Increasing The Attitude Estimation Accuracy of a 1U CUBESAT on Low Orbit Using the Developed Extended Kalman Filter Algorithm
Keywords:
CUBESAT, Extended Kalman Filter , Attitude Estimation ,Attitude Accuracy , Prediction, Circular Printed Coil PCB.Abstract
This research studies, analyzes, and develops the extended Kalman filter algorithm to increase its accuracy in estimating the attitude of a CUBESAT with a size of 1U and dimensions of 10 * 10 * 10 cm^3 at a low altitude of 600 km and a weight of 1.33 kg. This research also shows the components of the control system for the stability of the cubic satellite and its mechanism of action, Simulations were made for the control and attitude estimation systems using the MATLAB/R2020a environment. The nature of the orbit within which the cubic satellite moves is circular.
This research demonstrated the effectiveness of the developed EDEKF attitude estimation algorithm in increasing the position accuracy of the CUBESAT by 2.79 times over the EKF filter, with an improvement rate of 64.1%. It also contributed to increasing the stability of the CUBESAT on orbit by 1.73 times, with an average error of 0.01%. The EDEKF algorithm was also able to reduce the settling time of the CUBESAT in orbit to a value of 130.65 minutes, which is approximately 1.52 times that of the EKF filter.
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