Applied Nonsingular Astrodynamics
Optimal Low-Thrust Orbit Transfer
Will be published approx. on 16. August 2018
Book
Hardback
476 pages
978-1-108-47236-4 (ISBN)
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.
Reviews / Votes
'This book represents a lifetime of valuable contributions to optimal low-thrust orbit transfer.' John E. Prussing, University of Illinois 'This is a book for specialists in orbital dynamics, authored by one of the leading current practitioners in the field. Its subtitle, 'Optimal Low-thrust Orbit Transfer' reflects one of the principal technical drivers behind the book, namely that an increasing number of satellites in Earth orbit are now using more fuel-efficient ion thrusters which have far lower thrust-levels than their chemically-propelled predecessors. As a consequence, there is an increasing need to optimise the longer trajectories - both in terms of time and distance travelled - that result from the use of this technology.' Stuart Eves, The Aeronautical JournalMore details
Series
Language
English
Place of publication
Cambridge
United Kingdom
Target group
Professional and scholarly
Product notice
sewn/stitched
Cloth over boards
Illustrations
Worked examples or Exercises; 181 Line drawings, black and white
Dimensions
Height: 261 mm
Width: 184 mm
Thickness: 29 mm
Weight
1170 gr
ISBN-13
978-1-108-47236-4 (9781108472364)
Copyright in bibliographic data and cover images is held by Nielsen Book Services Limited or by the publishers or by their respective licensors: all rights reserved.
Schweitzer Classification
Other editions
Additional editions
E-Book
08/2018
Cambridge University Press
€88.99
Available for download
E-Book
07/2018
Cambridge University Press
€106.99
Available for download
Person
Jean Albert Kechichian is a retired Engineering Specialist from The Aerospace Corporation. His career has included senior level engineering positions at NASA's Jet Propulsion Laboratory and at Ford Aerospace. His main areas of contribution are in spaceflight guidance and navigation. He is a Fellow of The American Astronautical Society, and his work has regularly appeared in Acta Astronautica, the Journal of Guidance Control and Dynamics, the Journal of the Astronautical Sciences, and the Journal of Spacecraft and Rockets. He holds Degrees in Aeronautical and Mechanical Engineering from l'Universite de Liege, University of California, Berkeley, and a Ph.D. in Aeronautics and Astronautics from Stanford University.
Content
Preface; 1. The fundamental classic analysis of Edelbaum, Sackett and Malchow, with additional detailed derivations and extensions; 2. The analysis of the six-element formulation; 3. Optimal low-thrust rendezvous using equinoctial orbit elements; 4. Optimal low-thrust transfer using variable bounded thrust; 5. Minimum-time low-thrust rendezvous and transfer using epoch mean longitude formulation; 6. Trajectory optimization using eccentric longitude formulation; 7. Low-thrust trajectory optimization based on epoch eccentric longitude formulation; 8. Mechanics of trajectory optimization using nonsingular variational equations in polar coordinates; 9. Trajectory optimization using nonsingular orbital elements and true longitude; 10. The treatment of the Earth oblateness effect in trajectory optimization in equinoctial coordinates; 11. Minimum-time constant acceleration orbit transfer with first-order oblateness effect; 12. The streamlined and complete set of the nonsingular J2-perturbed dynamic and adjoint equations for trajectory optimization in terms of eccentric longitude; 13. The inclusion of the higher order harmonics in the modeling of optimal low-thrust orbit transfer; 14. Analytic expansions of luni-solar gravity perturbations along rotating axes for trajectory optimization: part 1: the dynamic system; 15. Analytic expansions of luni-solar gravity perturbations along rotating axes for trajectory optimization: part 2: the multipliers system and simulations; 16. Fourth order expansions of the luni-solar gravity perturbations along rotating axes for trajectory optimization; Index.