Title: Closed-loop guidance laws for low-thrust spacecrafts

Authors: Iman Shafieenejad; A.B. Novinzadeh

Addresses: Department of Aerospace Engineering, K.N. Toosi University of Technology, P.O. Box: 16765-3381, 4th Tehranpars Square, Vafadar St., East, Tehran, Postal Code: 16565-83911, Iran ' Department of Aerospace Engineering, K.N. Toosi University of Technology, P.O. Box: 16765-3381, 4th Tehranpars Square, Vafadar St., East, Tehran, Postal Code: 16565-83911, Iran

Abstract: This paper attempts to compare the two methods of Takagi-Sugeno (TS) fuzzy logic and neighbouring optimal control (NOC), for closed-loop guidance laws of low-thrust spacecraft system equations. At first, the open-loop optimal guidance is considered as the optimal thrust steering program that will transfer the vehicle from an inclined low earth orbit to a high earth orbit. Secondly, proper closed-loop guidance laws are achieved, as the novelty of this work, to examine the robustness of the two methods with respect to min-effort criterion for low-thrust spacecrafts. This performance index will be better than customary min-time and will be investigated as a new trend in this field for closed-loop guidance. The results illustrate the viability and efficiency of TS and NOC methods as closed-loop guidance laws for low-thrust orbital manoeuvres regarding the robustness of this guidance against disturbances. Finally, results illustrate a better method to achieve closed-loop guidance for low-thrust spacecraft manoeuvres.

Keywords: fuzzy logic; neighbouring optimal control; low-thrust orbital transfer; closed-loop guidance laws; low-thrust spacecraft; optimal thrust steering; orbital manoeuvres; spacecraft orbits; satellites.

DOI: 10.1504/IJMIC.2014.059389

International Journal of Modelling, Identification and Control, 2014 Vol.21 No.1, pp.17 - 28

Published online: 07 Jun 2014 *

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