Attitude Calculation Algorithm for Quadrotor UAV Based on Acceleration Correction Model

Hongbo Fan

doi:10.62051/ijcsit.v3n2.42

Authors

Hongbo Fan

DOI:

https://doi.org/10.62051/ijcsit.v3n2.42

Keywords:

Component, Quadroto UAV, Attitude calculation, Accelerometer, Kalman filtering

Abstract

To enhance the accuracy of quadrotor UAV navigation systems in dynamic environments, we propose an attitude calculation method based on an acceleration correction model. This model estimates and corrects non-gravitational acceleration from the accelerometer, reducing its impact on attitude calculation. Experimental results demonstrate that this algorithm effectively mitigates non-gravitational acceleration interference and significantly improves the accuracy and anti-interference capability of UAV navigation systems.

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References

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