Ashraf, M., Hendy, H., Sallam, A., Ashry, M., Elhalwagy, Y. (2023). Modeling and analysis for reaction control thruster used for station-keeping maneuvers of a GEO satellite. test, 20(20), 1-11. doi: 10.1088/1742-6596/2616/1/012026
M K Ashraf; H Hendy; A F Sallam; M M Ashry; Y Z Elhalwagy. "Modeling and analysis for reaction control thruster used for station-keeping maneuvers of a GEO satellite". test, 20, 20, 2023, 1-11. doi: 10.1088/1742-6596/2616/1/012026
Ashraf, M., Hendy, H., Sallam, A., Ashry, M., Elhalwagy, Y. (2023). 'Modeling and analysis for reaction control thruster used for station-keeping maneuvers of a GEO satellite', test, 20(20), pp. 1-11. doi: 10.1088/1742-6596/2616/1/012026
Ashraf, M., Hendy, H., Sallam, A., Ashry, M., Elhalwagy, Y. Modeling and analysis for reaction control thruster used for station-keeping maneuvers of a GEO satellite. test, 2023; 20(20): 1-11. doi: 10.1088/1742-6596/2616/1/012026

Modeling and analysis for reaction control thruster used for station-keeping maneuvers of a GEO satellite

International Conference on Aerospace Sciences and Aviation Technology
Volume 20, Issue 20, May 2023, Pages 1-11    PDF (1.09 M)
Document Type: Original Article
DOI: 10.1088/1742-6596/2616/1/012026
Authors
M K Ashraf* 1; H Hendy2; A F Sallam3; M M Ashry4; Y Z Elhalwagy5
1Electrical Engineering Department, MTC, Egypt.
2Dr. of Electrical Engineering, MTC, Egypt.
3Dr. of Mechanical Engineering, Space Technology Center, Egypt.
4Professor of Electrical Engineering, MTC, Egypt.
5Professor of Electrical and Computer Engineering, MTC, Egypt.
Abstract
This paper introduces a theoretical description, force, and torque analysis of a Reaction Control Thruster (RCT) used as an actuator in Attitude Determination and Control Subsystem (ADCS). Mathematical formalization, realization, and implementation are offered to implement the RCT model using Matlab-Simulink. Furthermore, this paper proposes an
accurate RCT Simulink model to control the orientation and stabilizes the Geostationary Earth Orbit (GEO) satellite within its orbit. Finally, a comparative analysis is carried out with an existing satellite platform (Eurostar-3000) based on the Root Mean Square Error (RMSE) for the delta velocity (delta-V) parameter. The outcomes of the model simulation validated the
effectiveness of the proposed approach.
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