Title: Upgrade balance system for CubeSat attitude simulator based on the air bearing platform
By Mahdi Rivandi
Supervisor: Dr. Mehran Mirshams
Advisor: Mr. Mohammad Zarorati
Chairmen: Dr. Mahdi Jafari Nadoushan (K. N. Toosi University of Technology), Dr. Mohammad Ali Noorian (K. N. Toosi University of Technology)
September 22, 2022
In order to test the attitude control of a satellite, it is necessary to have attitude control simulator, and this simulator must also be placed in the condition of balance, including weight. This thesis was carried out in the form of simulation and implementation, to simulate the deviations caused by the difference between the center of mass and the center of rotation, And also the movement of two horizontal operators, which causes rotational and vortex movement in the balance system, is entered as a disturbance in the balance system. For simulation, PID closed loop controller was chosen for three axes. Implementation based on the same observational models, time settings and experimental coefficients, without using control coefficients with an accuracy of 0.2 and 0.5 under Euler angles; the roll and twist became stable in 25 seconds, the presence of the third axis did not have a positive effect on the balance system. Moving masses were used for the horizontal axis, in which we see the roll and pitch changes, and for the third axis, in which we see the yaw changes, a reaction wheel was used.
