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Izvorni znanstveni članak
https://doi.org/10.7906/indecs.14.2.12

Control Design for Unmanned Aerial Vehicles with Four Rotors

Denis Kotarski ; Karlovac University of Applied Sciences
Zoran Benić ; Končar D&ST, Zagreb, Croatia
Matija Krznar ; Peti Brod, Zagreb, Croatia

Puni tekst: engleski, pdf (966 KB) str. 236-245 preuzimanja: 3.748* citiraj
APA 6th Edition
Kotarski, D., Benić, Z. i Krznar, M. (2016). Control Design for Unmanned Aerial Vehicles with Four Rotors. Interdisciplinary Description of Complex Systems, 14 (2), 236-245. https://doi.org/10.7906/indecs.14.2.12
MLA 8th Edition
Kotarski, Denis, et al. "Control Design for Unmanned Aerial Vehicles with Four Rotors." Interdisciplinary Description of Complex Systems, vol. 14, br. 2, 2016, str. 236-245. https://doi.org/10.7906/indecs.14.2.12. Citirano 25.01.2020.
Chicago 17th Edition
Kotarski, Denis, Zoran Benić i Matija Krznar. "Control Design for Unmanned Aerial Vehicles with Four Rotors." Interdisciplinary Description of Complex Systems 14, br. 2 (2016): 236-245. https://doi.org/10.7906/indecs.14.2.12
Harvard
Kotarski, D., Benić, Z., i Krznar, M. (2016). 'Control Design for Unmanned Aerial Vehicles with Four Rotors', Interdisciplinary Description of Complex Systems, 14(2), str. 236-245. https://doi.org/10.7906/indecs.14.2.12
Vancouver
Kotarski D, Benić Z, Krznar M. Control Design for Unmanned Aerial Vehicles with Four Rotors. Interdisciplinary Description of Complex Systems [Internet]. 2016 [pristupljeno 25.01.2020.];14(2):236-245. https://doi.org/10.7906/indecs.14.2.12
IEEE
D. Kotarski, Z. Benić i M. Krznar, "Control Design for Unmanned Aerial Vehicles with Four Rotors", Interdisciplinary Description of Complex Systems, vol.14, br. 2, str. 236-245, 2016. [Online]. https://doi.org/10.7906/indecs.14.2.12

Sažetak
Altitude and attitude controlled quadcopter model is used for the behavior and control algorithm testing, before the implementation on the experimental setup. The main objective is the control system design which will achieve good task performance in the combination with the quadcopter dynamic model. Also, for the control model, it is important to be relatively easy to modify for the use of other control algorithms and to be easy to implement on the experimental setup. At the beginning of this article, the control system design process is described. Quadcopter dynamics equations are simplified by applying several assumptions and in that form are used for the controller synthesis. Quadcopter control system is split into inner and outer control loop because the quadcopter is underactuated system which means that the direct control of all of the degrees of freedom is not possible. In the second part, the PI-D control algorithm is described which is applied on the simplified quadcopter dynamic model. The inner loop controls roll, pitch and yaw angles together with the quadcopter altitude. Its outputs are four control variables. Outer loop controls quadcopter X and Y position. Its outputs are roll and pitch desired angles. Regulated quadcopter model behavior is shown for the three types of task. First, the achieving of position in space is simulated. Second, the reference trajectory tracking is shown. Last task shown is the reference trajectory tracking with added periodical disturbances. Simulations show bounded positions error of the regulated quadcopter system using PI-D controller for the different types of tasks performed under different conditions.

Ključne riječi
quadcopter; control design; inner control loop; outer control loop; PI-D controller

Hrčak ID: 154449

URI
https://hrcak.srce.hr/154449

Posjeta: 4.048 *