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Analysis and design of 3-axis attitude control structure of small satellite mission using reaction wheel / Ahmad Adhwa’ Mohamad Basri

Analysis and design of 3-axis attitude control structure of small satellite mission using reaction wheel_ Ahmad Adhwa’ Mohamad Basri_A2_2011_NI
Tesis ini adalah tentang analisis dan rekabentuk struktur kawalan atitud tiga paksi untuk misi satelit kecil meenggunakan roda reaksi. Merekabentuk kawalan atitud adalah tugas yang penting dimana pencapaian misi dan kelangsungan hidup satelit bergantung kepadanya. Teknik kawalan aktif adalah pilihan terbaik kerana ia dapat memberikan kepersisan atitud yang tinggi tetapi ia kompleks dan mahal. Kawalan aktif menggunnakn alat momentum luar atau aktuator untuk menghasilkan momen kawalan. Dalam tesis ini, empat roda reaksi teleh digunakan sebai aktuator. Dengan menggunakan empat roda reaksi merupakan pilihan terbaik untuk memastikan kelangsunagn hidup satelit. Simulasi telah dijalankan menggunakan Matlab®-Simulink™ dengan mengimplikasikan persamaan yang berkenaan yang datang dari model orbit, gangguan luaran dan persamaan dinamik satelit. Pengawal PD telah digunakan untuk menghasilkan momen kawalan. Keputusan dianalisis dari sudut kesalahan atitud, momentum sudut, momen dan prestasi atitud. Berdasarkan simulasi, stuktur kawalan atitud tiga paksi. ______________________________________________________________________________________ This thesis is about analysing and designing 3-axis attitude control structure for small satellite mission using reaction wheel. Designing an attitude control is an important task where the mission achievement and survival of the satellite depends on it. Active control technique is the best option as it can provide higher attitude accuracy but it is relatively complex and more expensive compared to passive control system. Active control system uses external momentum device or actuator to generate control torque. In this thesis, four reaction wheels have been used as the actuator. Using four reaction wheels is the best option to ensure the survival of the satellite. Simulation was done using Matlab®-Simulink™ by implementing the governing equations from the orbit model, external disturbances and satellite dynamic equation. PD controller was used to generate the control torque. The results were analyzed in terms of attitude error, angular momentum, torque and attitude performance. Based on the simulation, the 3-axis attitude control structure was successfully designed.
Contributor(s):
Ahmad Adhwa’ Mohamad Basri - Author
Primary Item Type:
Final Year Project
Language:
English
Subject Keywords:
satellite mission ; orbit model; 3-axis attitude
First presented to the public:
5/1/2011
Original Publication Date:
7/29/2019
Previously Published By:
Universiti Sains Malaysia
Place Of Publication:
School of Aerospace Engineering
Citation:
Extents:
Number of Pages - 58
License Grantor / Date Granted:
  / ( View License )
Date Deposited
2019-07-29 11:10:34.489
Date Last Updated
2020-04-29 13:32:59.996
Submitter:
Nor Hayati Ismail

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