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This paper presents has as objective to design of an autopilot for an unmanned aerial vehicle (UAV) in phase of cruise flight, that is able to provide pilot age support and improvement of the aircraft performance, both in clear and severe weather conditions, including rain, gusty and crosswinds. Also, have a low cost to implement in future applications. First, the mathematical modeling of the aircraft’s dynamic system was performed, which includes the three axes of stability, namely longitudinal, lateral and directional, using the softwares Matlab and AVL (Athena Vortex Lattice) as support. Then, the proportional–integral–derivative (PID) controllers were design educing the Ziegler-Nichols criterion and the root-locus method, so that, the system achieve the design control requirements such as overshoot, peak time and damping. After, the design of all controllers, the chosen air craft was designed in the X-Plane software using the Plane Maker tool, where all its physical measurements and aerodynamic, structural, stability, control and performance were applied. Lastly, a network connection was established using the UDP protocol between the Matlab and X-Plane software, so that the project obtained in real time the response of the aircraft by applying each controller in a virtual environment, but very close to reality. The results show that the designed controllers achieve the established requirements, showing good responses in normal and severe weather conditions, Cite as: NL Vilaça et al. "Projeto de um piloto automático para um veículo aéreo não tripulado em fase de voo de cruzeiro". In: EUROPEAN ACADEMIC RESEARCH, Vol. IX, Issue 6/September 2021, pp. 3428-3451.

This paper presents has as objective to design of an autopilot for an unmanned aerial vehicle (UAV) in phase of cruise flight, that is able to provide pilot age support and improvement of the aircraft performance, both in clear and severe weather conditions, including rain, gusty and crosswinds. Also, have a low cost to implement in future applications. First, the mathematical modeling of the aircraft’s dynamic system was performed, which includes the three axes of stability, namely longitudinal, lateral and directional, using the softwares Matlab and AVL (Athena Vortex Lattice) as support. Then, the proportional–integral–derivative (PID) controllers were design educing the Ziegler-Nichols criterion and the root-locus method, so that, the system achieve the design control requirements such as overshoot, peak time and damping. After, the design of all controllers, the chosen air craft was designed in the X-Plane software using the Plane Maker tool, where all its physical measurements and aerodynamic, structural, stability, control and performance were applied. Lastly, a network connection was established using the UDP protocol between the Matlab and X-Plane software, so that the projectobtained in real time the response of the aircraft by applying each controller in a virtual environment, but very close to reality. The results show that the designed controllers achieve the established requirements, showing good responses in normal and severe weather conditions