Magnetic Attitude Control System and Magnetorquers Design for a CubeSat 3U
A magnetic attitude control model to do three-axis stabilization for a Cube Sat 3U for nadir pointing based on the lineal quadratic regulator theory, has been development in this paper. The mathematical model described in the background, involved the gravity gradient and modelled magnetic torque, which involve only remnant magnetic moments because the actuators are air core magnetorquers whose design was optimize using the Lagrange Multipliers. The magnetorquers cannot torque about the local magnetic field direction but if the spacecraft’s orbit is inclined, the direction of the magnetic field vector moves along the orbit and the resulting system is completely controllable and roughly periodic, because this, the Floquet theory can be used. The simulations based in both linear time invariant and linear time varying system. The results prove that the close loop system resulting is stable and the pointing error is less than two degrees before second orbit only for the linear time invariant system. The controller cannot counteract the varying disturbance torques.
How to cite this article:
Ramos LF, Torres GM, Torres EM et al. Magnetic Attitude Control System and Magnetorquers Design for a CubeSat 3U. J Adv Res Aero Space Sci 2021; 8(3&4): 10-16.
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