Communication and Optimization for Satellite Attitudes Using Proportional-Integral-Derivative Controller

M Raja¹ , Monish Mathur² , Ugur Guven³ , Om Prakash⁴

¹ Aerospace Engineering Department, UPES, Dehradun, India.
² Aerospace Engineering Department, UPES, Dehradun, India.
³ Aerospace Engineering Department, UPES, Dehradun, India.
⁴ Aerospace Engineering Department, UPES, Dehradun, India.

Section:Research Paper, Product Type: Journal
Vol.7 , Issue.6 , pp.1-6, Dec-2019

Online published on Dec 31, 2019

Copyright © M Raja, Monish Mathur, Ugur Guven, Om Prakash . This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
 

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Abstract :
In the proposed research work to determination of attitude and optimization of control parameters for attitude control and stabilization system. The equations as given to transform Euler angles to Quaternions and vice versa. PID Controller comprises is control loop feedback mechanism. The modelling (MATLAB-SIMULINK) for control parameters are defined and optimized to be actuated via reaction wheels in conjugation with Magneto Torquer. The attitude of the model is determined and then the control equations are adapted so that attitude as stabilized by reaction wheel and the torque rod achieves momentum damping. The stability of the system is demonstrated using Lyapunov function. Numerical simulations has performed on MATLAB to optimize control parameters. Thus, the feasibility and effectiveness of the PID control system as demonstrated.

Key-Words / Index Term :
Quaternion, PID, Wahba’s Loss Function, Lyapunov function

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