Modeling, simulation, and control of the spacecraft attitude dynamics
Fecha
2021-03-26
Autores
Ocampo, Carlos
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Editor
Universidad EAFIT
Resumen
Based on the three-dimensional dynamics of a rigid body and Newton’s laws, the simplified dynamics of a spacecraft is
studied and described through the systematical representation, mathematical modeling and also by a block diagram
representation, to finally simulates the spacecraft dynamics in the Matlab programming environment called Simulink. It
is paramount to be able to identify and recognize the attitude (often represented with the Euler angles) and position
variables like the degrees of freedom (DOF) of the system and also the linear behavior. All this to conclude up about the
non-linear behavior presented by the accelerations, velocities, positions and Euler angles (attitude) when those
mentioned are plotted against time. In addition to this, the linearized system is found in order to facilitate the control
analysis and stability analysis, at using linear analysis tools of Simulink and concepts like controllability and
observability, reaching the point of determining under the previous concepts to proceed with the control design phase.
Lastly, an uncertainty and sensitivity analysis is realized, by means the Monte-Carlo and the Linear regression method
(in Simulink too), to find the torque like critical model input, since it has the greatest effect on the response variables in
the system; and thus finally, to implement the Linear Quadratic Regulator (LQR) controller, at using the lqr Matlab
function