Global optimum spacecraft orbit control subject to bounded thrust in presence of nonlinear and random disturbances in a low earth orbit

The primary objective of this work is to develop an effective spacecraft orbit control algorithm suitable for spacecraft orbital maneuver and/or rendezvous. The actual governing equation of a spacecraft orbiting the earth is merely nonlinear. Disturbance forces resulting from aerodynamic drag, oblat...

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Bibliographic Details
Published in:The Egyptian journal of remote sensing and space sciences Vol. 15; no. 1; pp. 1 - 8
Main Author: Habib, Tamer Mekky Ahmed
Format: Journal Article
Language:English
Published: Elsevier B.V 01.06.2012
Elsevier
Subjects:
Drag
Earth oblateness
Orbit control
Random disturbance
Real coded genetic algorithms
Orbit control
Random disturbance
Real coded genetic algorithms
Drag
Earth oblateness
ISSN:1110-9823, 2090-2476
Online Access:Get full text
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Summary:The primary objective of this work is to develop an effective spacecraft orbit control algorithm suitable for spacecraft orbital maneuver and/or rendezvous. The actual governing equation of a spacecraft orbiting the earth is merely nonlinear. Disturbance forces resulting from aerodynamic drag, oblateness of the earth till the fourth order (i.e. J4), and random disturbances are modeled for the initial and target orbits. These disturbances increase the complexity of nonlinear governing equations. Global optimum solutions of the control algorithm parameters are determined throughout real coded genetic algorithms such that the steady state difference between the actual and desired trajectories is minimized. The resulting solutions are constrained to avoid spacecraft collision with the surface of the earth taking into account limited thrust budget.
ISSN:1110-9823
2090-2476
DOI:10.1016/j.ejrs.2011.08.002