Trajectory Optimization for Spacecraft Collision Avoidance - Couverture souple

Air Force Institute Of Technology

 
9781500903138: Trajectory Optimization for Spacecraft Collision Avoidance
Couverture souple
ISBN 10 : 1500903132 ISBN 13 : 9781500903138
Editeur : CreateSpace Independent Publishing Platform, 2014

Synopsis

The last several decades have resulted in an unfortunate byproduct of space exploration and development: orbital debris. Satellites in Low Earth Orbit have been required to make an ever increasing number of course corrections in order to avoid collisions. Despite efforts to the contrary, collisions continue to occur, each time creating additional debris and increasing the requirement for the remaining satellites to maneuver. Every required maneuver decreases a satellite’s service life. The purpose of this study is to develop a minimum thrust profile to maneuver an orbiting satellite out of its projected error ellipse before a collision occurs. For comparison, both the impulsive and continuous thrust cases were considered as well as in-plane versus out-of plane maneuvering. This study made use of the Radau Pseudospectral Method to develop this minimum thrust profile. This method was run in MATLAB® using General Pseudospectral Optimal Control Software (GPOPS-II). Once the optimal solution was obtained, Systems Tool Kit® was used to simulate the resulting calculated trajectories and confirm avoidance of the error ellipse.

Les informations fournies dans la section « Synopsis » peuvent faire référence à une autre édition de ce titre.

Présentation de l'éditeur

The last several decades have resulted in an unfortunate byproduct of space exploration and development: orbital debris. Satellites in Low Earth Orbit have been required to make an ever increasing number of course corrections in order to avoid collisions. Despite efforts to the contrary, collisions continue to occur, each time creating additional debris and increasing the requirement for the remaining satellites to maneuver. Every required maneuver decreases a satellite’s service life. The purpose of this study is to develop a minimum thrust profile to maneuver an orbiting satellite out of its projected error ellipse before a collision occurs. For comparison, both the impulsive and continuous thrust cases were considered as well as in-plane versus out-of plane maneuvering. This study made use of the Radau Pseudospectral Method to develop this minimum thrust profile. This method was run in MATLAB® using General Pseudospectral Optimal Control Software (GPOPS-II). Once the optimal solution was obtained, Systems Tool Kit® was used to simulate the resulting calculated trajectories and confirm avoidance of the error ellipse.

Les informations fournies dans la section « A propos du livre » peuvent faire référence à une autre édition de ce titre.

Éditeur
CreateSpace Independent Publishing Platform
Date d'édition
2014
Langue
anglais
ISBN 10 
1500903132
ISBN 13 
9781500903138
Reliure
Broché
Nombre de pages
130
Coordonnées du fabricant
non disponible
Personne responsable
non disponible