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Title

ALGORITHM DESIGN OF SPACECRAFT TRAJECTORY CORRECTION IN DE-ORBIT MANEUVER‏ ‏BY ‎FEEDBACK LINEARIZATION METHOD

Pages

 Start Page 65 | End Page 73

Abstract

 In this paper, the purpose is SPACECRAFT DEsign and correction/fa?page=1&sort=1&ftyp=all&fgrp=all&fyrs=all" target="_blank">TRAJECTORY DESIGN AND CORRECTION in DE-orbit maneuver. According to the ‎systematic requirements, this maneuver is required for a real project and its parameters and values have been ‎set by its system engineering team. In order to achieve the DEsired maneuver, propulsion system must produce ‎the velocity change vector. In practice, due to the unsatisfactory performance and uncertainties in the ‎propulsion system, ideal velocity change vector may not be realized. Consequently, SPACECRAFT DEviates from ‎the DEsired DE-orbit trajectory and it is possible the SPACECRAFT mission fails. So as to avoid this problem and ‎compensate the created DEviation, a controller based on Cowell’s formulation and using FEEDBACK LINEARIZATION ‎method is DEsigned and its performance, after generating and loading DEsired DE-orbit trajectory in the control ‎law (using the orbital elements), will be examined during a DE-orbit maneuver. In this article, for a considered ‎impulsive DE-orbit maneuver, velocity change vector and its execution time which are necessary for transfer ‎from initial orbit to the DE-orbit trajectory, are calculated. The simulation results indicate that, due to technical ‎constraints and the capacity of the propulsion system, the maximum error of DE-boost impulse value and ‎orientation which the controller can compensate are 15% and 20% respectively.

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