents are both theoretical and applied, with long-lasting value for aerospace engineers, trajectory designers, professors of orbital mechanics, and students at the graduate level and above.
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Author: Samuel J. Domino (2LT, USAF., Jr)
Author: Robert W. Roig
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Author: T. G. Black
Author: Howard D. Curtis
Author: Lawrence H. Hoffman
Author: Wilbur F. Dobson
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Author: Jean Albert Kéchichian