PID and Fuzzy-PID control model for quadcopter attitude with disturbance parameter

Endrowednes Kuantama*, Tiberiu Vesselenyi, Simona Dzitac, Radu Tarca

*Corresponding author for this work

Research output: Contribution to journalArticlepeer-review

76 Citations (Scopus)
40 Downloads (Pure)

Abstract

This paper aims to present data analysis of quadcopter dynamic attitude on a circular trajectory, specifically by comparing the modeling results of conventional Proportional Integral Derivative (PID) and Fuzzy-PID controllers. Simulations of attitude stability with both control systems were done using Simulink toolbox from Matlab so the identification of each control system is clearly seen. Each control system algorithm related to roll and pitch angles which affects the horizontal movement on a circular trajectory is explained in detail. The outcome of each tuning variable of both control systems on the output movement is observable while the error magnitude can be compared with the reference angles. To obtain a deeper analysis, wind disturbance on each axis was added to the model, thus differences between each control system are more recognizable. According to simulation results, the Fuzzy-PID controller has relatively smaller errors than the PID controller and has a better capability to reject disturbances. The scaling factors of gain values of the two controllers also play a vital role in their design.

Original languageEnglish
Pages (from-to)519-532
Number of pages14
JournalInternational Journal of Computers, Communications and Control
Volume12
Issue number4
DOIs
Publication statusPublished - Aug 2017
Externally publishedYes

Bibliographical note

Copyright the Publisher 2016-2017. Version archived for private and non-commercial use with the permission of the author/s and according to publisher conditions. For further rights please contact the publisher.

Keywords

  • Quadcopter
  • PID
  • fuzzy-PID
  • Simulink
  • attitude

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